# Mathematical Problems in Engineering, Aerospace and

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Mathematical Problems in Engineering, Aerospace and

PROGRAM & ABSTRACT World Congress: 8th International Conference on Mathematical Problems in Engineering, Aerospace and Sciences São José dos Campos, Brazil, June 30- July 3, 2010 Co-Sponsored by AIAA: American Institute of Aeronautics and Astronautics IEEE: Institute of Electrical and Electronics Engineers IFNA: International Federation of Nonlinear Analysts IFIP: International Federation of Information Processing INPE: Brazilian Institute for Space Research FAPESP: Fundação de Amparo à Pesquisa do Estado de São Paulo CAPES: Coordenação de Aperfeiçoamento de Pessoal de Nível Superior CSP: Cambridge Scientific Publishers, Cambridge, UK Wolfram Research Welcome Message from the Conference General Chair As the general chair of the conference, I am happy to welcome you all to the 2010 World Congress - 8th International Conference on Mathematical Problems in Engineering, Aerospace and Sciences. With the natural beauty and rich cultural activities of São Paulo state and also the world-renowned areas of Brazil, the INPE location is an outstanding venue for the conference. The 7th International Conference was held in Genoa, Italy in 2008, and shattered the attendance records of all the previous conferences. This year, in São Jose dos Campos, despite the current world wide economic constraints, we have an even larger number of attendees/delegates and there were many more who wanted to attend but could not, due to lack of funding. We have an excellent program with several keynote addresses, general sessions, and special sessions on areas including: neural network dynamics, unmanned aerial vehicles, and advances in nonlinear differential equations, stability and Lyapunov theory, contributions of PhD Students, mathematical research in dynamical systems theory, methods of nonlinear analysis for partial differential equations, advances in fractional differential equations. Petri nets for complex systems, system identification, theory and application in aerospace, biology, engineering and science, nuclear power and research systems modeling, integral equations and their applications. There are also mini symposia on aeroelasticty, astrodynamics, spacecraft attitude dynamics and control, mathematical modeling and applications in electrical, aerospace and control engineering, multidisciplinary design and optimization in aerospace industry. I would like to thank the international advisory committee and the international organizing committee, the international awards committee, the local advisory and local organizing committee, the sponsors AIAA (American Institute of Aeronautics and Astronautics), IEEE (Institute of Electrical and Electronics Engineers), IFNA (International Federation of Nonlinear Analysts), IFIP (International Federation of Information Processing), INPE (Brazilian Institute for Space Research), FAPESP (Fundação de Amparo à Pesquisa do Estado de São Paulo, CAPES (Coordenação de Aperfeiçoamento de Pessoal de Nível Superior), Cambridge Scientific Publishers, UK and Wolfram Research for their assistance and support in the preparation of the conference. I also wish to express my special thanks to all who have helped me in planning the chairing of sessions to make this conference a very successful event. Finally, I would especially like to thank the local organizers Antonio Prado and Vivian Gomes, the conference coordinator Eva Kaslik, and the administrative chair Jose Ruiz for their tireless efforts to make this a successful conference. I hope that you all enjoy the conference, have an exciting scholarly cooperation, collaboration and interaction, and have a pleasant stay in Brazil Seenith Sivasundaram 1 Conference Information Registration Registration for the conference will be open at the following times, in the LIT building: Tuesday, June 29 Wednesday, June 30 Thursday, July 1 Friday, July 2 Saturday, July 3 2:00 PM – 5:00 PM 8:00 AM – 6:00 PM 8:30 AM – 6:00 PM 8:30 AM – 12.40 PM 9:00 AM – 12:00 PM Internet Wireless internet access is available in the LIT building, as well as a computer for general use. Lunch breaks The INPE restaurant offers a self service buffet, at the price of 14,00 BRL per kilo. There is also a cafeteria (near LIT), which offers coffee, drinks and snacks during all day. Reception – Wednesday, June 30, 6:00 PM - LIT There will be a welcome reception (cheese & wine party) in the LIT lobby at the end of the first conference day. Banquet – Friday, July 2, 8:00 PM Churrascaria Vila D'Aldeia - http://www.villadaldeia.com.br/ The banquet will take place in a very nice barbecue restaurant. There is a large buffet with salads, cheese and vegetables. The main attraction of the place is the delicious Brazilian barbecue served in an all-you-can-eat basis. They also serve grilled chicken and sea food. The following drinks are included: water, soft drinks, juices, beer and caipirinha (a delicious tradicional Brazilian drink, based on sugar, lemon and sugar cane alcoohol) and one dessert of your choice. The banquet is included in the registration fee. Additional tickets (for accompanying persons), can be purchased at the registration desk. 2 Wolfram Research Tutorial: An Overview of Mathematica for Education Presented by Igor Canales Antonio Thursday, July 1, 1:10-2:10 PM - LIT This seminar provides an overview of the Mathematica functionality that makes it easy for educators to integrate the software into higher education classrooms and research facilities. Whether you have used Mathematica for years or have no technical computing experience, you'll see many examples of Mathematica's use for education that can be implemented immediately. Resources and presentation materials are made available to participants. Igor Canales Antonio is a lead software developer in the Software Technology Group at Wolfram Research, Inc. Igor was born in Sao Paulo and joined Wolfram Research in 2003 after receiving his Bachelor of Science in Computer Science from the University of Illinois at Urbana-Champaign. He is responsible for development of many of Mathematica's external data handling capabilities, which allows individuals to import and export data to hundreds of file formats. 3 4 7.00- 5.00-5.30 5.30-6.00 6.00-6.30 6.30-7.00 Aeroelasticity RECEPTION - LIT System Identification System Identification IAI - Amphitheatre SS10 coffee break - LIT 4.30-5.00 LIT - Small Auditorium M3 Spacecraft Attitude Dynamics and Control Keynote talks - LIT - Main Auditorium KEYNOTE: Sandro da Silva Fernandes KEYNOTE: Sunil L. Kukreja KEYNOTE: Jose Manoel Balthazar 2.00-2.50 2.50-3.40 3.40-4.30 Parallel sessions LIT - Room 1 SS2 Unmanned Aerial Vehicles lunch break LIT - Main Auditorium M1 Aeroelasticity 1.00-2.00 11.00-11.30 11.30-12.00 12.00-12.30 12.30-1.00 IAI - Amphitheatre SS10 coffee break - LIT 10.30-11.00 Parallel sessions LIT - Room 1 SS2 Unmanned Aerial Vehicles Keynote talk - LIT - Main Auditorium KEYNOTE: A.V. Balakrishnan 9.40-10.30 LIT - Small Auditorium M3 Spacecraft Attitude Dynamics and Control INAUGURATION - LIT - Main Auditorium 9.00-9.40 LIT - Main Auditorium M1 POSTER SESSION - LIT REGISTRATION - LIT 9.00-6.00 8.00- WEDNESDAY - JUNE 30 IAI - Auditorium SS7 Methods of Nonlinear Analysis for PDE General Session 1 IAI - Auditorium Gen 1 5 4.30-5.00 5.00-5.30 5.30-6.00 6.00-6.30 6.30-7.00 Astrodynamics coffee break - LIT 4.00-4.30 Petri nets for complex systems IAI - Amphitheatre SS9 Keynote talks - LIT - Main Auditorium KEYNOTE: Silvia Giuliatti Winter KEYNOTE: Irena Lasiecka 2.20-3.10 3.10-4.00 LIT - Small Auditorium SS12 Integral Equations and their Applications Wolfram Research Tutorial: An Overview of Mathematica for Education 1.10-2.10 Parallel sessions LIT - Room 1 SS11 Nuclear Power and Research Systems Modeling lunch break LIT - Main Auditorium M2 Astrodynamics IAI - Amphitheatre SS9 Petri nets for complex systems 12.40-2.20 10.40-11.10 11.10-11.40 11.40-12.10 12.10-12.40 Parallel sessions LIT - Room 1 SS11 Nuclear Power and Research Systems Modeling coffee break - LIT 10.10-10.40 LIT - Small Auditorium M3 Spacecraft Attitude Dynamics and Control Keynote talks - LIT - Main Auditorium KEYNOTE: Othon C. Winter KEYNOTE: Brian White 8.30-9.20 9.20-10.10 LIT - Main Auditorium M2 POSTER SESSION - LIT REGISTRATION - LIT 9.00-6.00 8.30- THURSDAY - JULY 1 IAI - Auditorium SS3 Advances in Nonlinear Differential Equations General Session 2 IAI - Auditorium SS9 6 8.00- 4.30-5.00 5.00-5.30 5.30-6.00 Astrodynamics BANQUET - Churrascaria Vila D'Aldeia IAI - Amphitheatre M4 Math. Applications in Electrical, Aerospace and Control Engineering 4.00-4.30 Parallel sessions LIT - Room 1 SS1 Neural Network Dynamics coffee break - LIT 2.20-3.10 3.10-4.00 LIT - Small Auditorium SS4 + SS8 Stability + Fractional Differential Eq, Keynote talks - LIT - Main Auditorium KEYNOTE: Stanislav N. Vassilyev KEYNOTE: Elbert Macau Neural Network Dynamics lunch break LIT - Main Auditorium M2 Astrodynamics IAI - Amphitheatre M4 Mathematical Applications in Electrical, Aerospace and Control Engineering 12.40-2.20 10.40-11.10 11.10-11.40 11.40-12.10 12.10-12.40 Parallel sessions LIT - Room 1 SS1 coffee break - LIT 10.10-10.40 LIT - Small Auditorium SS6 Mathematical Research in Dynamical Systems Theory Keynote talks - LIT - Main Auditorium KEYNOTE: Toshiya Nakamura KEYNOTE: Firdaus E. Udwadia 8.30-9.20 9.20-10.10 LIT - Main Auditorium M2 POSTER SESSION - LIT REGISTRATION - LIT 9.00-6.00 8.30- FRIDAY - JULY 2 IAI - Auditorium M5 Multidisciplinary Design and Optimization IAI - Auditorium M5 Multidisciplinary Design and Optimization in Aerospace Industry 7 11.30-12.00 12.00-12.30 12.30-1.00 1.00-1.30 1.30-2.00 2.00-2.30 11.00-11.30 8.30-9.20 9.20-10.10 10.10-11.00 9.00- Aeroelasticity LIT - Main Auditorium M1 LIT - Small Auditorium SS5 Contribuitions of PhD students and post-doctoral researchers General Session 3 Parallel sessions LIT - Room 1 Gen 3 coffee break - LIT END OF CONFERENCE Keynote talks - LIT - Main Auditorium KEYNOTE: Robert M.M. Mattheij KEYNOTE: Naira Hovakimyan KEYNOTE: S.N. Balakrishnan REGISTRATION - LIT SATURDAY - JULY 3 IAI - Amphitheatre M4 Math. Applications in Electrical, Aerospace and Control Eng. 9.00-9.30 9.30-10.00 10.00-10.30 10.30-11.00 IAI - Auditorium M5 Multidisciplinary Design and Optimization in Aerospace Ind Aeroelasticity LIT - Small Auditorium M1 Wednesday, June 30 MORNING PLENARY SESSION – LIT - Main Auditorium 9.00-9.40 Inauguration 9.40-10.30 Keynote Talk: A. V. BALAKRISHNAN Title: Flutter Analysis in Viscous Flow Chair: Luiz Carlos Góes 10.30-11.00 COFFEE BREAK PARALLEL SESSIONS MINISYMPOSIUM 1. Modern Aeroelasticity LIT - Main Auditorium Chair: Jiro Nakamichi 11.00-11.30 11.30-12.00 12.00-12.30 12.30-1.00 Transonic Aeroelasticity: Theoretical and Computational Challenges Oddvar O. Bendiksen Aeroelastic Analysis of a Typical Section Using of Shape Memory Wire Actuator Vinícius Piccirillo, Luiz Carlos Sandoval Goes, Jose Manoel Balthazar Aeroelastic Behavior of a Wing with a Magnetorheological Hysteretic Model for the Damping Kleber Augusto Lisboa Castão, Luiz Carlos Sandoval Goes, José Manoel Balthazar Flutter solution techniques and their applications Eulo Antonio Balvedi Jr., Roberto Gil Annes da Silva MINISYMPOSIUM 3. Spacecraft Attitude Dynamics and Control LIT - Small Auditorium Chair: Luiz Carlos DeSouza 11.00-11.30 11.30-12.00 12.00-12.30 12.30-1.00 Reduced order attitude dynamic model of a satellite with reaction wheels and appendages Valdemir Carrara IMU Calibration Procedure for a Redundant Tetrahedral Gyro configuration with Wavelet De-noising Élcio Jeronimo de Oliveira, Waldemar de Castro Leite Filho, Ijar Milagres da Fonseca Differential Games of Stabilization Ximena Cubillos, Susana Dias, Luiz Gadelha, Anna Guerman, Georgi Smirnov Performance Comparison of Attitude Determination Algorithms in a Microcontroller Platform Ricardo Oliveira Duarte, Luiz Siqueira Martins-Filho, Hélio Koiti Kuga 8 SPECIAL SESSION 2. Unmanned Aerial Vehicles LIT – Room 1 Chair: Krzysztof Slavomir Sibilski 11.00-11.30 11.30-12.00 12.00-12.30 12.30-1.00 Nonlinear flight dynamics analysis of flapping wing micro-air vehicle model Victor Mwenda Mwongera, Mark Lowenberg UAS test platform for parameter identification of powered paraglider Andras Nagy, Jozsef Rohacs Modeling and simulation of flapping wings nano-robots dynamics of flight Krzysztof Slavomir Sibilski Structural modeling and optimization of a joined-wing configuration of a high-altitude long-endurance (HALE) aircraft at global and local levels Valentina Kaloyanova, Karman Ghia, Urmila Ghia SPECIAL SESSION 10. System identification: Theory and Application in Aerospace, Biology, Engineering and Science IAI – Amphitheatre Chair: Sunil L. Kukreja 11.00-11.30 11.30-12.00 12.00-12.30 12.30-1.00 Robust nonlinear estimation in case of noises of unknown statistics Endre Nagy System Identification using Interval Analysis Erik-Jan van Kampen, Qi-Ping Chu, Bob Mulder Flutter Prediction Analysis using Output Only Flight Test Jie Zeng, Sunil L. Kukreja Global nonlinear system identification using multivariate splines Cornelis C. de Visser GENERAL SESSION 1. IAI – Auditorium Chair: Kenzu Abdella 11.00-11.30 11.30-12.00 12.00-12.30 12.30-1.00 1.00-2.00 Flight or Fight - Battle of the Overheads Bins: Another Factor Contributing to the Air Rage Phenomenon Joyce A. Hunter Temperature-dependent explicit stress-strain relations for stainless steel alloys Kenzu Abdella Convergence study of the condition number for some preconditioners to the Stokes problem Omar Ali Aleyan GA Optimization of Point Placement on a Hypersphere Janko Milutinovic, Dragoljub Pokrajac, Sam Kennerly LUNCH BREAK 9 AFTERNOON PLENARY SESSION – LIT - Main Auditorium 2.00-2.50 2.50-3.40 3.40-4.30 4.30-5.00 Keynote Talk: SANDRO DA SILVA FERNANDES Title: Analytical Theory of Optimal Low-Thrust Limited-Power Trajectories Chair: Brian White Keynote Talk: SUNIL L. KUKREJA Title: A Computational Biology Approach to Modelling and Identification of Human Physiology Chair: Antonio Prado Keynote Talk: JOSE MANOEL BALTHAZAR Title: Recent Developments on Regular and Irregular Oscillations and Their Possible Controls in a “Macro”, “MEMS” and “NEMS” Nonlinear Engineering Science Chair: Firdaus E. Udwadia COFFEE BREAK PARALLEL SESSIONS MINISYMPOSIUM 1. Modern Aeroelasticity LIT – Main Auditorium Chair: Justin Jaworski 5.00-5.30 5.30-6.00 6.00-6.30 6.30-7.00 Aeroservoelastic Flight Control Design For Military Aircraft Weapon System Wolfgang Luber Critical and post-critical study of elastic aircraft wings subjected to non-conservative loads S. Ahmad Fazelzadeh, Abbas Mazidi Aeroelastic Aircraft Landing Phase Simulation by Using Hybrid Modeling Approach S.Ahmad Fazelzadeh, Hanif Sadat Hoseini Contributions on smart structures and materials for applications on aeroelasticity and power harvesting Flávio D. Marques, Carlos De Marqui Jr., Volnei Tita MINISYMPOSIUM 3. Spacecraft Attitude Dynamics and Control LIT – Small Auditorium Chair: Luiz Carlos DeSouza 5.00-5.30 5.30-6.00 6.00-6.30 6.30-7.00 Combined Attitude and Solar Tracking (CAST) System for Spacecraft Mohd Faizal Allaudin, Renuganth Varatharajoo Integer ambiguity resolution in attitude determination using GPS measurements Leandro Baroni, Hélio Koiti Kuga Modeling a Reaction Wheel Valdemir Carrara Attitude Synchronization for swarms of Pico-Satellites using Consensus Algorithms Sid Ahmed Attia, Ariel Pratomo 10 SPECIAL SESSION 2. Unmanned Aerial Vehicles LIT – Room 1 Chair: Andras Nagy 5.00-5.30 5.30-6.00 6.00-6.30 6.30-7.00 Determination of Intelligent Control system for a Nonlinear Model of an Autonomous Scale-Model Helicopter by Emotional Learning Approach Abolfazl Mokhtari Non linear filtering technique analysis for Navigation of an UAV Saman Mukhtar Siddiqui, Jiancheng Fang Error Analysis of MEMS sensor data using Allan Variance technique Saman Mukhtar Siddiqui, Fang Jiangcheng Discussion SPECIAL SESSION 10. System identification: Theory and Application in Aerospace, Biology, Engineering and Science IAI – Amphitheatre Chair: Sunil L. Kukreja 5.00-5.30 5.30-6.00 6.00-6.30 6.30-7.00 Frequency response analysis of an aircraft shell panel subject to geometrical imperfections and material properties variations, using a stochastic finite element approach Francisco Scinocca, Airton Nabarrete Use of subjective analysis in flight safety analysis Jozsef Rohacs, Vladimir Alexandrovich Kasaynov CFD assisted analysis of Propeller theories Sathish Krishnan P.S. Discussion SPECIAL SESSION 7. Methods of Nonlinear Analysis for Partial Differential Equations IAI – Auditorium Chair: Eduard-Wilhelm Kirr 5.00-5.30 5.30-6.00 6.00-6.30 6.30-7.00 7.00 PM Stability for fluid structure interaction models with non-linear dissipation at the interface Roberto Triggiani Bifurcations of Nonlinear Bound-States in Schroedinger type equations Eduard-Wilhelm Kirr Elementary Numerical Differential and Integral Methods to Determine the Reaction Rates of Chemical Reactions Christopher Gunaseelan Jesudason Discussion RECEPTION - LIT 11 POSTER SESSION – LIT GEN GEN GEN GEN GEN GEN GEN GEN GEN SS6 SS6 SS6 SS6 SS6 SS6 SS6 SS6 SS6 SS1 On the structural stability of systems of differential equations occurring in aerospace engineering Stefan Balint Size, shape and stability evaluation for meniscus appearing in microfiber growth by pulling down method Agneta Maria Balint, Stefan Balint Model based planning of the capillary and thermal conditions for the growth of a silicon tube with a prior given inner and outer radius Loredana Tanasie, Stefan Balint Introduction to Theory of Physical-Geometry Space Ahmad Sabihi An Approach Towards the Proof of the Strong Goldbach's Conjecture for Sufficiently Large Even Integers Ahmad Sabihi Elementary proof of the Fermat's Last Theorem Artur Korgul, Rafał Andrzej Korgul Fuzzy differential equations Tofigh Allahviranloo Impact Behaviour of Sandwich Plates : Theoretical and experimental investigation Ertan Tengiz, Demet Balkan, Halit Suleyman Turkmen, Zahit Mecitoglu On Thermal Instabilities Occuring in Fires Vasily Novozhilov Homogenization Results for a Wave Equation with Interior and Boundary Damping Claudia Timofte Optimal Transfer Trajectories from Lagrangian Collinear Points Mihai Popescu Computational Methods for Panel Flutter Analysis Florin Frunzulica, Marius Stoia-Djeska, Alexandru Dumitrache Unsteady free-wake vortex particle model for prediction of the aerodynamic loads of HAWT rotor blades Florin Frunzulica, Alexandru Dumitrache, Horia Dumitrescu, Vladimir Cardos Generalized Riccati equations in Banach spaces Viorica Mariela Ungureanu Three-dimensional effects on rotor blade sections in stall Vladimir Cardos, Horia Dumitrescu A numerical algorithm to study the propagation of elastic plastic waves in bars Olga Martin Stability Study of Constrained Systems Ion Stroe Studies for type-II and type-III intermittencies Ezequiel del Rio, Sergio Elaskar, Jose Manuel Doloso Neural Network based Model Predictive Controller for Simplified Heave Model of an Unmanned Helicopter Mahendra Kumar Samal, Sreenatha Anavatti, Matthew Garratt 12 Thursday, July 1 MORNING PLENARY SESSION – LIT - Main Auditorium 8.30-9.20 9.20-10.10 10.10-10.40 Keynote: OTHON C. WINTER Title: On the Dynamics of Triple Asteroid Systems Chair: Harry H. Hilton Keynote Talk: BRIAN WHITE Title: Path Planning and Decision Making for Co-operative Multiple UAVs Chair: Elbert Macau COFFEE BREAK PARALLEL SESSIONS MINISYMPOSIUM 2. Astrodynamics LIT – Main Auditorium Chair: Antonio Prado 10.40-11.10 11.10-11.40 11.40-12.10 12.10-12.40 The close approach between a planet and a cloud of particles Vivian M. Gomes, Antonio F.B.A. Prado Closed Loop Control System Applied to Transfer Maneuvers Using Continuous Thrust Evandro Marconi Rocco, Eliel Wellington Marcelino, Antonio F,B.A. Prado Optimal Low-Thrust Limited-Power Transfers in a Non-central Gravity Field – Transfers Between Arbitrary Orbits Carlos Silveira, Sandro da Silva Fernandes Maneuvers control of a spacecraft through aerodynamics changes under the effects of the upper atmosphere Willer Gomes, Evandro Marconi Rocco, Valdemir Carrara MINISYMPOSIUM 3. Spacecraft Attitude Dynamics and Control LIT – Small Auditorium Chair: Valdemir Carrara 10.40-11.10 11.10-11.40 11.40-12.10 12.10-12.40 12.40-13.10 Fly-by guidance approach for rendezvous and capture of non-cooperating targets Gilberto Arantes Jr., Ananth Komanduri, Daniel Bindel, Luiz de Siqueira MartinsFilho Attitude Control of Spacecraft Using Three Axis Magnetorquer Only Ahmad Faraag, Ahmad Raffie, Ahmad Bahgat Preparation of Uniformly Distributed Onboard Guide Star Catalog Masood Ur Rehman Fine maneuver control for spacecraft simulator by reaction wheels using sliding mode speed controller Mohammad Hossein Beheshti On the modeling of a flexible spacecraft attitude motion considering fuel sloshing Vahid Rezvani 13 SPECIAL SESSION 11. Nuclear Power and Research Systems Modeling LIT – Room 1 Chair: Claubia Pereira 10.40-11.10 11.10-11.40 11.40-12.10 12.10-12.40 Mathematical modelling of a system for brachytherapy Wagner Leite Araujo, Tarcisio Passos Ribeiro Campos Comparative study of the neutron production by spallation and fusion reactions for subcritical hybrid systems applications Graiciany P Barros, Claubia Pereira, Maria Auxiliadora Fortini Veloso, Antonella Lombardi Costa, Patrícia A. L. Reis Comparation between WIMSD-5B and MCNPX 2.6.0 codes simulating a PWR fuel element Clarysson A. Mello da Silva, Claubia Pereira, Maria Auxiliadora Fortini Veloso, Antonella Lombardi Costa Evaluation of spallation source for neutrons production by Monte Carlo methods Maurico Gilberti, Claubia Pereira, Maria Auxiliadora Fortini Veloso, Antonella Lombardi Costa, Clarysson A. Mello da Silva SPECIAL SESSION 9. Petri nets for complex systems IAI – Amphitheatre Chair: Joslaine Cristina Jeske de Freitas 10.40-11.10 11.10-11.40 11.40-12.10 12.10-12.40 Simulation of Industrial Metabolism using Predicate Transition Petri Nets combined with Differential Equations Liliane Nascimento Vale, Stéphane Julia, Núbia Rosa Silva, Márcio Souza Dias Distributed modelling and simulation of complex systems using Petri net Fabrício Junqueira, Cristiano da Silva Costa, Diolino José dos Santos Filho, Paulo Eigi Miyagi Control Algorithms Partition Method for Distributed Control Systems Diolino Jose dos Santos Filho, Andre Cesar Martins Cavalheiro A Hybrid Method to Generate Control Algorithms for Complex Systems Francisco Yastami Nakamoto, Diolino José dos Santos Filho, Fabrício Junqueira, Paulo Eigi Miyagi GENERAL SESSION 2. IAI – Auditorium Chair: Vanessa Avelino Xavier de Camargo 10.40-11.10 11.10-11.40 11.40-12.10 12.10-12.40 12.40-2.20 Evolutionary Programming with Adaptative Stable Distributions Leopoldo Bulgarelli Carvalho Semi active suspension control techniques using only one measurement sensor Fábio Luis Marques dos Santos, Luiz Carlos Sandoval Goes, Alberto Luiz Serpa Designing Phase-Locked Loops for Frequency Modulation Atomic Force Microscope Atila Madureira Bueno, José Manoel Balthazar, José Roberto Castilho Piqueira Improvement in Relational Databases Query Using Fuzzy Logic Vanessa Avelino Xavier de Camargo, Wemerson Leonardo Ramos, Esdras Teixeira Costa, Marcos Wagner Souza Ribeiro LUNCH BREAK 14 1.10-2.10 Wolfram Research Tutorial: An Overview of Mathematica for Education Igor Canales Antonio AFTERNOON PLENARY SESSION – LIT - Main Auditorium 2.20-3.10 3.10-4.00 Keynote Talk: SILVIA MARIA GIULIATTI WINTER Title: New Horizons Mission and the Pluto-Charon System Chair: Roberto Triggiani Keynote Talk: IRENA LASIECKA Title: Well-posedness and long time behavior of finite energy solutions corresponding to 3-d flows interacting with dynamic elasticity Chair: Toshiya Nakamura 4.00-4.30 COFFEE BREAK PARALLEL SESSIONS MINISYMPOSIUM 2. Astrodynamics LIT – Main Auditorium Chair: Vivian M. Gomes 4.30-5.00 5.00-5.30 5.30-6.00 6.00-6.30 6.30-7.00 Innovative Dynamical Analysis of the Algorithmic Weak Stability Boundary Maisa de Oliveira Terra, Priscilla Andressa de Sousa Silva Escape Basins and Chaotic Saddles in the Planar Circular Restricted Three-Body Problem for the Earth-Moon System Sheila Crisley de Assis,, Maisa de Oliveira Terra Gravitational Capture under the Restricted Three-Body Problem Alexandre Lacerda Machuy Francisco, Antonio F.B.A. Prado, Teresinha de Jesus Stuchi Using extended Kalman filter and least squares method for spacecraft attitude estimation. Roberta Veloso Garcia, Helio Koiti Kuga, M.C. Zanardi A comparison of gravity-assisted maneuvers in different planets to optimize interplanetary missions Flaviane Venditti, Evandro Marconi Rocco, Antonio F.B.A. Prado, Alexander A. Sukhanov 15 SPECIAL SESSION 12. Integral Equations and their Applications LIT – Small Auditorium Chair: Luis Castro 4.30-5.00 5.00-5.30 5.30-6.00 6.00-6.30 6.30-7.00 Stability of Fredholm integral equations in the framework of generalized metric spaces Luis Castro Constructions of the approximate solutions of singular integral equations by using the Tikhonov regularization and the theory of reproducing kernels Saburou Saitoh Integral equations of Wiener-Hopf type characterized by piecewise almost periodic elements in Lebesgue spaces with weights Anabela Silva Splitting property for singular integral operators with a weighted shift Edixon Rojas Fredholm-Stieltjes integral equations with (O-M)integral in time scales and applications Luciano Barbanti, Berenice Camargo Damasceno, Jose Manoel Balthazar SPECIAL SESSION 11. Nuclear Power and Research Systems Modeling LIT – Room 1 Chair: Antonella Lombardi Costa 4.30-5.00 5.00-5.30 5.30-6.00 6.00-6.30 6.30-7.00 Initial Development of a Coupling Methodology between Thermal-Hydraulic and Neutron Kinetic Codes for Simulation of the IPR-R1 TRIGA Reactor Claubia Pereira, Patrícia A. Lima Reis, Antonella Lombardi Costa, Maria Auxiliadora Fortini Veloso, Clarysson A Mello da Silva Design of a deuteron accelerator for a portable neutron generator Wagner Leite Araujo, Tarcisio Passos Ribeiro Campos GB - a linking code between MCNP and ORIGEN2.1 - DEN/UFMG version Renan Cunha, Claubia Pereira, Daniel Campolina, André Cavatoni, Maria Auxiliadora Fortini Veloso Application of Nuclear Codes WIMSD-5B and MCNPX 2.6.0 to a Qualitative Evaluation of MHR (MODULAR HELIUM REACTOR) Clarysson A. Mello da Silva, Claubia Pereira, Maria Auxiliadora Fortini Veloso, Antonella Lombardi Costa A preliminary neutronic evaluation and depletion study of HTR using WIMSD5 and MCNPX2.6.0 codes Fabiano Cardoso Silva, Claubia Pereira, Clarysson A. Mello da Silva, Maria Auxiliadora Fortini Veloso, Antonella Lombardi Costa 16 SPECIAL SESSION 9. Petri nets for complex systems IAI – Amphitheatre Chair: Diolino Jose dos Santos Filho 4.30-5.00 5.00-5.30 5.30-6.00 6.00-6.30 6.30-7.00 A model to represent human behavior in workflow management systems. Joslaine Cristina Jeske de Freitas, Stephane Julia, Robert Valette Safety Instrumented Systems Design Based on Bayesian network and Petri net Reinaldo Squillante Junior, Diolino Jose dos Santos Filho, Jose Isidro Garcia Melo, Fabricio Junqueira, Paulo Eigi Miyagi Intelligent Building – Modeling and Reconfiguration using Petri Net and Holons Julio Arakaki, Diolino Jose dos Santos Filho, Fabricio Junqueira, Paulo Eigi Miyagi Scheduling Heuristic based on Time Windows for Service-oriented Architecture Marcosiris Amorim de Oliveira Pessoa, Diolino Jose dos Santos Filho, Jose Isidro Garcia Melo, Fabricio Junqueira, Paulo Eigi Miyagi Collaborative Control Model for Multifunctional Machine Tools Environment Osvaldo Luis Asato, Diolino Jose dos Santos Filho, Fabricio Junqueira, Paulo Eigi Miyagi SPECIAL SESSION 3. Advances in Nonlinear Differential Equations IAI – Auditorium Chair: Anjan Biswas 4.30-5.00 5.00-5.30 5.30-6.00 6.00-6.30 6.30-7.00 Optical solitons with higher order dispersion Anjan Biswas Wavelet transforms and its connection to established theories and Image processing Bharat Namdeo Bhosale Solutions of Kadomtsev-Petviashvili equation with power law nonlinearity in 3+1 dimensions Chaudry Masood Khalique The Combined Effect of the Linear and Nonlinear Couplings on the Phase and Velocity Shifts of Interacting Solitons in Coupled Nonlinear Schrodinger Equations Michail D Todorov Generalized Radon transform and Microlocal analysis Guoping Zhang, Fengshan Liu 17 POSTER SESSION – LIT M4 M4 M4 M4 M4 M4 M4 M4 M4 M4 M4 M4 SS8 SS8 SS8 SS8 SS8 SS4 SS4 A Comparision of PO Approximations with FDA Method to Obtain RCS of Simple Shapes Ahmad Sabihi, Mohammad Ali Vaziry Z. Smart beam deflection behavior due to two or more SMA wires attachment Hamid Salehi, Saeed Zeiaei Rad, Mohammad Reza Zakerzadeh, Mohammad Ali Vaziry Zanjani On the Laser Cross Section of Various Targets Ahmad Sabihi, Mohammad Ali Vaziry Z. On the Electromagnetic Waves and Propagation in Relativity-Quantum Space Ahmad Sabihi Solving the Sitnikov Equation by Means of the Fourier Expansion Mojtaba Dehghan Manshadi, Mohammad Farahani, Mohammad Ali Vaziry On the Modification of Node Swapping Method in graph partitioning Omid Talebi, Ahmad Sabihi, Pejman Khadivi A Non-Model Based Damage Detection Technique Using Dynamically Measured Flexibility Matrix Mehdi Salehi, Saeed Ziaei-Rad, Mostafa Ghayour, Mohammad Ali Vaziri-Zanjani Design and Simulation of Intelligent Aircraft Longitudinal Autopilots Using Particle Swarm Optimization Algorithms Mostafa Lotfi Forushani, Bahram Karimi, Ghazanfar Shahgholian, Alireza Karami Horestani Robust SDC Parameterization for a Class of Extended Linearization Systems Sam Nazari, Bahram Shafai Pseudo-stochastic-chaotic systems in Engineering Applications Hilda Angela Larrondo, Luciana De Micco Finite volume simulation of supersonic flows Sergio Elaskar, José Tamagno Finite volume solution of compressible magnetohydrodynamics equations Sergio Elaskar, Livio Maglione, Mariano Martinez Fractional differential equations with piecewise constant argument deviations William Edmond Dimbour Pseudo almost periodic and pseudo almost automorphic functions and their applications to fractional differential equations Ti-Jun Xiao New results on fractional differential and integrodifferential equations in Banach spaces Jin Liang Optimal control of a class of fractional diffusion equation Gisele Mophou Existence and uniqueness of mild solution for fractional integro-differential equations Gaston Mandata N’Guérékata, Fang Li Ultimate boundedness of solutions of non-homogeneous vector differential equation of the third-order Mathew Omonigho Omeike New stability and boundedness results of solutions of nonlinear differential equations of second and third order with variable delay Cemil Tunc 18 Friday, July 2 MORNING PLENARY SESSION – LIT - Main Auditorium 8.30-9.20 9.20-10.10 10.10-10.40 Keynote Talk: TOSHIYA NAKAMURA Title: JAXA's Aeronautical Research Project for Civil Transport - Endeavours to Enhance Safety and Environmental Friendliness Chair: S.N. Balakrishnan Keynote Talk: FIRDAUS E. UDWADIA Title: Advances in the Modeling and Control of Complex Multibody Systems Chair: Naira Hovakimyan COFFEE BREAK PARALLEL SESSIONS MINISYMPOSIUM 2. Astrodynamics LIT – Main Auditorium Chair: Evandro Marconi Rocco 10.40-11.10 11.10-11.40 11.40-12.10 12.10-12.40 The FEFF Methodology for Proximity Maneuvering Spacecraft Formations Laura Garcia-Taberner, Josep J. Masdemont Precise predicted extended ephemeris solution for GPS Rajendra P. Prasad, Hélio Koiti Kuga, Nagaraj Dixit Internal loading distribution in a statically loaded ball Mário César Ricci Evaluation of the Fuel Consumption in Orbital Maneuvers with Time and Position Constraints Thais Carneiro Oliveira, Evandro Marconi Rocco, Antonio F.B.A. Prado SPECIAL SESSION 6. Mathematical Research In Dynamical Systems Theory LIT – Small Auditorium Chair: Maisa de Oliveira Terra 10.40-11.10 11.10-11.40 11.40-12.10 12.10-12.40 Risk-Sensitive Second Grade Optimal Filtering Design Maria Aracelia Alcorta-Garcia, Hector Flores Cantu, Sonia Guadalupe AnguianoRostro Biparametric investigation of the general standard map: multistability and crises Priscilla Andressa de Sousa Silva, Maisa de Oliveira Terra Non-linear Inverse Dynamics Control of the Smart Column with Support Excitation S. Ahmad Fazelzadeh, E. Azadi, M. Azadi Risk-Sensitive Third Grade Optimal Filtering Design Maria Aracelia Alcorta-Garcia, Hector Raymundo Flores-Cantu, Mauricio Torres Torres 19 SPECIAL SESSION 1. Neural Network Dynamics LIT – Room 1 Chair: Seenith Sivasundaram 10.40-11.10 11.10-11.40 11.40-12.10 12.10-12.40 Bifurcation Networks: An Approach to Cortical Modeling and Higher Level Brain Function Nabil H. Farhat Bumps in a two population neural field model John Wyller Controlling the chaotic dynamics of neural networks Francisco Welington Lima, Tarik Hadzibeganovic Almost Periodic Solutions of Impulsive Hopfield Neural Networks with Periodic Delays Haydar Akca, Valery Covachev, Zlatinka Covacheva MINISYMPOSIUM 4. Mathematical Applications in Electrical, Aerospace and Control Engineering IAI – Amphitheatre Chair: , Leonardo D. Chiwiacowsky 10.40-11.10 11.10-11.40 11.40-12.10 12.10-12.40 An Hierarchical Approach for the Structural Damage Identification Leonardo B. L. Santos, Leonardo D. Chiwiacowsky, Haroldo F. Campos Velho On the Active Vibration Control and Stability of the Tubular Structures by Piezoelectric Patch-Like Actuators Sergey N. Shevtsov, Michail B. Flek, Vladimir A. Acopyan, Vladimir N. Axenov Passive Thermal Control with Pulsating Heat Pipe Liomar de Oliveira Cachuté, Roger Ribeiro Riehl On an Optimal Linear Control Design Applied to a Non-Ideal and Ideal Structure controlled through MR Damper Angelo Marcelo Tusset, Fábio Roberto Chavarette, Jorge L. P. Felix, José Manoel Balthazar MINISYMPOSIUM 5. Multidisciplinary Design and Optimization in Aerospace Industry IAI – Auditorium Chair: Amer Farhan Rafique 10.40-11.10 11.10-11.40 11.40-12.10 12.10-12.40 12.40-2.20 Implementation, Validation and Testing of an Inverse Design Tool for Redesigning NACA 65-410 Wing Profile Árpád Veress, András Nagy, József Rohács Sensitivity analysis of an aircraft shell panel with geometry imperfections Airton Nabarrete, Francisco Scinocca Trajectory Optimization of Air Launched Satellite Launch Vehicle using Genetic Algorithm Amer Farhan Rafique Design and Optimization of Slotted Tube Grain Configuration using Simulated Annealing Ali Kamran, Liang Guozhu LUNCH BREAK 20 AFTERNOON PLENARY SESSION – LIT - Main Auditorium 2.20-3.10 3.10-4.00 4.00-4.30 Keynote Talk: STANISLAV VASSILYEV Title: Analysis of dynamics of hybrid systems with nonlinear vector fields by homomorphic mappings Chair: Firdaus E. Udwadia Keynote Talk: ELBERT MACAU Title: Controlling Chaotic Transient and the Improvement of System Flexibility Chair: Irena Lasiecka COFFEE BREAK PARALLEL SESSIONS MINISYMPOSIUM 2. Astrodynamics LIT – Main Auditorium Chair: Helio Koiti Kuga 4.30-5.00 5.00-5.30 5.30-6.00 Analysis of disturbing effects in the dynamical model of orbit determination using GPS Paula C.P.M. Pardal, Rodolpho Vilhena de Moraes, Helio Koiti Kuga Artificial Satellites: Orbital Perturbations Rodolpho Vilhena de Moraes Optimization of Low-Thrust Spiral Transfers between Two Given Orbits Alexander A. Sukhanov SPECIAL SESSION 4. Stability and Lyapunov Theory SPECIAL SESSION 8. Advances in Fractional Differential Equations LIT – Small Auditorium Chair: Olufemi Adeyinka Adesina 4.30-5.00 5.00-5.30 5.30-6.00 Some remarks on the exponential stability and periodicity of solutions for certain delayed differential equations of fourth order Olufemi Adeyinka Adesina Pseudo-almost automorphic solutions to a class of semilinear fractional equations Marcos Rabelo Numerical analysis for singularly perturbed delay differential equations Fevzi Erdogan 21 SPECIAL SESSION 1. Neural Network Dynamics LIT – Room 1 Chair: Haydar Akca 4.30-5.00 5.00-5.30 5.30-6.00 Multistability in impulsive Hopfield neural networks with time-dependent and distributed delays Eva Kaslik, Seenith Sivasundaram Artificial neural networks applied to low cost INS/GPS integrated navigation systems Edmundo Alberto Marques Filho, Atair Rios Neto, Helio Koiti Kuga Stability and Bifurcation Analysis Of Three Neuron Delayed Network Model Of Hopfield Type Narayan Chandra Majee, Amiya Bhusan Roy MINISYMPOSIUM 4. Mathematical Applications in Electrical, Aerospace and Control Engineering IAI – Amphitheatre Chair: Ilse Camacho Cervantes 4.30-5.00 5.00-5.30 5.30-6.00 Spacecraft Trajectory Optimization Using State Parameterization and Interval Analysis Elwin de Weerdt, Q.P. Chu, J.A. Mulder Hybrid Tracking Control of Fixed Wing Aerial Vehicles Ilse Camacho Cervantes, Fany Mendez Vergara A Micro-Tuning-Fork Gyroscope Coupling with an Electrodynamic Engine Ana Rosa Klinke, J.M. Balthazar, Luiz Palacios Felix, F.R. Chavarete MINISYMPOSIUM 5. Multidisciplinary Design and Optimization in Aerospace Industry IAI – Auditorium Chair: Amer Farhan Rafique 4.30-5.00 5.00-5.30 5.30-6.00 8.00 PM Optimization of an Aeronautical Composite Structure through a Parallel Multilevel Approach Leonardo Dagnino Chiwiacowsky, Paolo Gasbarri, Haroldo Fraga de Campos Velho, Arthur Tórgo Gómez New heuristic approach for the multiobjective nonidentical circle packing problem José Carlos Becceneri Information Entropy as a Tool for Innovation Projects Fuzzy Front End Decision Luis Wwaack Bambace BANQUET – Churrascaria Vila D'Aldeia http://www.villadaldeia.com.br/ 22 POSTER SESSION – LIT M5 M5 M5 M5 M5 M5 M5 M5 M5 Optimal PID Controller Tuning in Missile Design Based on PSO Algorithm Alireza Karami Horestani, Mostafa Lotfi Forushani, Mohamad Hoseinyar Comparison Study of Geometrically and Numerically Regression of the Star Grain Design for SRM Soe Hlaing Tun, Xiang Hong Jun Experimental Study of Laminar Horseshoe Vortex Using PIV Zaw Zaw Oo, Muhammad Yamin, Hua Zhang Efficient Shock Capturing Scheme for Transonic Aerodynamics Hasan Junaid Hasham Review of Reduced Order Models for CFDCSD Interaction Problems Hasan Junaid Hasham Study on Random Initial Point Trajectory Planning for Missile Borne Unmanned Air Vehicle Wang Wei, Wang Hua, He LinShu Integrated Multidisciplinary Design and Multi-Objective Optimization Approach for Space Launch Vehicle Naeem Zafar, He LinShu Constraint Handling Approach using Multi-Objective Evolutionary Optimization Naeem Zafar, He LinShu Parametric Design Approach for Aero-performance of Hypersonic Reentry Body Muhammad Amjad Sohail, Yan Chao, Zahid Maqbool M5 Inviscid and Viscous Computation on Aerodynamic Characteristics of a Conventional Projectile with and without Fins Configuration by using Flux Difference Scheme Muhammad Amjad Sohail, Yan Chao, Zahid Maqbool, M. Yamin Younis, Muhammad Afzal, Mukkarum Hussain M5 Application of Sensitivity Region Based Robust Design Approach in MDO of Flight Vehicle Ma Ying, He LinShu Effectiveness optimization for a surface-to-air missile system based on MDO Jiang Huan, Chen Wanchun Optimization of Free-Flying Time between Two Joined Stages for Solid-Fuel Ballistic Missile Htoo Hlaing Win, Linshu He Steady State Problems in Financial Option Pricing Dejun Xie A Fuzzy Neural Network for Emitter Identification Mohamad Hoseinyar, Mostafa Lotfi Forushani FPGA Implementation of LMS-Based System Identification Core Omid Sharifi Tehrani, Ebrahim Hosseini, Mohsen Ashourian Damping identification in a non-linear aeroelastic structure Gareth A. Vio Numerical Analysis of Aerodynamic Performance of a Aircraft Wing With Simulated Glaze Ice Accretion Aung Ko Wynn, Cao Yi Hua, Ma Cao Physical Programming based Multidisciplinary Optimization for 2D Turbine Airfoil Zhang Nannan M5 M5 SS10 SS10 SS10 SS10 SS5 SS5 23 Saturday, July 3 MORNING PLENARY SESSION – LIT - Main Auditorium 8.30-9.20 9.20-10.10 10.10-11.00 Keynote Talk: Robert M.M. Matheijj Title: Flow in networks Chair: S. Sivasundaram Keynote Talk: NAIRA HOVAKIMYAN Title: The Theory of Fast and Robust Adaptation Chair: Antonio Prado Keynote Talk: S.N. BALAKRISHNAN Title: Approximate Dynamic Programming Based Control for Aircraft and Space Vehicles in the Presence of Uncertainties Chair: Brian White MINISYMPOSIUM 1. Modern Aeroelasticity LIT – Small Auditorium Chair: Oddvar Bendiksen 9.00-9.30 9.30-10.00 10.00-10.30 10.30-11.00 11.00-11.30 Limit Cycle Oscillations of Very Flexible High-Aspect-Ratio Wings Justin W. Jaworski, Earl H. Dowell Dynamic Instability of Viscoelastic Plate in Supersonic Flow Botir Usmonov Reconstruction of Aerodynamic Loads Based on Inverse Analysis Toshiya Nakamura, Hirotaka Igawa Bending without normal stress case on an isotropic micropolar beam Juan Alejandro Vazquez Feijoo COFFEE BREAK PARALLEL SESSIONS MINISYMPOSIUM 1. Modern Aeroelasticity LIT – Main Auditorium Chair: Wolfgang Luber 11.30-12.00 12.00-12.30 12.30-1.00 Application of Correction Methods for Aeroelastic Stability Analysis of Wing Structures in Transonic Flow Roberto Gil Annes da Silva Ricardo Franco Amaral The influence of starting transients, aerodynamic definition and boundary conditions on elastic and viscoelastic panel and wing flutter Craig G. Merrett, Harry H. Hilton Research on Aileron Buzz Controling by Changing Boundary Layer Thickness Masato Tamayama 24 1.00-1.30 1.30-2.00 Dynamic responses and eigenanalysis of non-classical vibrating beams Julio R. Claeyssen , Teresa Tsukazan, Rosemaira D. Copetti, Antonio L. Bidel A bifurcation based approach to the analysis and control of flexible aircraft Mohamed Nadjib Baghdadi SPECIAL SESSION 5. Contributions of PhD students (and post-doctoral researchers) LIT – Small Auditorium Chair: Anne Caroline Bronzi 11.30-12.00 12.00-12.30 12.30-1.00 1.00-1.30 1.30-2.00 2.00-2.30 Axi-symmetric, Darcy-Brinkman-Forchheimer flow through an annulus Pradeep Ganapathi Siddheshwar, Ashoka Basavaraje Gowda Sangarashettahally Heat transfer in a Darcy-Forcheimmer-Brinkman flow through a curved channel Mahesha Narayana, Vishwanath Kadaba Puttanna, Pradeep Ganapathi Siddheshwar Weak solutions of the incompressible ideal flow equations Anne Caroline Bronzi Superposition of a pulsating and oscillating flow of a complex structural liquid Edtson Emilio Herrera-Valencia Differential Transform Method of Solution for Non-Linear Boundary Value Problem: An Illustration Madhavanpillai Sumathykuttyamma Jagadeesh Kumar, Suresh G Singh, Pradeep Ganapathi Siddheshwar A Lane-Emden-Fowler type problem Dragos-Patru Covei GENERAL SESSION 3. LIT – Room 1 Chair: Luis Waack Bambace 11.30-12.00 12.00-12.30 12.30-1.00 1.00-1.30 1.30-2.00 Diversity QPSK-CDMA schemes for LEO mobile communication Luis Waack Bambace A new real inversion formula for the Sumudu Transform Fethi Bin Muhammad Belgacem Dynamic simulation of light space structures by finite element modeling and order reduction in state space Leandro Gonzalez, Eduardo N Zapico Nonlinear Analysis of Cables and Guyed Towers Shahin Nayyeri Amiri 6-DOF data and aerodynamic models for real-time flight simulation Pedro S. Giraudo, Javier E. Luiso, Eduardo N. Zapico, Horacio A. Abbate 25 MINISYMPOSIUM 4. Mathematical Applications in Electrical, Aerospace and Control Engineering IAI – Amphitheatre Chair: ,Ismail Hameduddin 11.30-12.00 12.00-12.30 12.30-1.00 1.00-1.30 On the Nonlinear Dynamics and Control of Modal Interactions Resulting from the Longitudinal and Lateral Flight of an Aircraft Rodrigo Bassinello Ramazotti Aircraft Generalized Dynamic Inversion Control Abdulrahman Hasan Bajodah, Ismail Hameduddin Position and Vibration Control of a Nonlinear Slewing Flexible Structure Considering Fluid-Structure Interaction André Fenili, Cayo Prado Fernandes Francisco Semi-Lagrangian Reachability Analysis for Aircraft Safe Flight Envelope Determination Eddy van Oort MINISYMPOSIUM 5. Multidisciplinary Design and Optimization in Aerospace Industry IAI – Auditorium Chair: Amer Farhan Rafique 11.30-12.00 12.00-12.30 12.30-1.00 1.00-1.30 Design and Optimization of Star Grain Configuration using Simulated Annealing Ali Kamran, Khurram Nisar, Amer Farhan Rafique, Qasim Zeeshan Development of a new algorithm for optimization of closed-loop liquid rocket engines Davood Ramesh Robust Design Optimization of Booster Phase Energy Management of Dual Thrust Propulsion System Muhammad Aamir Raza Nonlinear Stability and Optimization Techniques Arthur Cave END OF CONFERENCE 26 ABSTRACTS TABLE OF CONTENTS KEYNOTE TALKS 2 GENERAL SESSION 7 SPECIAL SESSION 1. Neural Network Dynamics 14 SPECIAL SESSION 2. Unmanned Aerial Vehicles 16 SPECIAL SESSION 3. Advances in Nonlinear Differential Equations 19 SPECIAL SESSION 4. Stability and Lyapunov Theory 21 SPECIAL SESSION 5. Contributions of PhD Students (and Post-Doctoral Researchers) 23 SPECIAL SESSION 6. Mathematical Research in Dynamical Systems Theory 25 SPECIAL SESSION 7. Methods of Nonlinear Analysis for Partial Differential Equations 29 SPECIAL SESSION 8. Advances in Fractional Differential Equations 30 SPECIAL SESSION 9. Petri Nets for Complex Systems 31 SPECIAL SESSION 10. Engineering and Science 34 System Identification: Theory and Application in Aerospace, Biology, SPECIAL SESSION 11. Nuclear Power and Research Systems Modeling 38 SPECIAL SESSION 12. Integral Equations and Their Applications 41 MINISYMPOSIUM 1. Aeroelasticty 43 MINISYMPOSIUM 2. Astrodynamics 49 MINISYMPOSIUM 3. Spacecraft Attitude Dynamics and Control 55 MINISYMPOSIUM 4. Mathematical Applications in Electrical, Aerospace and Control Engineering 60 MINISYMPOSIUM 5. Multidisciplinary Design and Optimization in Aerospace Industry 67 Author Index 74 27 KEYNOTE TALKS A.V. BALAKRISHNAN, UCLA, United States Title: Flutter Analysis in Viscous Flow The problem of Flutter - an inherent destructive instability of aircraft in subsonic flow which mandates the maximum speed at any altitude by the Federal Aviation Administration to be within 15% of the Flutter Boundary-continues to be of interest even as we consider unmanned aircraft. Much is understood about Flutter phenomena in nonviscous airflow but the extension to viscous flow is still open - and the only known technique involves the Prandtl Boundary Layer theory, still not proven mathematically. S.N. BALAKRISHNAN, Missouri University of Science and Technology, USA Title: Approximate Dynamic Programming Based Control for Aircraft and Space Vehicles in the Presence of Uncertainties Approximate dynamic programming formulation implemented with an Adaptive Critic (AC) based neural network (NN) structure has evolved as a powerful alternative technique that eliminates the need for excessive computations and storage requirements needed for solving the Hamilton-Jacobi-Bellman (HJB) equations. A typical AC structure consists of two interacting NNs. In this paper, a novel architecture, called the Single Network Adaptive Critic (SNAC) is used to solve control-constrained optimal control problems. Only one network is used that captures the mapping between states and the cost function. This approach is applicable to a wide class of nonlinear systems where the optimal control (stationary) equation can be explicitly expressed in terms of the state and costate variables. A non-quadratic cost function is used that incorporates the control constraints. Necessary equations for optimal control are derived and an algorithm to solve the constrained-control problem with SNAC is developed. Convergence of the network training is discussed. Benchmark nonlinear systems are used to illustrate the working of the proposed technique. Extensions to optimal control-constrained problems in the presence of uncertainties are also considered. Two aerospace tracking applications – an aircraft and a space vehicle with model and parametric uncertainties will be shown. José Manoel BALTHAZAR, UNESP, Brazil Title: Recent Developments on Regular and Irregular Oscillations and Their Possible Controls in a Macro, MEMS and NEMS Nonlinear Engineering Science The study of the vibrating systems when the external excitation it is influenced by the response of the system, has been considered a major challenge in theoretical and practical engineering research. When motors are attached to structures that need excitation power levels similar to the power capacity of those motors, interesting non-linear phenomena may happen, such as: Modal saturation-energy transfer between modes and Sommeferld effect. On one hand, it is also well know that those Micro-electromechanical systems (MEMS) are one of the new and modern challenges in the engineering sciences field, owing to its interdisciplinary nature of research and extremely small feature size, which are now produced cheaply and in very small packages, in the micro domain. The research is going on, by using macro model as a possible outlook in this area. We mention the study of the characteristics of the parameters need to be studied in more detail to guarantee the reliability of the (MEMS). On the other hand, the atomic force microscope (AFM) system has become a useful instrument to measure the intermolecular forces, with atomic-resolution, since its discovery in 1986. The nonlinear dynamic (AFM), consists itself of a vibrating micro cantilever, with a nanoscale tip, which interacts with a sample surface via short- and long-range intermolecular forces. Amplitude-modulation (AFM) involves amplitude oscillations between 1 and 100 nm. It is known that, micro cantilevers possess several distinct eigenmodes and the tipsample interaction forces are Highly nonlinear. The adopted cantilever-sample mode interaction was mathematically modeled as a number of single spring-mass (mass: being the tip of the cantilever). The cantilever interacts with the sample via a tip, which is mounted on the cantilever. 28 Sandro DA SILVA FERNANDES , Instituto Tecnológico de Aeronáutica - ITA, Brazil Title: Analytical Theory of Optimal Of Low-Thrust Limited-Power Trajectories In this work, an analytical theory of optimal low-thrust limited-power trajectories is presented. This theory is based on properties of generalized canonical systems, Lie-Hori canonical perturbation method and Hamilton-Jacobi canonical transformation theory. The optimization problem associated to the general space transfer problem is formulated as a Mayer problem of optimal control theory with Cartesian elements - position and velocity vectors - as state variables. After applying the Pontryagin Maximum Principle and determining the maximum Hamiltonian, classical orbital elements are introduced through a canonical transformation derived from the properties of generalized canonical systems. Short periodic terms are then eliminated from the maximum Hamiltonian function through an infinitesimal canonical transformation built by applying Lie-Hori canonical perturbation method. The new Hamiltonian function, resulting from the infinitesimal canonical transformation, describes the extremal trajectories associated with the long duration maneuvers for simple transfers (no rendez-vous). This new Hamiltonian function can be simplified for four special classes of maneuvers: transfers between elliptical coplanar orbits, transfers between elliptical non-coplanar coaxial orbits, transfers between elliptical non-coplanar coparameters orbits and transfers between orbits with very small eccentricities, and, closed-form analytical solutions can be obtained through Hamilton-Jacobi theory. Using Lie-Hori algorithm, first order approximated analytical solutions, which include short periodic terms, are obtained for these particular problems. Silvia GIULIATTI WINTER, Orbital Dynamics & Planetology Group - UNESP, Brazil Title: New Horizons Mission and the Pluto-Charon system Two new companions to the Pluto-Charon binary system, Nix and Hydra, have been detected in 2005 by Weaver et al., 2006 beyond Charon’s orbit. Although they are small when compared to Charon, their gravitational perturbations can decrease the stability of the external region of this binary system. In this work we present the results of a sample of numerical simulation concerning particles in P and S-type orbits under the gravitational perturbations of the four massive bodies: Pluto-Charon-Nix-Hydra. For those particles in S-type orbits around Pluto and Charon we found several stable regions whose the families of the periodic orbits have been identified through an analysis of the Poincaré surface of sections. Different values of the eccentricity and inclination of the particles have been investigated. The size of the stable regions reachs its minimum for those particles with initial inclination equals to 110◦ , and its maximum for an inclination equals to 180◦ . Through a sample of numerical simulations we have also determined the size and locaton of a sample of hypothetical satellites which could lie in the external region of the Pluto-Charon binary system. Naira HOVAKIMYAN , University of Illinois at Urbana-Champaign, USA Title: The Theory of Fast and Robust Adaptation The history of adaptive control systems dates back to early 50-s, when the aeronautical community was struggling to advance aircraft speeds to higher Mach numbers. In November of 1967, X-15 launched on what was planned to be a routine research flight to evaluate a boost guidance system, but it went into a spin and eventually broke up at 65,000 feet, killing the pilot Michael Adams. It was later found that the onboard adaptive control system was to be blamed for this incident. Exactly thirty years later, fueled by advances in the theory of nonlinear control, Air Force successfully flight tested the unmanned unstable tailless X-36 aircraft with an onboard adaptive flight control system. This was a landmark achievement that dispelled some of the misgivings that had arisen from the X-15 crash in 1967. Since then, numerous flight tests of Joint Direct Attack Munitions (JDAM) weapon retrofitted with adaptive element have met with great success and have proven the benefits of the adaptation in the presence of component failures and aerodynamic uncertainties. However, the major challenge related to stability/robustness assessment of adaptive systems is still being resolved based on testing the closed-loop system for all possible variations of uncertainties in Monte Carlo simulations, the cost of which increases with the growing complexity of the systems. This talk will give an overview of the limitations inherent to the conventional adaptive controllers and will introduce a new paradigm for design of adaptive control systems that leads to fast and robust adaptation with provable control specifications and guaranteed stability/robustness margins. Various applications will be discussed during the presentation to demonstrate the tools and the concepts. 29 Sunil L. KUKREJA, NASA Dryden Flight Research Center, Edwards, California, USA Title: A Computational Biology Approach to Modelling and Identification of Human Physiology We demonstrate the practical application of methods developed for identification of linear, nonlinear and hybrid (multimode) systems to human physiology. Although these tools were developed with biological applications in mind, they are generalizable to a large set of problems that span many disciplines. After an introduction to the system identification problem and model class considered in our work, we demonstrate the usefulness of a computational biology approach to the study of human biology. Two specific topics are highlighted, the modeling and identification of the human (i) neuromuscular and (ii) vestibular ocular reflex system. These topics are of importance to NASA’s Digital Astronaut Project for long term human space exploration. Results demonstrate that a computational biology approach to predicting the effects of spaceflight on the human body may allow for characterization of disease, early detection and quantification of ocular disease and balance disorder and better design of robotic motor control systems. Irena LASIECKA, University of Virginia, USA Title: Well-posedness and long time behavior of finite energy solutions corresponding to 3-D flows interacting with dynamic elasticity We shall discuss finte energy solutions corresponding to 3-D flows (gas or fluid) interacting on an interface with dynamic nonlinear elasticity. Specific examples include : fluid structure interactions (Navier Stokes equation coupled with wave equation), structural acoustic interaction (wave equation coupled with nonlinear dynamic plate or shell equation), flow-gas interaction (linearised Euler equation interacting with a nonlinear dynamic plate). The interaction in these models takes place on a manifold of lower dimension. Of particular interest to this talk are evolutions with ”supercritical” (with respect to Sobolev’s embeddings) nonlinearities. These include supercritical semilinear wave equations, von Karman evolutions, Kirchhoff Bousinesq equations and other non-linear plate equations. This class of models, while motivated by a multitude of physical applications, does not seem to have well established mathematical methodology for dealing with the issues such as existence, uniqueness and stability (including long time behavior) of solutions posed in physically significant finite energy space. The issue at hand is a well recognized dychotomy between global existence and uniqueness. Existence for weak (finite energy) solutions is known, while uniqueness holds for strong solutions that are defined only locally. In this talk we shall single out several classes of models for which rather general techniques have been recently developed. (see Ref. [1-4] and references therein). These techniques lead -ultimately- to the resolution of the dychotomy and also provide a treatment for the study of long time behavior (global attractors) for the resulting dynamics. The results presented will supply positive answers to several open questions raised in the context of ”supercritical” dynamic elesticity. The methods discussed are based on tools such as : harmonic analysis, compensated compactness and logarithmic control of Sobolev’s embeddings. References: [1] J. Ball, Global attractors for semilinear wave equations, Discr. Cont. Dyn. Sys. 10 (2004), 31-52. [2] G. Sell and Y. You. Dyanamics of Evolutionary Equations. Springer Verlag, 2002. [3] I. Chueshov and I. Lasiecka, Long-time behavior of second order evolution equations with nonlinear damping, Memoirs of AMS, vol.195, no. 912, AMS, Providence, RI, 2008. [4] I. Chueshov and I. Lasiecka. Von Karman Evolutions-Wellposedness and Long Time Dynamics, Springer Verlag, to appear 2009. 30 Elbert MACAU , National Institute for Space Research - INPE, Brazil Title: Controlling Chaotic Transient and the Improvement of System Flexibility In this work, we address the problem of how to exploit the dynamics behind a chaotic transient behavior to improve system performance and adaptability to many operational conditions requests. The phenomenon of chaotic transient is explained as due to the presence of a chaotic saddle in the phase space. Different systems operation points can be associated to the set of unstable periodic orbits that exists embedded in the chaotic saddle. A classical control procedure associated with a control of chaos strategy is proposed as a methodology to quickly guide system trajectories among different operation points and to keep the system on a particular operation point. The methodology is applied on an electronic circuit system. Robert M.M. MATTHEIJ , Technische Universiteit Eindhoven, The Netherlands Title: Flow in networks Turbines (jet engines or gasturbines) have rotors at the hot end that need to be cooled. This cooling is done by blowing cool air through the blade (internal cooling) or through holes in the surface (to provide for film cooling). A variety of methods is used to drill these holes (electrochemistry or laser drilling), Simulation of the flow eventually provides for a complex problem that is tackled by a domain decomposition technique. Toshiya NAKAMURA, Japan Aerospace Exploration Agency, Japan Title: JAXA’s Aeronautical Research Project for Civil Transport - Endeavours to Enhance Safety and Environmental Friendliness The Aviation Program Group of Japan Aerospace Exploration Agency (APG/JAXA) is moving forward in its research and development on advanced / fundamental aeronautical technologies in consideration of social demand such as advancement of aircraft safety and environmental compatibility for diversify needs and increase of air transport in the future. One of the goals of JAXAs aviation program is to develop the cutting-edge technologies which can be applied to the development of competitive aircraft in the world market. To achieve this, JAXA launched a research project in 2003 which covers wide variety of aeronautical science and technology: computational fluid dynamics (CFD), advanced optical measuring methods in wind tunnel test, aero-acoustic analysis (computational aero-acoustics, CAA) and identification of noise sources, computational tool to analyze transonic flutter behavior, analysis and test for crashworthiness, composite materials and structures, and control systems. This presentation describes JAXAs efforts conducted in the project in some details. Firdaus E. UDWADIA, University of Southern California, Los Angeles, USA Title: Advances in the Modeling and Control of Complex Multibody Systems A new general integrated method for the modeling and control of complex multibody systems is presented. The method utilizes recent results in analytical dynamics adapted to general complex multibody systems. The term complex is employed to denote those multibody systems whose equations of motion are highly nonlinear, non-autonomous, and possibly yield motions at multiple time and distance scales. The approach considered herein opens up new routes for modeling general multibody systems by explicitly developing closed form expressions in terms of any desirable number of generalized coordinates that may appropriately describe the configuration of the multibody system. Furthermore, the approach is simple in implementation because it poses no restrictions on the total number and nature of modeling constraints required to construct the equations of motion of the multibody system. Conceptually, the method relies on a simple three-step procedure. It utilizes a new set of equations of motion developed, which describes the explicit equations of motion for constrained mechanical systems with singular mass matrices. The simplicity of the method is highlighted by illustrating its use in the modeling and control of a multibody spacecraft system for which we provide numerical results of the system’s response. 31 Stanislav N. VASSILYEV , Institute of Control Sciences, Russian Academy of Sciences Title: Analysis of Dynamics of Hybrid Systems with Nonlinear Vector Fields by Homomorphic Mappings Hybrid systems with switching nonlinear vector fields of ordinary differential equations (ODE) are considered. The analysis of the dynamical properties of stability and attractivity in those models are reduced to a problem of analysis of analogous dynamics in impulsive differential equations. A reduction method with trajectory homomorphism from the initial model to auxiliary one is used. Some examples are considered. Brian WHITE , Cranfield University, Defence Academy of the United Kingdom Title: Path Planning and Decision Making for Co-operative Multiple UAVs The use of multiple UAVs for mapping and surveillance is becoming practical in the near future. As such, autonomous behaviour that is robust and predictable is necessary for such use. This presentation will describe the role of decision making and path planning in producing an autonomous system that can survey areas that have some rural areas and some urban areas, together with some structured waterways. This implies that paths need to follow route structures that are related to road networks, waterways or other natural features that require specific paths, such as valleys, forest clearings. In order to produce an autonomous system that has specific guaranteed behaviours, the link between the decision making code and the path planning needs to be defined in such a way as to be expressible in both domains. In terms of path planning, routines to search route networks will involve examining graph concepts such as the Chinese Postman Problem to produce a path that will traverse each road within the network, the Travelling Salesman Problem to produce paths that will overfly all raod junctions within the network, together with techniques to survey open areas with multiple UAVs. Decision making techniques using Temporal Logic to define the system behaviours will be presented. The resulting decision making and path planning techniques are illustrated by use of case studies that cover tracking contaminant clouds, monitoring highway traffic to surveying rural areas using UAVs and UGVs will be presented. Othon C. WINTER, Orbital Dynamics & Planetology Group - UNESP, Brazil Title: On the Dynamics of Triple Asteroid Systems In 2005 was discovered the first triple asteroid system, named Sylvia with satellites Romulus and Remus. This system is located in the middle of the main asteroid belt. At the present moment are known almost ten triple asteroid systems. They were found not only in the main asteroid belt, but also among the NEAs and among the TNOs. Their dynamics and stability are quite complex. There are cases where appear intriguing resonances, close encounters with planets and the non-spherical gravitational potential of the central body can play an important role on the stability of the system. In this presentation we will give a general view of this class of systems and will discuss the stability and evolution of the particular cases of 87 Sylvia and the 2001SN263. 32 GENERAL SESSION Temperature-dependent explicit stress-strain relations for stainless steel alloys Kenzu Abdella, Qatar University, Qatar This paper presents a new stress-strain relation for stainless steel alloys that provides the stress as an explicit function of strain and temperature. The relation is an approximation of the closed form inversion of an existing two-stage stress-strain relation based on a modified Ramberg-Osgood equation with an appropriate modification to account for temperature dependence. This new expression for the stress as an explicit function of the total strain, and temperature is obtained by making a modified power law assumption on the fractional deviation of the actual stress-strain curve from an idealized linear elastic behaviour. The validity of the temperature-dependent expression is tested over a wide range of material parameters and a wide range of temperatures. The tests show that the new expression is both qualitatively and quantitatively consistent with the fully iterated numerical solution of the full-range temperaturedependent stress-strain relation at moderate and high temperatures. Convergence study of the condition number for some preconditioners to the Stokes problem Omar Ali Aleyan, University of Almergeb, Faculty of Arts and Science Zliten, Libya We deal with the properties of the approximation of the Stokes equation which leads to the linear system Ax = b. We investigate the preconditioners of Block Diagonal, Upper Block Triangular, Lower Block Triangular and the Incomplete LU factorization preconditioner; Wathen and Silvester, Elman and Silvester, Grad-Div stabilization and Artificial Compressibility type. We also study the Simple, Simplic and Simpler preconditioners. We show the dependence of the condition number on the mesh size both on tables and graphs. Fuzzy differential equations Tofigh Allahviranloo, Azad University, Tehran, Iran In this presentation I am going to discuss about several methods of finding, numerically and analytically, solutions of first order Fuzzy Differential Equations(FDEs) and higher order FDEs. First of all, the existence and uniqueness of the solution are discussed. Then, difference methods such as Runge-Kutta, Predictor-Corrector and the differential transformation method are presented. Analytical methods such as the fuzzy Laplace transformation, Eigen value and vector and Expansion methods are also introduced. Finally, all of the above mentioned methods are followed by consideration of related theorems in detail and some numerical examples are solved. Nonlinear Analysis of Cables and Guyed Towers Shahin Nayyeri Amiri , Kansas State University, USA The research reported herein is on the nonlinear analysis of cables and guyed towers. Cables are analyzed without making a prior assumption as regards the type of loading on them and their final geometry. Nonlinear constitutive relations are also considered. After discussing the previously proposed analysis techniques, a Newton-Rasphson solution procedure is proposed for solving the cable equilibrium equations. The mast of the tower is assumed to be a beam-column having a spring mounted base and supported by preloaded nonlinear springs. These springs represent the effect of guy cables. A procedure is described and a computer program is developed for the nonlinear analysis of guyed towers under arbitrary loads. The program is applied to the analysis of some sample guy cables and guyed tower models to check the accuracy of the analysis procedure and of the program. 33 Size, shape and stability evaluation for meniscus appearing in microfiber growth by pulling down method Agneta Maria Balint, Stefan Balint West University of Timisoara, Romania The process parameter considered in this paper is the pressure p, which incorporates the gas pressure in front of the free surface of the meniscus, the hydrostatic pressure of the melt column situated behind the meniscus, the hydrodynamic pressure associated to the thermoconvection in the meniscus and the Marangoni pressure associated to the Marangoni convection. The meniscus’s shape and size are analyzed in function of the above parameter p. More precisely, for a meniscus having a given shape and size, the range of the values where p should be, is found. Furthermore, it is shown that if p is in a prescribed range, then a meniscus, having a given shape and the size (crystal radius) in a given range, is obtained. Finally, the (static) stability of the menisci is analyzed. For NdYAG microfiber numerical illustrations are given. On the structural stability of systems of differential equations occurring in aerospace engineering Stefan Balint, West University of Timisoara, Romania Frequently, the evolution of real phenomena is described by systems of ordinary differential equations. These systems express physical laws, geometrical connections, and they are often obtained by neglecting some influences and quantities which are assumed negligible with respect to others. The simplified system describes correctly the real phenomenon if and only if it is topologically equivalent to the system in which the small influences and quantities are also included. This means that there exists a homeomorphism of the parameter space and a parameter dependent homeomorphism of the phase-space, which sends the orbits of the simplified system onto the orbits of the non simplified system. A system defined in a region D is structurally stable in a sub-region of D if any system sufficiently close in D is topologically equivalent in the sub-region to the initial system. This talk presents systems used in aerospace engineering which are structurally stable, systems for which structural stability has never been proved, and systems which are not structurally stable, opening the problem of legitimacy of the use of the last two types of systems. Diversity QPSK-CDMA schemes for LEO mobile communication Luis Wwaack Bambace, National Institute for Space Research -INPE, Brazil CDMA radio to station links are asynchronous and thus user signals are not absolutely orthogonal though interference is low. Separation from a cell to another requires a long code that with a period different of the symbol. Due to residual interference issues if all user operates at full power the number of possible user is reduced, so good capacity is assured by fast control of individual user transmission levels, independently of what error correcting code is used. In satellite systems the transmission delay avoids a fast control, and its necessary to use another scheme to enhance traffic capacity. Except for Globalstar, that remain close to IS95 standard, all the other systems made option to long pseudo random codes and Gold codes to separate users. Here is described a diversity scheme that use the fact that slipping the long code and keeping matched the Gold codes of copies of messages of a radio, they are nearly orthogonal one to each other, and its annoying effect in other user per unit of energy is unchanged. This channeling expansion allows diversity to be used, reducing the average power per user and enhancing capacity. A new real inversion formula for the Sumudu Transform Fethi Bin Muhammad Belgacem, Arab Open University, Kuwait So far the inversion formula for the Sumudu transform has been complex related established through the residue theorem. In this paper, we present a new real inversion formula for the Sumudu transform. 34 Designing Phase-Locked Loops for Frequency Modulation Atomic Force Microscope Atila Madureira Bueno, Universidade Estadual Paulista, Brazil José Manoel Balthazar , Universidade Estadual Paulista, Brazil José Roberto Castilho Piqueira, Universidade de São Paulo, Brazil The Atomic Force Microscope introduced the surface investigation with true atomic resolution. In the noncontact mode of operation both amplitude and frequency modulation methods can be implemented by using Phase-Locked Loops (PLLs). The Frequency Modulation - Atomic Force Microscope (FM-AFM) control system consists of two control loops, i. e, the amplitude and distance control loops. The amplitude loop controls the cantilever’s oscillation amplitude, and the distance loop controls the mean distance between tip and sample. The PLL performance is vital to FM-AFM control system since it generates the feedback signals to both the amplitude and distance control loops. Nevertheless, little attention is drawn to PLL design and performance in atomic force microscopy literature. Perhaps because designing stable higher order PLLs, in contrast to second-order, demand some effort. A virtual FM-AFM is implemented and the calculations of FM-AFM images are presented. The results are compared considering the various PLL designs, attempting to determine the best characteristics of PLL response to the FM-AFM system. Improvement in Relational Databases Query Using Fuzzy Logic Vanessa Avelino Xavier de Camargo, Wemerson Leonardo Ramos , Esdras Teixeira Costa, Marcos Wagner Souza Ribeiro Federal University of Goias, Brazil Fuzzy Logic and Fuzzy Set Theory have been widely exploited on account of their feature to translate uncertain, ambiguous and vague information - typical of human beings thoughts - to numerical data. The scope of fuzzy applications is actually large and it may be increasing. One of its applications is in Relational Databases, promoting an improvement in information retrieval. In this context, this paper presents a convenient and simple way to treat linguistic variables in database queries with the aim to make data retrieval closer to imprecise human reasoning. A trigger, using Structured Query Language (SQL) and MySQL Database Management System, has been created to make fuzzy membership degrees based on trapezoidal fuzzy numbers. With the purpose to illustrate and test the advantages of this approach, a case study based on age variables - child, young, middle-age, elderly - has been done, assuming an insurance company interested in setting values according to the age of customers. As conclusion, a parallel between fuzzy and traditional (crisp) queries results has been shown, beyond future works. Evolutionary Programming with Adaptative Stable Distributions Leopoldo Bulgarelli Carvalho, Pedro P.B. de Oliveira Mackenzie University, Brazil Recent applications in evolutionary programming have suggested the use of further stable probability distributions, such as Cauchy and Lévy, in the random process associated with the mutations, as an alternative to the traditional, also stable, Normal distribution. This work considers a new self-adaptative class of algorithms in respect to the determination of the more adequate stable distribution parameters for optimization problems. Evaluations that rely upon standard analytical benchmarking functions and comparative performance tests between them were carried out in respect to the baseline defined by a standard algorithm using Normal distribution. Additional comparative studies were made in respect to various self-adaptive approaches, also proposed herein, and an adaptive method drawn from the literature. The results suggest numerical and statistical superiority of the more general stable distribution based approach, when compared with the baseline. However, they show no improvement over the adaptive method available in the literature, possibly due, at least partially, to implementation decisions that had to be made in the present implementation, that were not made explicit therein. 35 Semi active suspension control techniques using only one measurement sensor Fábio Luis Marques dos Santos, Luiz Carlos Sandoval Goes, Alberto Luiz Serpa Instituto Tecnologico de Aeronautica, Brazil In this paper two control strategies are addressed - the Linear Quadratic Regulator (LQR) and the Internal Model Control (IMC). These techniques were tested in a system where saturation is present, the semi-active suspension problem. They are then evaluated by some performance indexes that characterize the problem as optimization problems, and solved by the use of some specific tools of the MATLAB software. The main goal is to obtain optimal performance, in order to minimize the sprung mass (chassis) acceleration and to ensure road-holding characteristics, while minimizing the number of feedback sensors used. To make-up for the minimum sensor usage, state observers are designed. A comparison is then made, by means of numerical simulation, using a quarter-car model and real road profiles as well. 6-DOF data and aerodynamic models for real-time flight simulation Pedro S. Giraudo, National University of Cordoba, Argentina Javier E. Luiso, Instituto de Investigaciones Cientı́ficas y Técnicas para la Defensa, Argentina Eduardo N. Zapico, National University of Cordoba, Argentina Horacio A. Abbate, Instituto de Investigaciones Cientı́ficas y Técnicas para la Defensa, Argentina The purpose of this paper is to present the data model developed for a 6DOF real-time flight simulator. The simulation engine in which this data model is embedded is also briefly presented. As usual, the aircraft aerodynamic is defined through aerodynamic coefficients, which are dimensionalised to calculate the acting forces and moments on the aircraft. In order to take into account a complete aerodynamic parameter set, which results necessary for an accurate simulation, great information volume is required; in this paper the matrix organization used for the treatment of these data is presented, which proved to be fast and accurate, moreover allowing to use simple search and interpolation algorithms. Finally, simulation results obtained for a 6-DoF model of a military trainer aircraft are presented. Dynamic simulation of light space structures by finite element modeling and order reduction in state space Leandro Gonzalez, Eduardo N. Zapico National University of Cordoba, Argentina The state space formulation of the equations of motion allows to achieve simple dynamic models from complex structures, in order to integrate them to a dynamic simulation program which will be acting like an efficient platform for high shock load structures design, suitable on space mission development. In the beginning of a new structural design project will be required to acquire sensitivity and knowleadge on the dynamic problem to study, when no definitive design has been established yet, and the component dynamic properties of the structure are not certainly known either. Its usual to propose simplified system models for several constructive solutions, while latter project stages involves generally structural changes which compel to re-examine the entire dynamic behaviour; then is desirable in this design stage to have the smallest dynamic model that still provides a precise representation of system dynamics and allows a quick proposal evaluation, with the aim to reduce the solicitations over critical satellital components.¡/p¿¡p¿In this paper a certain satellital configuration is proposed for a preliminar dynamic analysis by the finite element method, with the aim of generate a flexible enough model to admit latter adjusts on the basis of behaviour appreciations and test results. Then, a reduction method for high order lineal dynamic systems is applied by means of balanced gramians, with the intention to obtain a state space reduced order model. Flight or Fight - Battle of the Overheads Bins: Another Factor Contributing to the Air Rage Phenomenon Joyce A. Hunter , Saint Xavier University, Graham School of Management, Chicago, USA Baggage fees have been implemented within many of the airline carriers for both domestic and foreign travel. With the recent mandate for baggage fees by airlines, passengers are struggling to gain access to the overhead compartments. As more flyers use carry-on bags, there is less room in the bins. Six passengers are competing for overhead bin space designed to fit four wheelie bags. This condition leaves 36 some fliers out of luck at a time when more of them are opting to lug their bags, rather than check them, to avoid airline fees. Boarding lines move at a snail’s pace when the last luggage bins are filled and passengers are forced to deplane and return to the jet bridge to check their bags. The baggage situation has frustrated travelers and, for many of them, has added even more stress to their travel experience. This stress is a physiological and psychological experience of disruption to their homeostatic balance. It has been documented that since the start of last year, the number of bags checked at the boarding gate has risen nearly 50 percent, while the volume of bags checked at the ticket counters has dropped 18 percent. Air travel has changed over the past year and a half. Both the fees and space constraints can contribute to a breakdown in social conventions as passengers increasingly feel that they are left to fend for themselves. As planes fill and tensions rise, carriers are exploring ways to ease congestion in their aisles. This paper will focus on strategies to deal with the battle for limited overhead bin space and explore solutions to alleviate the related passenger congestion in the aisle on board the aircraft. Elementary proof of the Fermat’s Last Theorem Artur Korgul, Rafal Andrzej Korgul Patent Office of the Republic of Poland Fermat’s Last Theorem (FLT) was until the mid-1990’s the most famous unsolved problem in mathematics. In about 1637 Pierre de Fermat stated that: For all n > 2 there do not exist x, y, z such that xn + y n = z n , where x, y, z are positive integers. He claimed that he had a simple proof of this theorem, but no record of it has ever been found. Ever since that time, countless professional and amateur mathematicians have tried to find a valid proof. Even outstanding mathematicians (e.g. Euler, Legendre, Dirichlet and others) could only prove that this equation worked for individual numbers n. In 1994 professor Andrew Wiles of Princeton University announced that he had discovered a proof while working on a more general problem in geometry [1]. Wile’s proof is based on modern mathematical tools, which were not known for Fermat. Apparently the Fermat’s proof should be not beyond seventeenth century mathematics. Is it possible that FLT has a simple solution, it was an open question to date. This paper presents an elementary proof of Fermat’s Last Theorem. Reference: [1] Singh, Simon. Fermat’s Enigma. New York: Anchor Books, 1998. GA Optimization of Point Placement on a Hypersphere Janko Milutinovic, Delaware State University, USA Dragoljub Pokrajac, Delaware State University, USA Sam Kennerly , Drexel University, USA Placement of points on a hypersphere according to a pre-specified optimization criterion is an important problem with potential applications ranging from spherical coding theory to computational geometry to defense. Unfortunately, optimal point configurations are known only for a limited number of cases in lower dimensional spaces. Genetic algorithms have been applied to optimal point placement on a 2D sphere. Here, we investigate applications of genetic algorithms to higher dimensional optimization. We utilize minimal energy or maximized minimal inter-point distance optimization criteria, and propose and compare several genetic algorithms crossover and mutation operators. On Thermal Instabilities Occuring in Fires Vasily Novozhilov , University of Ulster, UK The presentation identifies a unified mathematical approach to description of a number of thermal instabilities typically observed in fire behaviour. Consideration is mostly focused on compartment fires. The two key instabilities that are most important in fire behaviour are ignition and flashover. Proposed mathematical framework for consideration of these instabilities relies on the concept of conjugate 37 thermal explosion, proposed and developed recently by the author. This concept generalises the classical thermal explosion theory, and has been found very useful in interpreting fire instabilities, as well as some other combustion phenomena. In the present talk, relevant mathematical models are developed, and their dynamics is investigated. Generally, the proposed formulation leads to non-linear integro-differential equations. As a specific example, dynamical model of fire flashover is investigated in more detail. For such a model, we study qualitatively the set of corresponding integro-differential equations, and derive critical conditions for flashover. Finally, other potential application of conjugate thermal explosion theory are briefly discussed. Introduction to Theory of Physical-Geometry Space Ahmad Sabihi , Sharif University of Technology, Tehran, Iran In this paper, the Author wishes to present a novel Mathematical-Physics Theory in an n-dimensional space which is called Physical-Geometry Space Theory. This theory deals with global space geometry of the universe. As well-known, Einstein gave General Theory of Relativity in 1915. The theory represented a general view of the universe so that could connect mechanical sciences with non-Euclidian space in pure mathematics. The theory does not consider space’s geometrical characteristics in each time created by physical conditions. On the other word, the parameters of geometry and physics are considered to be isolated from one another. Here, the Author improves the theory by considering geometrical characteristics and parameters in combination with physical variations made by both observer coordinate system oscillation and circumstances. Also, the universe extension and curvature of space and time are taken into account. Therefore, the Author proves that variation of geometrical parameters of space can affect mechanical and physical events. String, superstring theory, and M-theory can demonstrate the special cases of this theory in quantum mechanics and general relativity or quantum relativity mechanics (quantum field theory). An Approach Towards the Proof of the Strong Goldbach’s Conjecture for Sufficiently Large Even Integers Ahmad Sabihi , Sharif University of Technology, Tehran, Iran The author approaches to a new proof of the strong Goldbach’s conjecture for sufficiently large even integers by applying to the Dirichlet’s series. Using Perron formula and the Residue Theorem in complex variable integration, one could show that any large even integer is demonstrated as a sum of two primes. A novel function is defined on the natural numbers set. This function is a typical sieve function. Then based on this function, several new functions are represented and using Prime Number Theorem, the Conjecture is proved for large even integers. Model based planning of the capillary and thermal conditions for the growth of a silicon tube with a prior given inner and outer radius Loredana Tanasie, Stefan Balint West University of Timisoara, Romania This paper an algorithm is presented for the choice of the capillary and thermal conditions which assure a stable growth of a silicon tube with a prior given inner and outer radius. The algorithm is based an mathematical model in which the tube growth is described by a system of the three nonlinear ordinary differential equations. Impact Behaviour of Sandwich Plates : Theoretical and experimental investigation Ertan Tengiz, Demet Balkan, Halit Suleyman Turkmen, Zahit Mecitoglu Turkey The sandwich materials are widely used in aerospace structures. This is because they have high stiffness to weight and strength to weight ratios, good vibration damping characteristics, and impact resistance. In this study, the sandwich plates subjected to the impact loading are investigated theoretically and experimentally. For this purpose, two types of sandwich plates are produced. The first one has carbon/epoxy facings and aramid honeycomb core and the second one has glass/epoxy facings and a 38 stepwise graded viscoelastic core. The plates are produced using a heated vacuum table and hand lay-up technique. The plate is tested against an impact. The plate is also modeled using the finite element method and impact analysis is achieved. In the finite element method, the plate is modeled using the layered shell elements. The mechanical properties of the sandwich plate are obtained experimentally. For this purpose, three point bending test and dynamic mechanical analyzing (DMA) test are used. The properties determined experimentally are used in the impact analysis. The results are compared and an agreement is found between the experimental and numerical results. 39 SPECIAL SESSION 1. Neural Network Dynamics Organizers: Eva Kaslik (Romania), Seenith Sivasundaram (USA) This special session will focus on the area of neural networks mathematical theory, analysis, simulations and applications in engineering, aerospace and all areas of sciences. Intended audience includes researchers for neural applications as well as those with mathematical interests. Almost Periodic Solutions of Impulsive Hopfield Neural Networks with Periodic Delays Haydar Akca, United Arab Emirates University, Al Ain, UAE Valery Covachev , College of Science, Sultan Qaboos University, Muscat, Sultanate of Oman and Institute of Mathematics, Bulgarian Academy of Sciences, Sofia, Bulgaria Zlatinka Covacheva, Higher College of Technology, Muscat, Sultanate of Oman and Higher College of Telecommunications and Post, Sofia, Bulgaria An impulsive Hopfield neural network with delay which differs from a constant by a small amplitude periodic perturbation is considered. If the corresponding system with constant delay has an isolated ω-periodic solution and the period of the delay is rationally independent with ω, then under suitable assumptions it is proved that in a sufficiently small neighbourhood of this orbit the perturbed system has a unique almost periodic solution. Bifurcation Networks: An Approach to Cortical Modeling and Higher Level Brain Function Nabil H. Farhat, University of Pennsylvania, USA Evidence is presented in support of the hypothesis that the basic functional unit in the cortex, the seat of higher-level brain function, maybe mathematically modeled by a bifurcation processing element consisting of a parametrically driven noninvertible map on the unit interval such as the logistic map. Such simplifying abstraction is shown to capture functional attributes of thalamo-cortical units as seen in numerical simulations to be presented for a network of parametrically coupled maps. Under extrinsic dynamic input, the network exhibits input-specific attractors in the form of isolated clustering of activity analogous to Hebbian assemblies and the ”hot-spots” of activity revealed in functional fMRI in the brain of a subject engaging in a cognitive task. These networks can play an important role in explaining self-organization, bifurcation and chaos in higher-level brain function and lead to their abstraction into artificial systems for use in specific applications that are beyond the abilities of present day neural networks and connectionist models. Artificial neural networks applied to low cost INS/GPS integrated navigation systems Edmundo Alberto Marques Filho, Atair Rios Neto , Hélio Koiti Kuga National Institute for Space Research - INPE, Brazil This paper addresses the use of artificial neural network (ANN) into Global Positioning System (GPS) aided low cost inertial navigation systems based on micro-electromechanical sensors (MEMS). The GPS technology dominates, nowadays, the positioning and navigation (POS/NAV) general market, and alternative POS/NAV systems are only needed because GPS does not work in all environments, or can not provide reliable solutions, under certain circumstances, during some time interval. There are different solutions to fulfill information during GPS blockage and integrated inertial sensors systems with GPS are frequently used with stochastic parameter estimation techniques. However, low cost inertial sensors have the disadvantage of accumulating continuous errors in great extension, leading to poor system performance. In this context a multi-layer feed-forward ANN is applied, to provide better NAV/POS solutions, during the lack of information in GPS outages portion of time. This work presents: an approach to model the input-output ANN signals based on a set of constrained land vehicle navigation equations; an adaptive ANN training Kalman filtering methodology and preliminary numerical simulation results based on urban vehicular positioning application data, acquired from low cost Crossbow CD400-200 inertial measurement unit and an Astech Z12 GPS receiver. 40 Multistability in impulsive Hopfield neural networks with time-dependent and distributed delays Eva Kaslik , West University of Timisoara, Romania Seenith Sivasundaram, USA In this paper, we investigate the multistability properties of impulsive hybrid Hopfield-type neural networks with time-dependent and distributed delays, by using Lyapunov functionals, stability theory and control by impulses. Examples and simulation results are given to illustrate the effectiveness of the results. Controlling the chaotic dynamics of neural networks Francisco Welington Lima, Universidade Federal do Piauı́, Brazil Tarik Hadzibeganovic, Austria Roughly the past decade of research on chaos control in neural networks will be reviewed and discussed, with a focus on the most actively developing directions and applications. A particular attention will be given to a method using local control, i.e. pinnings acting only on a small subset of neuronal units. Pertinent simulation results employing this method will be compared against other competing approaches. As it will be demonstrated, there are many practical advantages in knowing how to take a system with a large number of degrees of freedom from a chaotic to a fixed or periodic behavior. Stability and Bifurcation Analysis Of Three Neuron Delayed Network Model Of Hopfield Type Narayan Chandra Majee, Amiya Busan Roy Jadavpur University, India In this paper we have studied the dynamics of three neuron network model of Hopfield type with time delay in signal transmission. Results regarding delay independent stability, estimation of critical delay to preserve stability for the linearised system is obtained. Considering time delay as the bifurcation parameter Hopf type bifurcation is discussed of the said model. Computer simulation results are also presented depicting different dynamics like stable equilibrium, stable limit cycle and twin limit cycle of the model. Neural Network based Model Predictive Controller for Simplified Heave Model of an Unmanned Helicopter Mahendra Kumar Samal , Sreenatha Anavatti, Matthew Garratt Univeristy of New South Wales at Australian Defence Force Academy, Australia Neural Network based model predictive controller (NN-MPC) scheme for designing autonomous flight control of a rotary-wing unmanned aerial vehicle is presented in this paper. The applicability of the NNMPC scheme is evaluated on a simplified heave model of the helicopter in simulation. Neural Network (NN) based system identification (NNID) technique is used to model the nonlinear dynamics of the unmanned helicopter. The NN model is then used in the MPC algorithm to estimate the future control moves. To show the efficacy of the NN-MPC scheme, controller results are provided. Results indicate that NN-MPC scheme is capable of handling external disturbances and parameter variations of the system. Bumps in a two population neural field model John Wyller, Norwegian University of Life Sciences, Norway Neural field models have a long tradition in mathematical neuroscience. In the present talk a survey of a two-population neural field model describing excitatory and inhibitory neurons interacting via nonlocal spatial connections will be given. Results from investigations of such models on the existence and stability of stationary localized activity pulses (”bumps”) and generation of stationary spatial and spatiotemporal oscillations through a Turing-type of instabilities will be described. 41 SPECIAL SESSION 2. Unmanned Aerial Vehicles Organizer: Gilney Damm (IBISC Lab. - Evry - Val d’Essonne University, France) This special session is dedicated to Unmanned Aerial Vehicle’s (UAV) control, models and applications. UAVs may be of different kinds, and may range from helicopters less than 1 meter wide used for indoors inspection, to unmanned airplanes of several meters. Structural modeling and optimization of a joined-wing configuration of a high-altitude longendurance (HALE) aircraft at global and local levels Valentina Kaloyanova, Karman Ghia, Urmila Ghia University of Cincinnati, USA A high-altitude long-endurance mission requires a light vehicle flying at low speed at altitudes of 60, 000 − 80, 000 ft, with a continuous loiter time of up to several days. To provide high lift and low drag at these high altitudes, where the air density is low, the wing area should be increased, i.e., highaspect-ratio wings are necessary. To reduce the structural deformation, and increase the total lift in a long-spanned wing, a sensorcraft model with a joined-wing configuration, proposed by AFRL, is employed. A detailed finite-element model of the joined-wing is built and nonlinear static analysis performed for the aerodynamic load corresponding to flow at altitude 60, 000 ft, M = 0.6 and α = 12◦ . Design optimization is carried out at global and local levels. At local level detailed models of wing panels are constructed. Bi-level optimization resulted in a wing structure with mass of 1001.33 kg and wing tip deflection of 3.93 m or 10.5% of the wing length. Determination of Intelligent Control system for a Nonlinear Model of an Autonomous Scale-Model Helicopter by Emotional Learning Approach Abolfazl Mokhtari , K.N. Toosi University of Technology, Iran There is a growing interest in the modeling and control of model helicopters using nonlinear dynamic models and nonlinear control. Application of a new intelligent control approach called Brain Emotional Learning Based Intelligent Controller (BELBIC) to design autopilot for an autonomous helicopter is addressed in this paper. This controller is applied to a nonlinear model of a helicopter. This methodology has been previously proved to present robust characteristics against disturbances and uncertainties existing in the system. The controller design goal is that the helicopter tracks a special maneuver to reach the commanded height and heading. The performance of the controllers is also evaluated for robustness against perturbations with inserting a high frequency disturbance. Simulation results show a desirable performance in both tracking and improved control signal by using BELBIC controller. Nonlinear flight dynamics analysis of flapping wing micro-air vehicle model Victor Mwenda Mwongera, Mark Lowenberg Department of Aerospace Engineering, University of Bristol, UK The limitations placed on the size of flapping wing micro-air vehicles (MAVs) means that they operate in a region of highly unsteady aerodynamics, dominated by 3D effects. Thus, a comprehensive flight dynamics model would be nonlinear, with associated problems in evaluating stability and control. Nonlinear dynamical systems theory - specifically bifurcation methods - is therefore seen to be useful for analysing the flight dynamics system of equations. An aerodynamic model has been created to capture the flow regime, using a modified blade element theory. The model is initially limited to rigid body modes, with only the effects of inertial accelerations of the flapping wing being coupled to the modified quasi-steady aerodynamic analysis. The system is periodically forced and an appropriate form of numerical bifurcation analysis is then applied to this system. From this, tools for looking at the oscillatory steady states can be developed, especially in response to perturbations in wing beat parameter changes; the flap, lag and feather frequencies and amplitudes. The stability analysis and steady state variation will then be used to define preliminary simplified vehicle control system boundaries, and also create a base of knowledge for introducing other effects such as structural dynamics, wind gusts/perturbations and ultimately time-dependent aerodynamics. 42 UAS test platform for parameter identification of powered paraglider András Nagy, József Rohács Budapest University of Technology and Economics, Hungary The design of remotely controlled and unmanned aerial system (UAS) is an important direction in modern aircraft development. Some researches are aimed at UASs which use paraglider canopy as their wing. This group of UASs can be successfully used in applications where stable, low speed flying and mobility are required. In this paper, we introduce a UAS test platform being developed by us, which can be used to test different paraglider canopy. We focus on paragliders used for leisure purposes which have take-off weight up to 150 kg. The most important thing when a new type of UAS is born is the automatic control, which has a very critical function: it has to keep the vehicle in stable fly. To realize this function the motion equations and the parameters of the mathematical model must be known. With the help of our test platform this parameters can be identified and measured along with other flight dynamics parameters. The mathematical model applied in this paper and suggested in another paper is focused on the longitudinal motion of powered paragliders. The applied mechanical model of the vehicle represents a single rigid body with three degrees of freedom that consists of a canopy (wing) and the UASs body (gondola). The wing and the gondola are connected by lines, which are modelled by rigid rods. A propeller producing a thrust is mounted on the gondola. This simple model is the first approximation of the powered paraglider, but it seems it is enough when we concentrate on its longitudinal motion. First investigations show that the difference remains under 4 − 5% between the results of the non-linear and linear model. Modeling and simulation of flapping wings nano-robots dynamics of flight Krzysztof Slavomir Sibilski , Air Force Institute of Technology, Poland Flapping wings micro aerial vehicles (MAV) flight stability and control presents some difficult challenges. The low moments of inertia of MAVs make them vulnerable to rapid angular accelerations, a problem further complicated by the fact that aerodynamic damping of angular rates decreases with a reduction in wingspan. Another potential source of instability for MAVs is the relative magnitudes of wind gusts, which are much higher at the MAV scale than for larger aircraft. Other problem occurs with influence of flapping wings on MAVs body motion. The birds and flying insects, the biological counterpart of mechanical MAVs, can offer some important insights into how one may best be able to overcome these problems. Biological systems, while forceful evidence of the importance of vision in flight, do not, however, in and of themselves warrant a computer-vision based approach to MAV autonomy. Fundamentally, flight stability and control requires measurement of the MAVs angular orientation. While for larger aircraft this is typically estimated through the integration of the aircrafts angular rates or accelerations, a visionbased system can directly measure the MAVs orientation with respect to the ground. The two degrees of freedom critical for stability the bank angle and the pitch angle can be derived from a line corresponding to the horizon as seen from a forward facing camera on the aircraft. Therefore, we have developed a vision-based horizon-detection algorithm that lies at the core of our flight stability system. Non linear filtering technique analysis for Navigation of an UAV Saman Mukhtar Siddiqui, Jiancheng Fang Beijing University of Aeronautics and Astronautics, China Integrated Navigation using Low cost MEMS Inertial Sensors and GPS along with some other secondary sensor is a wide area of research these days. Complementary characteristics of GPS and INS in giving long term and short term accuracy respectively make them an ideal combination for these type of systems. This multisensor approach has proved beneficial economically but requires intelligent filtering algorithims. The non linear dynamics of system prevents the use of conventional Kalman filter. Usually Extended Kalman filtering is a replacement in non linear environment but has certain limitations. This paper explores other techniques such as unscented Kalman Filter and Partical Filter to address the same problem on the same set of data of a UAV. The results are compared and demerits and merits of all approaches is deduced. The GPS is integrated in loosely coupled mode like all commercially available low cost systems. Other sensors include three accelerometers three gyros magnetometer, pressure sensor and air speed sensor. A simple north pointing navigation scheme is used with WGS84 earth model. The results are verified both 43 on simulations and actual tests. Error Analysis of MEMS sensor data using Allan Variance technique Saman Mukhtar Siddiqui , Jiancheng Fang Beijing University of Aeronautics and Astronautics, China For low cost commercial Navigation systems usually MEMS type inertial sensors are used along with GPS and other secondary sensors. These MEMS are low cost, light weight, easily manufacturable but highly erroneous as compared to their tactical grade counterparts. Error modelling of these sensors is done using techniques like PSD or Allan Variance technique. Allan Variance was originally developed for determining clock bias stability, a lot of work has been done on it with reference to calibration of inertial sensors and their sensitivity towards thermal change. This paper describes a study of calibration and error modelling of MEMS type sensors used in a UAV using Allan Variance technique. 44 SPECIAL SESSION 3. Advances in Nonlinear Differential Equations Organizers: Anjan Biswas (USA), Fengshan Liu (USA), Chaudry Masood Khalique (South Africa) This session will include all talks that are related to nonlinear differential equations that are both ordinary and partial. It will also include Stochastic Differential Equations. The focus will be on the solution techniques that include asymptotic analysis, Lie symmetry and Lie transform approach, Inverse Scattering Transform, Hirota Calculus, sub-ODE method, G’/G method, Adomian decomposition method, He’s variational principle and many more. The solutions will include nonlinear waves like the solitary waves, shock waves, compactons, cnoidal waves and others. The solutions obtained by using the multiple-scale perturbation analysis are also encouraged. Optical solitons with higher order dispersion Anjan Biswas, Delaware State University, Dover, Delaware, USA This talk is on optical solitons, in presence of higher order dispersion terms. The governing equation, namely the nonlinear Schrödinger’s equation, will be integrated by the aid of He’s semi-inverse variational principle. Both Kerr law and power law are taken into consideration. Wavelet transforms and its connection to established theories and Image Processing Bharat Namdeo Bhosale, University Of Mumbai, India Wavelet theory is the mathematics associated with building a model for a signal, system or process with a set of special signals. The past two decades have witnessed the development of wavelet analysis, a new tool which emerged from mathematics and was quickly adopted by diverse fields of science and engineering. In the brief period since its emergence in 1987-88, it has reached a certain level of maturity as well as well defined mathematical discipline; having broad range of applications including signal processing, data and image compression, solution of partial differential equations, modeling multiscale phenomena, and statistics. The connections with research in other fields have emerged and become clarified in recent years. In this paper, a strong relationship of FrFT with the Wavelet transform is established in n-dimensional set up. By exploiting this relationship, WT is extended to the spaces of Tempered Distributions. It is proved that the WT and its inverse, is a continuous isomorphism from S(Rn ) onto S(Rn ). Generalized WT is then defined using duality argument; and it is shown to be a continuous isomorphism from S(Rn ) onto S(Rn ). The theory so developed will have virtues of both FrFT and WT. This framework is used to explore its connections with established theories that include Fourier transform, Wigner distribution, Ambiguity function, Radon-Wigner transform and its applicability in Signal/Image processing. Solutions of Kadomtsev-Petviashvili equation with power law nonlinearity in 3+1 dimensions Chaudry Masood Khalique, North-West University, Mmabatho, South Africa In this talk we present some solutions of the Kadomtsev-Petviasvili equation with power law nonlinearity in 3+1 dimensions. The Lie symmetry approach as well as extended tanh-function and G0 /G methods are used to carry out the analysis. Subsequently, the soliton solution is obtained for this equation with power law nonlinearity. Both topological as well as non-topological solitons are obtained for this equation. 45 The Combined Effect of the Linear and Nonlinear Couplings on the Phase and Velocity Shifts of Interacting Solitons in Coupled Nonlinear Schrödinger Equations Michail D. Todorov, Technical University of Sofia, Bulgaria For a system of nonlinear Schroedinger equations (SCNLSE) coupled both through linear and nonlinear terms, we investigate numerically the taking-over interaction dynamics of elliptically polarized solitons. In the case of general elliptic polarization, analytical solution for the shapes of a steadily propagating solitons are not available, and we develop a numerical algorithm finding the initial shape. We use as superposition of generally elliptical polarized solitons as the initial condition for investigating the soliton dynamics. In order to extract the pure effect of the linear coupling, we consider the case without crossmodulation: the Manakov system to which a linear coupling term with real coefficient is added, when the individual solitons are actually breathers whose breathing frequency is defined by the linear coupling parameter. The interactions properties of the breathers differ from the the stationary shapes, mostly in the fact that changes of the initial phase angle of the components of the vector soliton do not affect the values of polarization after the interaction. The masses of the individual quasi-particles (QPs) oscillate, but the sum of the masses for the two QPs is constant. Respectively, the total energy oscillates during one period of the breathing, but the average over the period is conserved. When the linear coupling is purely imaginary then we observe gain or self-dispersion of solitons. Involving, however, into the interaction a nontrivial cross-modulation combined with different initial phase angles causes velocity shifts of interacted solitons. The results of this work outline the role of the initial phase, initial polarization and the interplay between the linear and nonlinear couplings on the interaction dynamics of soliton systems in SCNLSE. All the numerical experiments are implemented by using of fully conservative difference scheme in complex arithmetic. Generalized Radon transform and Microlocal analysis Guoping Zhang, Fengshan Liu Delaware State University, Dover, Delaware, USA One of the major inventions in last century is the CT-scanner (computerized Tomography). Cormack and Hounsfield got the Nobel-prize in Medicine 1979 for their work with computed axial tomography. The CT-scanner can be used for reconstruction of X-ray absorption in the interior of structures, such as patients or machine parts with possible internal fractures. The crucial idea for the image reconstruction is that Radon transform can provide a natural link between the image function of the object and the measurement of the machine such as CT-scanner and MRI. In this talk we will give a brief introduction to Radon transform, the generalized Radon transform and their relations with microlocal analysis theory. We will also provide some of their applications to image processing. 46 SPECIAL SESSION 4. Stability and Lyapunov Theory Organizer: Cemil Tunç (Yuzuncu Yil University, Van, Turkey) This session will be devoted to the Stability and Lyapunov Theory in Ordinary Differential Equations, Integral and Integro-Differential Equations, Functional Differential Equations (differential equations with constant delay, variable delay, neutral differential equations with constant delay, variable delay and their applications in control theory, mathematical modeling, shell theory, fluid dynamics, informatics, oscillation theory etc.). Some remarks on the exponential stability and periodicity of solutions for certain delayed differential equations of fourth order Olufemi Adeyinka Adesina, Obafemi Awolowo University, Ile-Ife, Nigeria The frequency domain method is used to prove the existence of a bounded solution which is exponentially stable, periodic or almost periodic (according as the forcing term is periodic or almost periodic). Results in the literature on corresponding situations where there are no delays are generalized. Numerical analysis for singularly perturbed delay differential equations Fevzi Erdogan, Yuzuncu Yil University, Van, Turkey We study numerical analysis of a difference scheme applied to singularly perturbed initial value problem for a linear second-order delay differential equations. An exponentially fitted difference scheme is constructed in an equidistant mesh, which gives first order uniform convergence in the discrete maximum norm. The difference scheme is shown to be uniformly convergent to the continuous solution with respect to the perturbation parameter. Numerical results are presented. References: [1] R. Bellman, K.L. Cooke, Differential-Difference Equations, Academy Press, New York, 1963. [2] R.D. Driver, Ordinary and Delay Differential Equations, Belin-Heidelberg, New York,Springer, 1977. [3] E.R. Doolan, J.J.H. Miller, W.H.A. Schilders, Uniform Numerical Methods for Problems with Initial and Boundary Layers, Boole, Press, Dublin, 1980. [4] P.A. Farrell, A.F. Hegarty, J.J.H. Miller, E. O’Riordan, G.I. Shishkin, Robust Computational Techniques for Boundary Layers; Chapman-Hall/CRC, New York, 2000. [5] H.G. Roos, M. Stynes, L. Tobiska, Numerical Methods for Singularly Perturbed Differential Equations, Convection-Difusion and Flow Problems, Springer Verlag, Berlin, 1996. [6] G.M. Amiraliyev, Y.D. Mamedov, Difference schemes on the uniform mesh for singularly perturbed pseudo-parabolic equations, Tr. J. of Math.,19(1995) 207-222. [7] G.M. Amiraliyev, F. Erdogan, Uniform numerical method for singularly perturbed delay differential equations, J.Comput. Math. Appl. 53(2007)1251-1259. [8] H. Tian, The exponential asymptotic stability of singularly perturbed delay differential equations with a bounded lag, J. Math. Anal. Appl. 270(2002)143-149. [9] C.G. Lange, R.M. Miura, Singular perturbation analysis of boundary-value problems for differentialdifference equations. v. small shifts with layer behavior, SIAM J. Appl. Math.54 (1994) 249-272. [10] M.K. Kadalbajoo, K.K. Sharma, Numerical analysis of singularly perturbed delay differential equations with layer behavior, Appl. Math. Comput. 157 (2004) 11-28. 47 Ultimate boundedness of solutions of non-homogeneous vector differential equation of the third-order Mathew Omonigho Omeike, University of Agriculture, Abeokuta, Ogun State, Nigeria We present here the ultimate boundedness of solutions of some nonlinear non-homogeneous vector differential equation of the third order, by means of the Lyapunov second method. We provide, in simple form, sufficient conditions which ensure ultimate boundedness of solutions of equations of the form ... X +φ(Ẋ)Ẍ + G(Ẋ) + H(X) = P (t, X, Ẋ, Ẍ). Results obtained generalize, improve and include the results obtained by previous authors. New stability and boundedness results of solutions of nonlinear differential equations of second and third order with variable delay Cemil Tunç, Yuzuncu Yil University, Van, Turkey In this paper, we investigate stability and boundedness of solutions to nonlinear certain differential equations of second and third order with variable delays. We find some sufficient conditions for solutions of these equations to be asymptotically stable and bounded by means of Lyapunov functional approach. Specific examples are given to show the effectiveness of our results. References: [1] Afuwape, A. U.; Omeike, M. O. On the stability and boundedness of solutions of a kind of third order delay differential equations. Appl. Math. Comput. 200 (2008), no. 1, 444-451 [2] Tunç, C., Some stability and boundedness results to nonlinear differential equations of Liénard type with finite delay. J. Comput. Anal. Appl. 11(4), (2009), 711-727. [3] Tunç, C., On the stability and boundedness of solutions to third order nonlinear differential equations with retarded argument. Nonlinear Dynam. 57 (2009), no. 1-2, 97-106. [4] Tunç, C., Some stability and boundedness conditions for non-autonomous differential equations with deviating arguments. Electron. J. Qual. Theory Differ. Equ. 1 (2010), 1-12. [5] Tunç, C., Some new stability and boundedness results of solutions of Liénard type equations with deviating argument, Nonlinear Analysis: Hybrid Systems, 4 (1), (2010), 85-91. [6] Tunç, C.; Tunç, E., On the asymptotic behavior of solutions of certain second-order differential equations. J. Franklin Inst., Engineering and Applied Mathematics 344 (5), (2007), 391-398. 48 SPECIAL SESSION 5. Contributions of PhD Students (and Post-Doctoral Researchers) Organizers: Anne Caroline Bronzi (Brazil), Dragos-Patru Covei (Romania) Many developments in the fields of Engineering, Aerospace and Sciences frequently occur as a result of the interaction between scientists and applied mathematicians. The high complexity of practical applications requires the joint work of specialists from different fields. The aim of this session is to give an opportunity to Ph.D. students and young post-doctoral researchers to present their own contributions related to mathematical problems from different fields, as well as to interact with other Ph.D. students. Weak solutions of the incompressible ideal flow equations Anne Caroline Bronzi , UNICAMP, Brazil The notion of weak solution allows for rather irregular, perhaps even turbulent, flows to be studied as solutions of the incompressible ideal flow equations. However, it is also clear that the notion of weak solution has severe shortcomings, allowing clearly nonphysical examples of weak solutions. We survey the analytical theory of weak solutions, specially some of the examples of weak solutions that highlight the shortcomings of the notion of weak solution and the possible avenues for producing a physically meaningful, complete theory. A Lane-Emden-Fowler type problem Dragos-Patru Covei , University Constantin Brancusi of Tg.-Jiu, Romania The problem of existence, non-existence, uniqueness, asymptotic behaviour, determination or numeric approximation of solutions for the Lane-Emden-Fowler type problems plays an important role in the scientific community, especially from the point of view of the fact that a significant number of processes from applied sciences are modelled by them, and general development provides us with new perspectives and research ways. This article improves the results achieved so far for some problems studied by the author during his PhD training as well as by other researchers from the scientific community. Superposition of a pulsating and oscillating flow of a complex structural liquid Edtson Emilio Herrera-Valencia, McGill University, Canada The rectilinear Poiseuille flow of a complex liquid flowing in a vibration pipe coupled with a pulsating-time pressure gradient is analyzed. The pipe wall performs ultrasonic vibrations (longitudinal and transversal). Pulsating flow can be adequately represented by a time Fourier series. In order to find an analytical expression for the flow enhancement a quasi-static perturbation solution in terms of a small parameter is suggested. The stress tensor is separated in two contributions, the first due to the solvent and the second to the polymer. The solvent is characterized by a Newtonian liquid and the complex liquid with the Bautista-Manero-Puig model (BMP) constitutive equation, consisting in the Upper Convected Maxwell equation coupled to a kinetic equation to account for the breakdown and reformation of the fluid structure. Several particular cases are analyzed and the results are consistent with other simple models that have been analyzed in the literature. The viscoelastic, kinetic and structural mechanisms were characterized by the association of non-dimensional numbers to each mechanism. Finally, flow enhancement is predicted using experimental data reported elsewhere for a worm-like micellar solutions of CETAT. Differential Transform Method of Solution for Non-Linear Boundary Value Problem: An Illustration Madhavanpillai Sumathykuttyamma Jagadeesh Kumar , Vellore Institute of Technology, India Suresh G. Singh, University of Kerala, India Pradeep Ganapathi Siddheshwar , Bangalore University, India Darcy Forchheimer Brinkman flows through porous media in different geometries are known to be quite formidable due to the governing equation being quasi-linear. A boundary value problem arising in such a flow through a rectangular porous box is considered in this paper for arriving at its solution by the differential transform method with assistance from the secant method. Comparison of the results of our 49 study is made with those obtained by using the finite difference method with quasi-linearization. Good agreement is found between the two results. Physical Programming based Multidisciplinary Optimization for 2D Turbine Airfoil Zhang Nannan, Northeastern University, China This paper concerns on the computation and development of 2D turbine airfoil. In order to obtain a turbine blade shape with better performance, a physical programming based multidisciplinary optimization strategy is employed. The aim of multidisciplinary optimization here is to minimize the total pressure loss as well as to maintain a good structural stress. So there must be a compromise between aerodynamic performance and structural performance. That part of work is done by physical programming method in this paper, which can get more reasonable results than traditional ones. And the optimization process studied a range of design factors including the airfoil geometry parameters, the deviation angle, and a two-dimensional k-e turbulence model. Heat transfer in a Darcy-Forcheimmer-Brinkman flow through a curved channel Mahesha Narayana, M.S. Ramaiah Institute of Technology, Bangalore, India Vishwanath Kadaba Puttanna, Jawaharlal Nehru Centre for Advanced Scientific Research, India Pradeep Ganapathi Siddheshwar , Bangalore University, Bangalore, India The paper presents the analysis of forced convective heat transfer in a flow through a curved channel filled with porous matrix using a most general model of Darcy-Forcheimmer-Brinkman. A homotopybased method is employed in order to arrive at the solution for the governing nonlinear equation with an assured convergence. Darcy and Brinkman model is recovered as a limiting case of the study. The Nusselt number is calculated for different values of the parameters involved, namely, curvature parameter, Darcy number, Brinkman number and Forcheimmer number. Axi-symmetric, Darcy-Brinkman-Forchheimer flow through an annulus Pradeep Ganapathi Siddheshwar, Ashoka Basavaraje Gowda Sangarashettahally, Bangalore University, India The nonlinear boundary value problem arising in the two-dimensional fully-developed Darcy-BrinkmanForchheimer flow through an annulus is solved numerically using a combination of finite-difference and homotopy continuation methods. The RKF45 procedure is used to solve the initial value problem arising in the homotopy method. Results of the study are compared with those obtained by the shooting method. The effect of increasing Darcy number is to flatten the velocity profile. The influence of the Brinkman and Forchheimer numbers on the velocity is not as significant as that of the Darcy number. Numerical Analysis of Aerodynamic Performance of a Aircraft Wing With Simulated Glaze Ice Accretion Aung Ko Wynn, Cao Yi Hua, Ma Cao School of Aeronautics Science and Engineering, Beijing University of Aeronautics and Astronautics, China This paper deals with the computational studies carried out on the aircraft rectangular wing with and without leading edge glaze ice accretion at subsonic Mach number conditions. The rectangular wing was extruded from a business jet GLC 305 airfoil sections with a 6 minute glaze ice 072895-05 accretion denoted as a two dimensional glaze ice shape. The aerodynamic performance degradation of lift, drag and pitching moment coefficients and pressure coefficients were evaluated. The computation were carried out at Mach number 0.3 with the Reynolds number 6.4x106 conditions to obtain the flow field around the aircraft rectangular wing with and without 6 minute glaze ice accretions. The pressure distribution over the aircraft wing with ice accretion on the angle of attack (4 and 6) degrees has also been investigated. This computational study is based on the Fluent-UNS code using the one equation Spalart-Allmaras(S-A) turbulence model and second order upwind differencing. The results show that the 3D-CFD computation can accurately predict the lift, drag and pitching moment coefficients for the aircraft rectangular wing with 6 minute glaze ice accretion. 50 SPECIAL SESSION 6. Mathematical Research in Dynamical Systems Theory Organizer: Mihai Popescu (Institute of Applied Mathematics, Bucharest, Romania) This special session is devoted to the study of a large class of dynamical systems corresponding to physical phenomena. Some of the presented problems represent mathematical researches within aerospace sciences and include studies related to stability, controllability and optimization of the analyzed phenomena. All considered problems are contributions in nonlinear dynamical system theory and applications. Risk-Sensitive Second Grade Optimal Filtering Design Maria Aracelia Alcorta-Garcia, Hector Flores Cantu, Sonia Guadalupe Anguiano-Rostro Autonomous University of Nuevo Leon, Mexico The risk-sensitive filter design problem for polynomial systems of second grade drift terms and intensity parameters multiplying diffusion terms in the state and observations equations with respect to the exponential mean-square criterion is considered for stochastic Gaussian systems. The closed form optimal filtering algorithm is obtained using quadratic value functions as solutions to the corresponding FockerPlank-Kolmogorov equation. The performance of the obtained risk-sensitive filter for stochastic second degree polynomial systems is verified in a numerical example against the optimal polynomial for second grade filter through comparing the exponential mean-square criteria values. The simulation results reveal strong advantages in favor of the designed risk-sensitive algorithm for all values of the intensity parameters. Risk-Sensitive Third Grade Optimal Filtering Design Maria Aracelia Alcorta-Garcia, Hector Raymundo Flores-Cantu, Mauricio Torres Torres Autonomous University of Nuevo Leon, Mexico The risk-sensitive filter design problem with respect to the exponential mean-square criterion is considered for stochastic Gaussian systems with polynomial of third grade drift terms and intensity parameters multiplying diffusion terms in the state and observations equations. The closed-form optimal filtering algorithm is obtained using quadratic value functions as solutions to the corresponding Focker-PlankKolmogorov equation. The performance of the obtained risk-sensitive filter for stochastic third degree polynomial systems is verified in an numerical example against the optimal polynomial for third grade filter through comparing the exponential mean-square criteria values. The simulation results reveal strong advantages in favor of the designed risk-sensitive algorithm for large values of the intensity parameters. Three-dimensional effects on rotor blade sections in stall Vladimir Cardos, Horia Dumitrescu Institute of Statistics and Applied Mathematics, Bucharest, Romania Most aerodynamic design tools for wind energy converters are based on the blade element-momentum theory. Due to the nature of this theory, the design tools need 2D steady sectional lift and drag curves as an input. In practice, flow over a wind turbine rotor blade is neither two-dimensional nor steady, and is affected by rotation. Pioneering experiments have identified a consequence: at inboard rotor blade sections stall is delayed. This so-called Himmelskamp effect gives a longer lift than predicted, and, as a result, a higher power and loading than expected. Consequently, an aerodynamic analysis tool is needed to predict sectional lift and drag under rotating conditions. In this paper, development and validation of such a tool is described, with the wind turbine application in mind. Non-linear Inverse Dynamics Control of the Smart Column with Support Excitation S. Ahmad Fazelzadeh, E. Azadi, M. Azadi Shiraz University, Iran In this paper, the non-linear vibrations of a smart column carrying the tip mass under support excitation when a pair of piezoelectric layers is attached are controlled. The column is subjected to a support motion, with one end fixed and the other end has an effect on a concentrated mass. The governing equations, which 51 are based on classical beam theory, include the large deformation nonlinearity. Moreover, the analysis is based on the generalized function theory and Lagrange-Rayleigh-Ritz technique. The inverse dynamics control is used to suppress the vibrations of the column under lateral excitation. The mathematical modeling of the column with control algorithm is derived and in purpose to study the effects of the amount of tip mass, size and location of the piezoelectric layers and the type of the support excitation on the column vibrations, the system is simulated. The performance of the nonlinear control system is examined. Also, the numerical results are shown that the vibration of the column is suppressed for each condition. Unsteady free-wake vortex particle model for prediction of the aerodynamic loads of HAWT rotor blades Florin Frunzulica, Politehnica University of Bucharest, Faculty of Aerospace Engineering, Romania Alexandru Dumitrache, Institute of Statistics and Applied Mathematics, Bucharest, Romania Horia Dumitrescu, Institute of Statistics and Applied Mathematics, Bucharest, Romania Vladimir Cardos, Institute of Statistics and Applied Mathematics, Bucharest, Romania In the design of horizontal axis wind turbines (HAWT) one problem is to determine the aeroelastic behaviour of the rotor blades for the various wind inflow conditions. A step in this process is to predict with accuracy the aerodynamic loads on the blades. The Vortex Lattice Method (VLM) provides a transparent investigation concerning the role of various physical parameters which influence the aerodynamic problem. A major problem encountered in the numerical simulation of the threedimensional incompressible inviscid flows is the expensive computation effort to specify the wake location and its influence. In this paper we present a method for the calculation of the non-uniform induced downwash of a HAWT rotor using the vortex ring model for the lifting surface coupled with an unsteady free-wake vortex particle model. Comparative studies between results obtained with different models of wake for a generic HAWT are presented. Computational Methods for Panel Flutter Analysis Florin Frunzulica, Politehnica University of Bucharest, Faculty of Aerospace Engineering, Romania Marius Stoia-Djeska, Politehnica University of Bucharest, Faculty of Aerospace Engineering, Romania Alexandru Dumitrache, Institute of Statistics and Applied Mathematics, Bucharest, Romania The panel flutter phenomenon is a self-excited oscillation of a thin shell exposed to high speed flow. From an engineering point of view, the panel flutter analysis is performed using frequency and/or time domain computational techniques. This paper is concerned with the evaluation of three different approaches for the numerical analysis of the panel flutter phenomenon. The structural model is based on the finite element discretization and is assumed to be linear, while the aerodynamic model can be linear or nonlinear. A large number of numerical results are presented for supersonic flows over a rectangular metallic shell. The predictions provided by the three methods are used for the analysis of the influence of the simplified piston theory, coupling algorithms and time steps in the panel flutter analysis. A numerical algorithm to study the propagation of elastic plastic waves in bars Olga Martin, Romania The action of loads suddenly applied to a body is not propagated instantaneously but is transmitted from one particle to another in a wave-like manner. In this paper, we study the impact loading of semi-infinite prismatic bars using a numerical algorithm based on the finite element method (FEM) and finite-differences method (FDM). A detailed analysis of the calculus errors is made and a theorem concerning the approximations is proved. The numerical example confirms the efficiency of the proposed method. 52 Optimal Transfer Trajectories from Lagrangian Collinear Points Mihai Popescu, Institute of Applied Mathematics, Bucharest, Romania The present paper illustrates the study of transferring the space vehicle from the collinear libration points of the Earth-Moon system to the maximum distance assuming that the evolution time is given. After the analysis of the admissible states, the optimal control which represents the absolute extremum in a class of relative extremum is determined. Studies for type-II and type-III intermittencies Ezequiel del Rio, Universidad Politecnica de Madrid, Spain Sergio Elaskar , CONICET - Universidad Nacional de Cordoba, Argentina Jose Manuel Donoso, Universidad Politecnica de Madrid, Spain We have proposed a new method to evaluate the reinjection probability function for type-II and type-III intermittencies [1]. The new reinjection probability density (RPD) has been observed in the broad class of maps as we have checked by numerical simulations and analytical studies. For type-II intermittency, we have presented a new one-parameter family of functions describing the reinjection probability. It has been proved that the usual uniform reinjection is a particular case of our RPD. We have also found a new expression for the RPD in type-III intermittency by extending the analysis used for type-II intermittency. For the type-III case, a new two-parameters family of RPD has been found from which one can be derive the lower bound of reinjection (LBR). Using the news RPD we have also derived the densities of the laminar phase lengths and the new characteristic relations. [1] Ezequiel del Rio and Sergio Elaskar - New Characteristic Relations in Type-II Intermittency. International Journal of Bifurcation and Chaos. Vol. 20 April (2010) Biparametric investigation of the general standard map: multistability and crises Priscilla Andressa de Sousa Silva, Maisa de Oliveira Terra Instituto Tecnologico de Aeronautica, Brazil We investigate global bifurcations in the phase space of a biparametric two-dimensional map, the standard map, derived from a model for the periodically kicked mechanical rotor. This mathematical model presents a wide assortment of dynamical phenomena, being an adequate paradigm for studying several fundamental features such as multistability, crises, and chaotic transients. Starting with the conservative case of the map, we illustrate the mechanisms of creation, merging and destruction of typical chaotic attractors, as dissipation builds up. Through the characterization of an interior, a merging and a boundary crisis, we study the crucial role played by important invariant structures, such as unstable periodic orbits and their invariant manifolds, in the mechanisms by which the phase space is globally transformed. Also, special attention is payed to the effects of the dissipative and the forcing parameters in the feature of multistability. Stability Study of Constrained Systems Ion Stroe, Politehnica University of Bucharest, Romania A new method for systems’ stability analysis is presented. This method is called weight functions method and it replaces the problem of finding a Liapunov function with a problem of finding a number of functions (weight functions) equal to the number of first order differential equations describing the system. It is known that there are no general methods for finding Liapunov functions. The weight functions method is simpler than the classical method since one function at a time has to be found. This methods conditions of solution stability and holonomic systems with dependent variables are analyzed. Also, applications such as the Lurie-Postnikov problem, stability of the rotational motion of a rigid body, the rigid body command stabilization are presented. 53 Homogenization Results for a Wave Equation with Interior and Boundary Damping Claudia Timofte, Faculty of Physics, University of Bucharest, Romania The asymptotic behavior of the solution of a singularly perturbed wave equation with dynamic boundary conditions in a periodically perforated medium is analyzed. We consider, at the microscale, an ε-periodic structure obtained by removing from a bounded connected open set Ω in Rn a number of closed subsets of characteristic size ε. As a result, we obtain an open set Ωε , which will be referred to as being the perforated domain. In this domain, we consider a wave equation, with interior sources and damping and with dynamic boundary conditions imposed on the boundaries of the perforations. Assuming suitable initial conditions, we prove that this boundary value problem is a well-posed one. This type of boundary-value problems can be encountered in the modelling of various phenomena arising, for instance, in electricity, magnetism, in the theory of elasticity, in vibrations theory or in hydrodynamics. We are interested in describing the asymptotic behavior, as the small parameter ε which characterizes the size of the perforations tends to zero, of the solution of such a problem. Using an homogenization procedure, we prove that the effective behavior of this solution is governed by a new parabolic equation, defined on the nonperforated domain Ω. Generalized Riccati equations in Banach spaces Viorica Mariela Ungureanu, Romania In this paper we consider the existence problem of some global solutions for a general class of discrete-time backward nonlinear equations defined on ordered Banach spaces. The discussed class of nonlinear equations includes as special cases many of the discrete-time Riccati equations arising both in deterministic and stochastic optimal control problems. Based on a linear matrix inequalities (LMI) approach we give necessary and sufficient conditions for the existence of the maximal solution, the stabilizing solution and respectively the minimal positive semi-definite solution of the considered discretetime backward nonlinear equations. This paper extends the results in [V. Dragan, T. Morozan, A class of discrete time generalized Riccati equations, Journal of Difference Equations and Applications, 1563-5120, 11 December 2009] and [V. M. Ungureanu, Optimal control for linear discrete-time systems with Markov perturbations in Hilbert spaces, IMA J. Math. Control Inform. 26 (2009), no. 1, 105-127]. 54 SPECIAL SESSION 7. Methods of Nonlinear Analysis for Partial Differential Equations Organizers: Eduard-Wilhelm Kirr (USA), Radu Precup (Romania) This special session will focus on methods of nonlinear functional analysis: fixed point theorems, critical point theory, upper and lower solutions method, iterative techniques etc. for partial differential equations and systems arising from the mathematical modeling in engineering, aerospace and all areas of science. Intended audience includes researchers in nonlinear analysis, partial differential equations and applied mathematics. Elementary Numerical Differential and Integral Methods to Determine the Reaction Rates of Chemical Reactions Christopher Gunaseelan Jesudason, Chemistry Department, University of Malaya, Malaysia Quantitative chemical reaction rate determination are derived mainly by linear plots of reagent concentration terms or its logarithm (depending on the order) against time with initial concentration specified, which is experimentally challenging. By definition, the rate constant is an invariant quantity and the kinetic equations follow this assumption. Different schemes have been used to circumvent specifying initial concentrations. Here, the differential method focuses on the gradient which provides a sensitive measure of the rate constant that does not require specification of initial concentrations and the results are compared with those derived from standard methodologies from an actual chemical reaction and one simulated ideally. It is shown that the method is feasible. We verify experimentally our previous theoretical conclusion based on simulation data [J. Math. Chem. 43 (2008) 976-1023] that the so called rate constant is never constant even for elementary reactions and that all the rate laws and experimental determinations to date are actually averaged quantities over the reaction pathway. The integral approach is also developed and proved feasible. It is concluded that elementary nonlinear methods in conjunction with experiments could play a crucial role in extracting information of various kinetic parameters. Bifurcations of Nonlinear Bound-States in Schroedinger type equations Eduard-Wilhelm Kirr , University of Illinois at Urbana-Champaign, USA I will discuss recent results on existence, bifurcations and stability of periodic in time, localized in space solutions (bound-states) of nonlinear Schroedinger equation. They form curves in certain Sobolev spaces parametrized by their period. It turns out that, under generic assumptions, the curves bifurcate leading to changes in both the spatial shape of the bound-states (symmetry-breaking) and in their dynamical stability. I will identify and classify the bifurcations and their effect on the dynamical stability of the solutions. This is joint work with D. Pelinovski, P. Kevrekidis and V. Natarajan. Stability for fluid structure interaction models with non-linear dissipation at the interface Roberto Triggiani , University of Virginia, Mathematics Department, USA We consider an established fluid structure interaction: a structure (the hyperbolic dynamic system of elasticity) is immersed in a fluid (the minearized navier-Stokes equation) with coupling at the interface between the two media. The original system is at best sytrongly stable mod a one-dimensional factor space, under favorable geometrical conditions of the structure (the sphere is excluded). We then introduce a dissipative term at the boundary interface: the linear system is uniformly stable under no geometrical conditions and so is the non-linear boundary case. We follow via the linear theory into the LasieckaTataru’s approach in the non linear case. Joint work with G. Avalos and I. Lasiecka. 55 SPECIAL SESSION 8. Advances in Fractional Differential Equations Organizers: Gisèle M. Mophou (Guadeloupe, France), Gaston M. NGuérékata (USA) This session is devoted to the qualitative theory of fractional differential equations and its applications to science and engineering. Main focus includes existence theorems, controllability as well as long term behavior of solutions of such equations and related numerical problems. Fractional differential equations with piecewise constant argument deviations William Edmond Dimbour , Guadaloupe, France Fractional differential equations of advanced type with piecewise constant argument deviations are studied. The fractional time derivative is considered in Caputo sense. Existence, uniqueness, stability of solutions of these equations are proved. New results on fractional differential and integrodifferential equations in Banach spaces Jin Liang , China We are concerned with the existence and uniqueness of solutions to fractional differential and integrodifferential equations in Banach spaces. New existence and uniqueness theorems are obtained by fixed point theorems and monotone iterative techniques. Some examples are given to illustrate our abstract results. Optimal control of a class of fractional diffusion equation Gisèle Mophou, Université des Antilles et de la Guyane, Guadaloupe, France In this paper we apply the classical control theory to a fractional diffusion equation in a bounded domain. The fractional time derivative is considered in Riemann-Liouville sense. We first study the existence and the uniqueness of the solution of the fractional diffusion equation in a Hilbert space. Then interpreting the Euler-Lagrange first order optimality condition with an adjoint problem defined by means of Weyl fractional integral type, we obtain an optimality system for the optimal control. Existence and uniqueness of mild solution for fractional integro-differential equations Gaston Mandata NGuérékata, Morgan State University, Baltimore, USA Fang Li , Yunnan Normal University, China In this paper, we study the existence and uniqueness of mild solution to a class of some nonlinear fractional integro-differential equations in a Banach space. We present an application to the abstract results. Pseudo-almost automorphic solutions to a class of semilinear fractional equations Marcos Rabelo, Universidade Federal de Pernambuco, Brazil We study pseudo-almost automorphic (mild) solutions of the semilinear fractional equation ∂tα u = Au + ∂tα−1 f (·, u), 1<α<2, considered in a Banach space X, where A is a linear operator of sectorial type ω < 0. Pseudo almost periodic and pseudo almost automorphic functions and their applications to abstract fractional differential equations Ti-Jun Xiao, China Examples are given to show that the decomposition of weighted pseudo almost periodic function is not unique for certain ρ ∈ U∞ . Some basic properties of weighted pseudo almost periodic functions and pseudo almost automorphic functions are presented. Moreover, an new existence and uniqueness theorem of pseudo almost automorphic solutions to abstract fractional differential equations is obtained. 56 SPECIAL SESSION 9. Petri Nets for Complex Systems Organizer: Joslaine Jeske de Freitas (Universidade Federal de Goias, Campus Jataı́, Brazil) Petri nets have graphical representation and are easy to learn. Their use makes it possible to describe the static and dynamic aspects of the system with the necessary mathematical formalism. This session is devoted to present the use of formal models based on Petri nets for modeling, simulation and validation of complex systems. Intelligent Building - Modeling and Reconfiguration using Petri Net and Holons Julio Arakaki , Pontificia Universidade Católica de Sao Paulo, Brazil Diolino Jose dos Santos Filho, Fabricio Junqueira, Paulo Eigi Miyagi University of Sao Paulo, Brazil The evolution of technology has increased the complexity of intelligent buildings environments. This paper proposes a procedure for the modeling of control systems in intelligent buildings (IB). The proposed procedure adopts the concept of Discrete Event System (DES), Holon, and Petri net and its extensions to describe the structure and the operation of control systems in IB. The procedure focuses on the FTCS (Fault-Tolerant Control Systems) requirements, with special attention on the system reconfiguration. The approach adopted in the modeling process is based on Petri net. The holons can be physical (chiller, sprinkler, PLC, etc.) or logical components (service, order, etc.). The interactions between holons are described using Petri net. The mechanism adopted to implement control architecture enables it to be hierarchical or heterarchical, and react to faults in a more agile way. This work involves the edition, simulation and validation of Petri net models. From the valid models it is possible to derive the specification of programs that should be executed in PCs (programmable controllers) and supervisory systems. Collaborative Control Model for Multifunctional Machine Tools Environment Osvaldo Luis Asato, Diolino Jose dos Santos Filho, Fabricio Junqueira, Paulo Eigi Miyagi University of Sao Paulo, Brazil In general, Manufacturing Systems (MS) are composed by a set of resources and can execute a set of processes. According to these processes the control system of the MS realizes the allocation of the transformation resources (e.g., machines) to execute the activities. In order to assure the global efficiency of production systems with multiple processes strongly connected that share a set of resources, it is essential to apply the concept of lean manufacturing to avoid machine idles. However, when the MS is composed by several multifunctional machine tools, there is a new level of control that needs to be handled: the functionality of the machines. The purpose of this paper is to present a control system of MS compatible with this behavior. The contributions can be synthesized as the improvement of the control system with a new architecture based on Petri net models that is capable to deal with a partition between the resource allocation and the functionality allocation, i.e. the functionality of the multifunctional machines can be controlled dynamically. A model to represent human behavior in workflow management systems Joslaine Cristina Jeske de Freitas, Universidade Federal de Goias, Campus Jataı́, Brazil Stephane Julia, Universidade Federal de Uberlandia, Brazil Robert Valette, Laboratoire dAnalyse et dArchitecture des Systèmes, Toulouse, France Currently, the need to represent the information needs is essential. One of the great difficulties that exist is to represent human behavior when it comes to Workflow. The purpose of Workflow Management Systems is to execute Workflow Processes. Workflow Processes represent the sequence of activities that have to be executed within an organization to treat specific cases and to reach a well-defined goal. Of all notations used for modeling Workflow Processes, Petri Nets are the most appropriate. Moreover, Petri nets can be used for specifying the real time characteristics of Workflow Management Systems (in the time Petri net case) and resource allocation mechanisms. The aim of this paper is to present a model of human resource allocation based on Petri nets to workflow management systems. 57 Distributed modelling and simulation of complex systems using Petri net Fabrı́cio Junqueira, Cristiano da Silva Costa, Diolino José dos Santos Filho, Paulo Eigi Miyagi Departamento de Eng. Mecatrônica e de Sistemas Mecánicos da EPUSP, Brazil The man-made systems are becoming more complex. This is due to changes in productive systems, such as the adoption of different technologies (heterogeneous components and subsystems), and even for more interaction between companies. Consequently, the productive systems are becoming more susceptible to errors of projects. For this, models and simulation techniques can be used to minimize the chances of error. In particular, modelling and simulation distributed stand out. It deals with the execution of simulation in physically dispersed computers connected through a network. It allows different teams to work simultaneously on the system being modelled and the use of multiple computers can reduce the simulation time. In this context, this paper presents a method for distributed modelling using Petri net. To illustrate the method, this is applied to model systems of a conventional submarine. A Hybrid Method to Generate Control Algorithms for Complex Systems Francisco Yastami Nakamoto, Diolino José dos Santos Filho, Fabrı́cio Junqueira, Paulo Eigi Miyagi Departamento de Eng. Mecatrônica e de Sistemas Mecánicos da EPUSP, Brazil Access to intelligent technology of sensors and actuators, monitoring, control and communication in industrial environments contributed to a significant increase of the demand for complex automation and control. Concomitantly, the presence of more efficient and effective computational resources promotes new technologies and new methodologies for systems control project . The basis of the convergence of factors for a common point of view is the integration, flexibility and reuse of the elements that make up the system, i.e. hardware and software. This will only be possible if there are availability and access to standards and procedures. In this context, the IEC 61499 standard has provided subsidies that guide the project to develop control of production systems with emphasis on modularization, i.e. the botton-up approach. However, the first challenge in the modeling process of such systems is the understanding, definition and sequencing of activities of the global processes that the system should control. Thus, the aim of this paper is to present a hybrid method based on global and local state representation to generating the control algorithm, represented by a derivative of the Petri net through the use of graphical tools for modeling. Scheduling Heuristic based on Time Windows for Service-oriented Architecture Marcosiris Amorim de Oliveira Pessoa, University of Sao Paulo, Brazil Diolino Jose dos Santos Filho, University of Sao Paulo, Brazil Jose Isidro Garcia Melo, Universidad del Valle Cali, Colombia Fabricio Junqueira, University of Sao Paulo, Brazil Paulo Eigi Miyagi , University of Sao Paulo, Brazil Nowadays the global economic markets have an intense world-wide competition. The modern manufacturing enterprises are dispersed in a world-wide area. In this context, the enterprises are more geographic dispersed and the productive activities could need the global distributed productive systems. Hence, there are some new requirements for production scheduling in this distributed productive systems. The distributed productive systems could be developed in Service-Oriented Architecture (SOA). The SOA has become a technologic unifying architecture for the integration of distributed software systems witch disparate software components using Internet Protocols. The web service composition is highly important for the development in service-oriented architecture. In this way, the Business Process Execution Language for Web Services (BPEL) is becoming the industrial standard for modeling the web-service. This paper proposes a scheduling heuristic based in Time Windows to attend the new requirements of the distributed systems and a procedure for modeling and analysis the results of the scheduling heuristic in this new distributed context. For modeling the distributed productive systems was characterized as a discrete event dynamic system. The procedure uses techniques derived from Petri net to mapping the BPEL process definition and to perform the modeling. 58 Control Algorithms Partition Method for Distributed Control Systems Diolino Jose dos Santos Filho, Andre Cesar Martins Cavalheiro University of Sao Paulo, Brazil The evolution of control devices and the Software Engineering techniques increase the flexibility, autonomy and reliability of control systems. As result, new programmable controllers need to be considered, taking into account aspects such as capacity and processing speed as well as communication functions according to IEC 61499. In this context, the challenge is to specify a distributed control system for Manufacturing Systems composed by a set of autonomous resources (logical and physical dispersed) that are able to execute great number of different processes, simultaneously. In this way, the control strategy cannot be concentrated in a single device, i.e., it must be distributed in different controllers. Currently, the software engineering has been contributing with new approaches to systematize the control algorithms development. In this work a method to specify an efficient distributed control architecture is proposed: Petri net is applied to structure the internal organization of programmable controller programs and function blocks; the control algorithms is partitioned using techniques derived from operational research to arrive at optimal or near-optimal solutions according to the specification of the controllers architecture that can be used. This proposal is supported by IEC 61131-3 and IEC 61499 standards. Safety Instrumented Systems Design Based on Bayesian network and Petri net Reinaldo Squillante Junior , University of Sao Paulo, Brazil Diolino Jose dos Santos Filho, University of Sao Paulo, Brazil Jose Isidro Garcia Melo, Universidad del Valle Cali, Colombia Fabricio Junqueira, University of Sao Paulo, Brazil Paulo Eigi Miyagi , University of Sao Paulo, Brazil Actually, Safety Instrumented Systems (SIS) are designed to prevent and / or mitigate accidents, avoiding undesirable high potential risk scenarios and saving costs and protecting health of people, environment and equipments. It demands formal methods to assure the safety specifications. In this sense, this paper introduces a methodology for modeling diagnostic and treatment of critical faults using Bayesian networks (BN) and Petri nets (PN) respectively. This approach considers some critical faults got from hazard and operability (HAZOP) study in the equipment or system under control and define each safety instrumented function (SIF) as well determine the safety instrumented level (SIL) by each SIF. The present approach uses Bayesian networks (BN) for diagnoses and decision-making proposes, and the Petri nets (PN) for the synthesis, modeling and control proposes implemented by Safety PLC to prevent and / or mitigate accidents. A case study considering diagnostic and treatment of critical faults is presented. Simulation of Industrial Metabolism using Predicate Transition Petri Nets combined with Differential Equations Liliane Nascimento Vale, Universidade Federal de Goias, Brazil Stéphane Julia, Universidade Federal de Uberlandia, Brazil Núbia Rosa Silva, Universidade Federal de Uberlandia, Brazil Márcio Souza Dias, Universidade Federal de Goias, Brazil The goal of our work is to propose an approach based on modeling for the study of industrial metabolism, improving the metabolic flows of industrial processes and the appropriate use of materials. The industrial metabolism is characterized as a result of physical and chemical transformations to convert raw materials into manufactured products. We begin by using an ordinary Petri net model to show the main activities and different routes that make up an industrial metabolism. After this, we present a hybrid model using predicate transition Petri nets. These nets are combined with systems of differential equations for the allocation of resources such as industrial equipment, and quantity of materials to be used. A predicate transition Petri net with differential equations allows combining continuous and discrete aspects in a single model. Continuous part represents a set of differential equations which indicates, the quantity of resources (raw materials) to be used, maximizing production. Discrete part is indicated by the predicate transition Petri net where industrial activity for the production of a certain product is represented. Finally, it is presented a case study including hybrid modeling and simulations in the Java programming language for the analysis and validation of industrial metabolism modeling. 59 SPECIAL SESSION 10. System Identification: Theory and Application in Aerospace, Biology, Engineering and Science Organizer: Sunil Kukreja (NASA Dryden Flight Research Center, USA) This special session is devoted to the theory, development of novel algorithms and applications to a wide range of unique problems in aerospace, biology, engineering and science. The papers presented in this session will introduce innovative techniques for unsolved problems in system identification and applications to ongoing research problems in industry, government laboratories and universities. Global nonlinear system identification using multivariate splines Cornelis de Visser , Delft University of Technology, The Netherlands The ability to identify accurate global models of complex nonlinear systems is highly desired in many fields of science and engineering. We present a powerful new method for global nonlinear model identification based on a recent type of multivariate spline, the multivariate simplex spline. Multivariate simplex splines are defined on non-rectangular domains and can be used to accurately fit scattered nonlinear datasets in any number of dimensions. The simplex splines consist of piecewise defined, ordinary multivariate polynomials with a predefined continuity between neighboring polynomial pieces. A new linear regression model for the simplex splines was developed. This regression scheme allows for the use of standard parameter estimators, like generalized least squares and maximum likelihood estimators, for the estimation of the polynomial coefficients of the splines. The new identification method was used to estimate a global 5-dimensional aerodynamic model for the aerodynamic force and moment coefficients of the F-16 fighter aircraft based on a NASA wind tunnel dataset. The multivariate simplex spline based aerodynamic model was validated and integrated in a non-linear F-16 simulator. A Fuzzy Neural Network for Emitter Identification Mohamad Hoseinyar, Mostafa Lotfi Forushani , Iran In this article, a new effort is done to decrease the emitter identification (EID) procedure based on a multilayer vector neural network (VNN) and Fuzzy Logic via a supervised learning algorithm along with more comprehensive input parameters of the received signal in a real-time manner. As a matter of fact, we define a new Pulse Descriptor Word (PDW) used for modern RWRs (Radar Warning Receivers) and provide the signal recognition pattern using simultaneously processing parameters encompassing Career Frequency (CF), Pulse Repetition Frequency (PRF), Pulse-Width (PW), Pulse Amplitude (PA), Angle of Arrival (AOA), Transmitter Power (TP) and Antenna Scan Rate (ASC). The input parameters are ranked via applicable values so as to prioritize the learning algorithm of the VNN; consequently, the processing time would decrease to a certain extent compared to the same approaches and more reliable results in coping with the problem of multi-threats ambiguity are gained. Robust nonlinear estimation in case of noises of unknown statistics Endre Nagy , Japan The paper presents two different methods for nonlinear robust estimation. The frame of the estimation in both cases is nonlinear regression; however, they differ in the form of applied prediction: in one of the cases prediction is performed through optimum estimation of past noises, in the other case through the concept multi intersample linearization. To avoid consequences of model errors and not expected large noises, robust estimator design is desirable. The paper first deals with the problem of design of non - robust estimators in case of noises of unknown statistics, then it shows how to make them robust. When prediction is made through optimum noise estimation, a particular problem is the great number of variables to determine. As a rule a long horizon is desirable, but the number of variables increases linearly with extension of the horizon. However, when the dynamic optimization method optimized stochastic trajectory / output sequence tracking is used, only the noise and state components at the bottom of horizon and the parameter values for parameter estimation have to be considered as independent variables; the others may be computed from optimization. The estimated noise components will be the ones, which best fit the process, i.e. the ones at the values of which a suitable performance index has 60 its minimum. In case of applying the principle multi intersample linearization, nonlinear evolution of states between sampling instants is followed in linear increments, computed with linear equations. The nonlinear parameter estimator gives the value of estimated states, too, together with the parameter estimates. Several methods are presented in the paper for robustification. Use of subjective analysis in flight safety analysis József Rohács, Budapest University of Technology and Economics, Hungary Vladimir Alexandrovich Kasaynov , Kiev Aviation University, Ukraine The central deterministic element of the aircraft conventional control systems is a subject that is an operator - pilot. Such systems are called as active endogenous systems. The pilots make decision on control depending on their situation awareness, knowledge, practice and skills. The pilots must make decisions in situations characterized by a lack of information, human robust behaviors and their individual possibilities. So, the decisions origin from analysis of pilot-subjects or subjective analysis. Safety of aircraft control can be characterized with use of subjective analysis together the aircraft motion models. The general model of solving the control problems includes the passive (information, energy like aircraft control system in its physical form) and active (physical, intellectual, psychophysiology, etc. behaviors of subjects) resources. The decision making is the right choosing the required results giving the best (effectively, safety, etc.) solutions. The proposed lecture investigates the flight safety with using the subjective analysis. There are used the statistical hypotheses and a special chaotic attractor, namely a modified Loraenz attractor. This lecture gives some results of the national and EU projects, as SafeFly and PPLANE and describe new models for investigation of the less-skilled pilots aspects. CFD assisted analysis of Propeller theories P.S. Sathish Krishnan, India In this study, various propeller theories such as momentum theory, blade element theory (BET) and the combined blade element-momentum theories (BEMT) are compared for finding the performance parameters of an aircraft propeller operating at subsonic regime. The lift and drag coefficients of propeller airfoil sections are computed and validated against a standard airfoil. An analysis to check the independency of the airfoil grid density and different turbulence models available in the CFD software are also done. Panel method is used to find the drag coefficient, whereas, Reynolds-averaged NavierStokes (RANS) equations are used to find the lift coefficient of the airfoil, due to better accuracies. The results of the propeller sections are finally integrated to get the performance of the entire propeller, after considering the tip loss factor. The computed results are then compared with the experimental results. A special condition of propeller undergoing yawed inflow condition has also been analyzed through propeller theories. Frequency response analysis of an aircraft shell panel subject to geometrical imperfections and material properties variations, using a stochastic finite element approach Francisco Scinocca, Airton Nabarrete ITA - Instituto Tecnológico de Aeronáutica, Brazil Frequency response analysis of an aircraft shell panel subject to geometrical imperfections and material properties using a probabilistic approach was evaluated. A stochastic finite element model was developed and implemented applying the Monte Carlo method to perform several spectral distributions and obtaining non-deterministic results. This work extends previous results obtained with the buckling instability analysis for an aircraft plate panel. In this research, the investigation considers the variations for shell panel geometry and material properties. In order to observe the major contributors, a sensitivity analysis was performed. The modal results and the frequency response function variations are presented. 61 FPGA Implementation of LMS-Based System Identification Core Omid Sharifi Tehrani, Ebrahim Hosseini, Mohsen Ashourian Islamic Azad University of Majlesi, Isfahan, Iran A synthesizable FPGA-based system identification core is proposed. Adaptive filters are widely used in different applications such as adaptive noise cancelation, prediction, equalization, inverse modeling and system identification. FIR adaptive filters are mostly used because of their low computation costs and their linear phase. Least mean squared algorithm (LMS) is used to train FIR adaptive filter weights. Advances in semiconductor technology especially in digital signal processors (DSP) and field programmable gate arrays (FPGA) with hundreds of mega hertz in speed, will allow digital designers to embed essential digital signal processing units in small chips. But designing a synthesizable core on an FPGA is not always as simple as DSP chips due to complexity and limitations of FPGAs. In this paper we design a LMS-based FIR adaptive filter for system identification based on VHDL97 hardware description language (HDL) and Xilinx SPARTAN3E (XC3S500E) which utilizes low resources and is high performance and FPGA-brand independent so can be implemented on different FPGA brands (Xilinx, ALTERA, ACTEL). Simulations are done in MODELSIM and MATLAB and implementation is done with Xilinx ISE. Finally, results are compared with otherpapers for better judgment. System Identification using Interval Analysis Erik-Jan van Kampen, Qi-Ping Chu, Bob Mulder Delft University of Technology, The Netherlands Interval analysis deals with interval numbers, which are an extension of the regular numbers. numbers have their own set of arithmetic rules and operations, which are derived from the inclusion theorem. Interval analysis was initially introduced in the 1960s for investigation propagation in dynamical systems. Later, it was shown that interval analysis is an excellent solving global nonlinear optimization problems. Interval interval of error tool for In this paper the application of interval analysis for system identification in aerospace applications is presented. System identification methods often rely on minimization of possibly nonlinear cost functions and interval analysis can guarantee to find the global minimum of a cost function, thereby guaranteeing the optimal identification of the system parameters. Two aerospace related applications of interval identification are presented in this paper: firstly the identification of the parameters in a multimodal human pilot perception model (visual and vestibular), and secondly the identification of all trim points for a generic nonlinear aircraft model. For both applications the interval identification method produces better estimates of the parameters than the conventional gradient-based methods, which can get stuck in a local optimum. It can be concluded that interval analysis is a promising tool for system identification. Damping identification in a non-linear aeroelastic structure Gareth A. Vio, UK The study of nonlinearity in aircraft is increasingly becoming a necessity. The main driver behind the research is the fact that nonlinear aeroelastic systems display dynamic behaviour that cannot be modelled or predicted using linear methods. One area that has not received much attention is the field damping identification. Damping is present in every vibrating structure: a portion of the energy input by external forces is always dissipated by damping mechanisms. The common and simplest approach to identify damping in large degree-of-freedom systems is linear viscous damping. However, this approach is usually chosen for its mathematical convenience and can represent a valid approximation especially when damping is considered to be small. In this paper an energy-based method is proposed to identify damping parameters from time histories of responses to sets of single-frequency harmonic excitation. The method is intended to be practically applicable to real structures and is able to identify the spatial location and value of damping. It will be shown that if the system is undergoing Limit Cycle Oscillations, no external force is required for the identification process. There is no need to know or to evaluate the mass and stiffness matrices. Spatial incompleteness can be successfully overcome by modal expansion of the measurements and modal 62 incompleteness does not affect the method in the range of interest. The spatial expansion may be avoided if the locations of the main damping energy sinks are known. Steady State Problems in Financial Option Pricing Dejun Xie, Jinan University, China This paper considers a financial contract where the borrower makes a continuous payment to the lender at each moment when the contract is in effect. We study the optimal financial decision from the borrower’s point of view when he has the choice of early settlement of debt and when alternative market investment is available. Assume market interest follows the CIR model, an infinite horizon problem is formulated with an unknown optimal early settlement interest rate to be determined together with the contract values at all interest rate levels. The well posedness of the problem is established. The analytical solution to the problem is obtained using variational method. Finally, a finite element scheme is designed for finding numerical solutions. Flutter Prediction Analysis using Output Only Flight Test Jie Zeng , Zona Technology Inc., USA Sunil L. Kukreja, NASA Dryden Flight Research Center, USA In this paper, a flutter boundary prediction technique for an aeroeasltic/ aeroservoelastic structure is introduced. This approach utilizes time series flight flutter test data to compute an accurate estimate of the flutter speed. The flutter boundary prediction tool discussed in this paper can be categorized into three steps. (i) A signal preprocessing technique is introduced to compute the auto power spectrum when only responses from sensors can be measured due to a strong turbulence perturbation during flight flutter test. (ii) A frequency domain system identification methodology combined with a stabilization diagram is implemented to extract elastic modes of the flexible structure. Accuracy of modes estimated in the second step directly affects the robustness of flutter prediction. (iii) A well known flutter prediction tool, the so-called Zimmerman-Weissenburger flutter margin, is used to perform flutter prediction. Application of the proposed flutter boundary prediction method to the Aeroelastic Test Wing (ATW) demonstrates that it is an efficient tool for flutter boundary prediction of aeroelastic/aseroservoelastic structures. 63 SPECIAL SESSION 11. Nuclear Power and Research Systems Modeling Organizers: Antonella Lombardi Costa, Claubia Pereira (Universidade Federal de Minas Gerais, Brazil) This special session will focus on simulation methodologies applied to Nuclear Engineering. The main topics include neutronic, thermohydraulics and safety analysis. Mathematical modelling of a system for brachytherapy Wagner Leite Araujo, Tarcisio Passos Ribeiro Campos Universidade Federal de Minas Gerais, Brazil The present article describes the prototype design of a system that helps permanent brachytherapy and a software that constitute its methodology of operation. Bractron is a system that consists of a chamber and a multi degree-of-freedom mechanical arm whose extremity holds a device designed to aid radioactive seeds implant on soft tissues. A laser device is placed under the plate that holds the template and is free to perform 2D rotation. The templates are made with a fine set of holes in which needles can be introduced. These holes draw a topologic spatial distribution on the region of the implant. Various geometrical patterns are defined for the purpose of setting up linear segments separated each other maintaining a fixed distance after implantation. The software developed assigns an orientation to the plate and the mechanical arm fixes it on the space, after adjust and calibration is done by means of a laser pointer. Moreover, the software determines the needles length. The algorithm for this proposes will be depicted. This mechanism allows the user to reproduce the implant protocol on the patient. An accurate adjustment of the seeds in the tumor region is expected with the use of this system for performing brachytherapy procedures. Design of a deuteron accelerator for a portable neutron generator Wagner Leite Araujo, Tarcisio Passos Ribeiro Campos Universidade Federal de Minas Gerais, Brazil Neutron generators based on particle accelerators offer various advantages over the others two available sources of neutrons, nuclear reactors and sealed sources of radioisotopes. As example the devices mobility and the fact that radiation can be turned off are suitable features of those generators. The basic project of a small size neutron generator includes the design of a modern and compact accelerator, a gas-control reservoir, a plasma and ion source to generate and gather the ions in a beam shape, respectively; and a target constituted of material loaded of deuterium hydrides on metal. This article explores basic concepts of the portable neutron generators. It describes an analytical modeling to the electrodes positioning in the ion extraction system in order to evaluate the maximum deuteron current. The result of the mathematical development provided some parameters to the computer simulation of the deuteron transport in the ion extraction system and inside the particle accelerator device. Results from the analytical model and the simulations are presented. As conclusion, on the final set up, the deuteron beam showed a low emissivity. Hence, experimental essays to validate the computational simulation shall be developed in the near future. Comparative study of the neutron production by spallation and fusion reactions for subcritical hybrid systems applications Graiciany P. Barros, Claubia Pereira, Maria Auxiliadora Fortini Veloso , Antonella Lombardi Costa, Patrı́cia A. L. Reis Universidade Federal de Minas Gerais, Brazil Subcritical hybrid nuclear systems consist in a sub-critical reactor core and an external neutron source for the maintenance of the fission chain. Such an external source may be either spallation or fusion reactions, which are used, respectively, in accelerators driven systems (ADS) or fusion-fission systems. In this work the MCNPX 2.6.0 code is used to evaluate the neutron production taking into account several types of targets commonly utilized in ADS. The concept of ADS combines a particle accelerator with a sub-critical reactor core. The particles of accelerator are driven on a target for the neutron production by spallation reactions. This paper provides the results regarding the neutron production by spallation reactions induced by protons with energy of 1 GeV in various targets materials. The MCNPX 2.6.0 64 code is further used in the present study for the modeling of fusion reactions that occur in sub-critical fusion-fission systems. The simulation results regarding the neutron production by spallation and fusion reactions as well, allows us to compare these two types of neutron sources for sub-critical systems. The results also enable us to verify differences between the energy spectrums of the neutrons emitted by each type of source. GB - a linking code between MCNP and ORIGEN2.1 - DEN/UFMG version Renan Cunha, Claubia Pereira, Daniel Campolina, André Cavatoni, Maria Auxiliadora Fortini Veloso Universidade Federal de Minas Gerais, Brazil The GB code is a linking code between Origen2.1 (Oak Ridge National Laboratory) and MCNP (Los Alamos National Laboratory). ORIGEN 2.1 is a deterministic code to solve Bateman equations that can determine isotopic composition balance considering a given input power. The MCNP is a general-purpose, continuous-energy, generalized-geometry, time-dependent, coupled neutron/photon/electron Monte Carlo transport code. A first version of GB code described the behavior during the burn up only to 25 isotopes. In this version, the goal is to increase this isotope amount. The results were compared with the ones obtained with the MCNPX 2.6.0 code and were very similar. Comparation between WIMSD-5B and MCNPX 2.6.0 codes simulating a PWR fuel element Clarysson A. Mello da Silva, Claubia Pereira, Maria Auxiliadora Fortini Veloso, Antonella Lombardi Costa Universidade Federal de Minas Gerais, Brazil In this work, the codes WIMSD-5B and MCNPX 2.6.0 were used to study a cycle of a PWR reactor (ANGRA II). The same geometry was configured in both codes and two fuels type were studied: (1) UO2 (2) (U-Pu-MAs)O2. It was evaluated the multiplication factor and the fuel composition at zero power and during the burnup at full power. The main goal is evaluate the results obtained using a deterministic code (WIMSD-5B) and a stochastic code (MCNPX 2.6.0). Application of Nuclear Codes WIMSD-5B and MCNPX 2.6.0 to a Qualitative Evaluation of MHR (Modular Helium Reactor) Clarysson A. Mello da Silva, Claubia Pereira, Maria Auxiliadora Fortini Veloso, Antonella Lombardi Costa Universidade Federal de Minas Gerais, Brazil Deterministic and stochastic nuclear codes have been used to simulate several reactor types around the world. The deterministic code spent short time in the simulations but have the disadvantageous of the simplification in the geometry. In the statistical codes, the geometry can be configured very detailed but it spent very time in the simulations. In this work, the deterministic code WIMSD-5B and the stochastic code MCNPX 2.6.0 were used to simulate a representative core of a Modular Helium Reactor (MHR). Two geometries (cell and cluster) were evaluated in both codes to a qualitative study. In this way, the effective multiplication factor (keff) during steady state and burnup were evaluated. Evaluation of spallation source for neutrons production by Monte Carlo methods Maurico Gilberti, Claubia Pereira, Maria Auxiliadora Fortini Veloso, Antonella Lombardi Costa, Clarysson A. Mello da Silva Universidade Federal de Minas Gerais, Brazil In the interaction of high energy protons with heavy materials and extended targets such as lead and tungsten, a high neutron fluxes is produced by bombarding target of the so-called spallation process. These neutrons can be used to drive a sub-critical nuclear assembly for energy generation and/or for the transmutation of the long-lived nuclear waste isotopes. These nuclear assemblies are referred to as accelerator driven systems (ADS). Knowledge of the neutron yield in the spallation process and an understanding of the behavior of these neutrons in the desired sub-critical nuclear assembly are the most important and determining factors in 65 the design and operation of these systems. This work uses the Los Alamos High Energy Transport Code (LAHET) into Monte Carlo code MCNPX 2.6, which allows to simulate the interaction of wide variety of particles for calculations and simulation the spallation reaction. Evaluating the cost of electric production of neutrons in the targets, flux e heat absorbed, resulting of incidence of a high energy beam protons with heavy massive materials, in energy range 200 Mev a 10 Gev. From this analysis it was possible to characterize and optimize the spallation reaction with a view to production neutrons for a sub-critical reactor. Initial Development of a Coupling Methodology between Thermal-Hydraulic and Neutron Kinetic Codes for Simulation of the IPR-R1 TRIGA Reactor Claubia Pereira, Patrı́cia A. Lima Reis, Antonella Lombardi Costa, Maria Auxiliadora Fortini Veloso, Clarysson A. Mello da Silva Universidade Federal de Minas Gerais, Brazil The TRIGA IPR-R1 research reactor is located in the Nuclear Technology Development Center (CDTN), Brazil. It is a 250 kW, light water moderated and cooled, graphite-reflected, open pool type research reactor. The development and the assessment of a RELAP5 model for the IPR-R1 TRIGA have been validated for steady state and transient situations. Giving continuity to this study this paper presents an initial idea of model for the IPR-R1 including the coupling between the RELAP5/MOD3.3 thermal hydraulic (TH) system code and the PARCS-2.4 3D neutron kinetic (NK) code. This technique consists in incorporating three-dimensional (3D) neutron modeling of the reactor core into system codes mainly to simulate transients that involve asymmetric core spatial power distributions and strong feedback effects between neutronics and reactor thermal-hydraulics. To perform such model it is necessary to supply adequate cross sections to the PARCS code. Therefore, the idea is to employ the two-dimensional (2D) transport calculations with the TRITON/NEWT module from the SCALE6 package to produce the averaged cross-section libraries as a function of fuel temperature and coolant temperature and density for PARCS calculations. The general scheme of the calculation is presented in this work. A preliminary neutronic evaluation and depletion study of HTR using WIMSD5 and MCNPX2.6.0 codes Fabiano Cardoso Silva, Claubia Pereira, Clarysson A. Mello da Silva, Maria Auxiliadora Fortini Veloso, Antonella Lombardi Costa Universidade Federal de Minas Gerais, Brazil In this study, it will be analyzed two HTR concepts, VHTR and LS-VHTR, using reprocessed fuel coming from typical PWRs. Neutronic parameters obtained using the WIMSD5, and MCNPX2.6.0 codes are evaluated and compared. The results show good agreements in BOL but presents differences during the burnup. 66 SPECIAL SESSION 12. Integral Equations and Their Applications Organizers: Luis Castro, Stefan Samko (Portugal) This section is devoted to integral equations and their applications to the areas of the general scope of the conference. Special emphasis is put in the analysis of properties of Fredholm, Volterra and singular integral equations including equations generated by Wiener-Hopf, Toeplitz, Hankel and fractional order integral operators and their various applications. Talks presenting the use of integral equations in the areas of aerodynamics, fluid mechanics and wave diffraction are especially welcomed. Fredholm-Stieltjes integral equations with (O-M)integral in time scales and applications Luciano Barbanti , UNESP, Brazil Berenice Camargo Damasceno, MAT-FEIS-UNESP-Ilha Solteira, Brazil José Manoel Balthazar , DEMAC-IGCE-UNESP-Rio Claro, Brazil Time scale calculus is a unification of the theory of difference equations and the differential equations, unifying integral and differential calculus with the calculus of finite differences, offering a formalism for studying hybrid discrete-continuous dynamical systems. Established in 1988 by S. Hilger, it has applications in any field that requires simultaneous modeling of discrete and continuous data. In the context of the time scale calculus we have the integral concerning the Riemann-Stieltjes (R-S) type, done by D.Mozyrska, E.Pawluszewicz and D.F.M.Torres in 2009. An essentially proper extension of the (R-S) one, named odd-meshed integral (O-M) was defined in 2010 by L.Barbanti, B.C.Damasceno and J.M.Balthazar in general Banach spaces. Here we introduce the Fredholm-Stieltjes integral equations in the context of the regulated functions (that is, having discontinuities only of the first kind) with operators of semi-variation that compose a dual structure when using the bilinear association (O-M). Later, results regarding periodicity and stability will be presented by using difference kind equations associated with the Fredholm-Stieltjes general ones. We conclude this work with an application of the results in the spectral concentration problem as considered by D. Slepian, in signal processing. Stability of Fredholm integral equations in the framework of generalized metric spaces Luis Castro, Universidade de Aveiro, Aveiro, Portugal Considerable attention has been recently given to the study of the Hyers-Ulam-Rassias stability of functional equations. The concept of stability for a functional equation arises when we replace the functional equation by an inequality which acts as a perturbation of the equation. Thus, the stability question of functional equations is how do the solutions of the inequality differ from those of the given functional equation. In the present talk, we will consider such question for certain Fredholm integral equations by using fixed point arguments in the framework of generalized metric spaces. In particular, conditions to ensure the Hyers-Ulam-Rassias stability of such equations will be obtained. Splitting property for singular integral operators with a weighted shift Edixon Rojas, Universidade de Aveiro, Aveiro, Portugal We use operator relations and a polynomial collocation method to obtain information about the ksplitting property and kernel dimension of singular integral operators with a weighted Carleman shift, and having piecewise continuous functions as coefficients. Due to the increasing importance of this kind of operators in numerical applications, the order of convergence of the singular values of the corresponding approximation method will be described in detail. 67 Constructions of the approximate solutions of singular integral equations by using the Tikhonov regularization and the theory of reproducing kernels Saburou Saitoh, Universidade de Aveiro, Aveiro, Portugal In this Conference, we first would like to introduce some fundamental theory for linear transforms in the framework of Hilbert spaces and its general applications with very concrete typical examples. Secondly, we introduce the construction of the approximate solutions of the equations by using the Tikhonov regularization and the theory of reproducing kernels. Thirdly, we will propose a new method that the singular integral equations may be transformed to regular and discrete integral equations. The contents will be given by the following key words: Reproducing kernel, Pythagorean theorem, inversion of the linear systems, numerical analysis, inverse problem, inverse heat conduction, observation data, discretization, noise, error estimate, generalized inverse, Tikhonov regularization, singular integral equations with shift. Integral equations of Wiener-Hopf type characterized by piecewise almost periodic elements in Lebesgue spaces with weights Anabela Silva, Universidade de Aveiro, Aveiro, Portugal The talk will be devoted to the study of operators which characterize equations of Wiener-Hopf type having so-called Fourier symbols in the algebra of piecewise almost periodic elements. A main part of the talk will be addressed to identify conditions which ensure the Fredholm property of those operators in weighted Lebesgue spaces. In addition, the Fredholm index will be discussed as well. The equations under study are known to be useful in the modelling of various applied problems. 68 MINISYMPOSIUM 1. Aeroelasticty Organizers: Jiro Nakamichi (Japan), A.V. Balakrishnan (USA), Luiz Carlos Góes (Brazil) Advanced aeroelasticity research progresses are demonstrated in this session, theoretically by CFD and experimentally by up-to-date measurement techniques. Nonlinear phenomena due to coupling between structures and aerodynamic forces are focused on in aeronautics. Other fields are also welcome, for example, mechanical engineering, civil engineering and so on. A bifurcation based approach to the analysis and control of flexible aircraft Mohamed Nadjib Baghdadi , UK Modern aircraft designs are continuously driven towards a light weight configuration due to performance and mission requirements. Consequently, these aircraft are characterised with high structural displacements resulting in a reduction of the frequency margin between rigid-body and flexible modes. Strong dynamic coupling may occur in the presence of nonlinearities and in such cases, classical analysis methods are unable to accurately identify the resulting nonlinear behaviour. In this paper, we demonstrate the effect of dynamic coupling between rigid-body, flexible and controller modes on the stability and control of flexible aircraft using a novel analysis approach based on the use of bifurcation analysis linked to classical methods. The robustness of different control law design is also demonstrated. Flutter solution techniques and their applications Eulo Antonio Balvedi Jr., Roberto Gil Annes da Silva Instituto Tecnologico de Aeronáutica, Brazil The main purpose of the flutter solution techniques is to evaluate the aeroelastic system stability by means of eigenvalue analysis. We present a comparison among the principal methods available in literature applied to a typical section airfoil. Modern aeroelastic fields, like nonlinear analysis and active control design, require the system representation in time domain. Normally, the aerodynamic forces are available only in frequency domain with implicit dependency on the reduced frequency. Thus, a series of rational functions are used to approximate airloads and the flutter solution techniques are carried out to evaluate the accuracy. Moreover, a generalization of the Roger rational function approximation is presented. Theoretically, the transcendental characteristic of the flutter equations could lead to an unlimited number of roots, in contrast to the algebraic equations. The existence and the physical meaning of these additional roots are also discussed. Transonic Aeroelasticity: Theoretical and Computational Challenges Oddvar O. Bendiksen, University of California, Los Angeles, USA Despite research extending over more than 50 years, we still do not have a good understanding of transonic flutter or other aeroelastic phenomena occurring near Mach 1. Transonic flutter prediction remains among the most challenging problems in aeroelasticity, both from a theoretical and a computational standpoint. It is also of considerable practical importance, as large subsonic transport aircraft cruise at transonic Mach numbers, and supersonic fighter aircraft must be capable of sustained operation near Mach 1, where the flutter margin often is at a minimum. In this lecture, we review unsteady transonic flow theory and combine classical results from the nonlinear asymptotic theory with new results based on computational fluid dynamics. Because transonic flows are inherently nonlinear even in the limit of small disturbances, a flutter analysis based on the classical Hopf bifurcation theory may not be able to predict all types of transonic flutter, because no uniformly valid linearization may be possible. Examples of nonclassical flutter behaviors observed in our time-marching simulations include delayed flutter and period-tripling flutter. The usefulness of transonic similarity principles in understanding flutter, divergence, and control reversal phenomena are illustrated through practical examples. Among the computational challenges, the fluid-structure coupling problem remains of central importance, and accurate and reliable flutter solutions cannot be obtained unless certain dynamic consistency conditions are met. Advances in computational methods have made it feasible to study problems with structural as well as fluid nonlinearities, and in some cases both must be considered in order to 69 obtain the correct stability behavior. Recent results for a swept transport wing show that interactions between aerodynamic and structural nonlinearities may lead to multiple limit cycles and counterintuitive flutter behaviors. For example, decreasing the dynamic pressure at a fixed Mach number may become destabilizing, and flutter then occurs at altitude rather than at sea level. Aeroelastic Behavior of a Wing with a Magnetorheological Hysteretic Model for the Damping Kleber Augusto Lisboa Castão, Technological Institute of Aeronautics, Brazil Luiz Carlos Sandoval Goes, Technological Institute of Aeronautics, Brazil José Manoel Balthazar , São Paulo State University - Campus Rio Claro This paper shows the application of a hysteretic model for the Magnetorheological Damper (MRD) placed in the plunge degree-of-freedom of aeroelastic model of a wing. This hysteretic MRD model was developed by the researchers of the French Aerospace Lab. (ONERA) and describe, with a very good precision, the hysteretic behavior of the MRD. The aeroelastic model used in this paper do not have structural nonlinearities, the only nonlinearities showed in the model, are in the unsteady flow equations and are the same proposed by Theodorsen and Wagner in yours unsteady aerodynamics theory; and the nonlinearity introduced by the hysteretic model used. The main objective of this paper is show the mathematical modeling of the problem and the equations that describes the aeroelastic response of our problem; and the gain obtained with the introduction of this hysteretic model in the equations with respect to other models that do not show this behavior, through pictures that represents the time response and Phase diagrams. These pictures are obtained using flow velocities before and after the flutter velocity. Finally, an open-loop control was made to show the effect of the MRD in the aeroelastic behavior. Dynamic responses and eigenanalysis of non-classical vibrating beams Julio R. Claeyssen, Federal University of Rio Grande do Sul, Porto Alegre, Brazil Teresa Tsukazan, Federal University of Rio Grande do Sul, Porto Alegre, Brazil Rosemaira D. Copetti , Federal University of Santa Maria, Brazil Antonio L. Bidel , Federal University of Santa Maria, Brazil Elastic beams models with no-classical and non-linearities are of importance in aeroelasticity, control, atomic force microscope and carbon nanotubes. The eigenanalysis of such beams is formulated here by using a basis generated by the initial value Green response of the corresponding modal equation. The system function and the impulse response are given in closed form. The non-linear models are approximated by using the Galerkin method. We discuss forced responses of a damped cantilever EulerBernoulli beam with an attached damper at the free end and a Timoshenko beam subject to an axial force and to an elastic append. The matrix frequency response of the beam and the distributed impulse response are approximate by using spectral matrices and time matrix functions. The dynamic response is obtained through dual integral equations that involve time convolutions with the non-linear forcing and nonhomogeneous boundary conditions. Application of Correction Methods for Aeroelastic Stability Analysis of Wing Structures in Transonic Flow Roberto Gil Annes da Silva, Ricardo Franco Amaral IAE/DCTA, Brazil In spite of the recent development in computational aeroelasticity and CFD tools for unsteady flows, most of the aeroelastic stability analyses of wing structures in the transonic regime that are performed in engineering environment still rely on the application of correction methods to the aerodynamic loadings provided by linear aerodynamic theory based codes. However, there is lack of literature on the capabilities and limitations of each method, just as on their adequacy to each wing design or physical phenomenon involved. This paper presents a study on three different correction methods (NLR method - use of local Mach number; SKEM - Successive Kernel Expansion Method; Dau-Garner method), applied to three different wing structures (PAPA supercritical wing; AGARD 445.6 weakened wing; YXX airplane wing). Correlation between theoretical predictions and experiment indicates that distinct wing designs, dominated by dissimilar physical phenomena, require the use of different methods for accurate incorporation of the dominant nonlinear features to classical aeroelastic analysis tools. 70 Aeroelastic Aircraft Landing Phase Simulation by Using Hybrid Modeling Approach S. Ahmad Fazelzadeh, Hanif Sadat Hoseini Shiraz University, Iran In this paper flight simulation of aeroelastic aircraft in landing phase is presented. Hybrid state equations of motion in terms of quasi-coordinates provide the framework for nonlinear simulation. The wings of the aircraft are assumed to be flexible and modeled as cantilever beams undergoing elastic bending and torsion about their elastic axis. Unsteady aeroelastic forces are computed using strip theory and finite state induced flow theory. An asymmetric landing condition in which the elastic aircraft encounters cross wind all the way to touchdown is considered. In order to design the landing controller, nonlinearly coupled equations of motion are linearized about trim condition and separated to two sets of decoupled equations in which the elastic variables affect lateral-directional equations. An optimal-integral-feedforward control scheme is exploited to realize the auto-landing while suppressing wind effects on flight path as well as elastic variables. The performance of the control system is examined through nonlinear simulation. Critical and post-critical study of elastic aircraft wings subjected to non-conservative loads S. Ahmad Fazelzadeh, Shiraz University, Iran Abbas Mazidi , Yazd University, Iran As a result of recent technological advances, the importance of stability investigations of elastic systems has increased considerably. The development of modern mechanical and aeronautical engineering has considerably widened the class of the load types requiring investigation. Non-conservative forces are associated with theoretically interesting and, from the practical point of view, very important problems in engineering. Of particular interest is the stability behavior of systems subject to non-conservative external forces in connection with alternative manifestations instability like divergence (static instability) or flutter (dynamic instability). Mathematically such an analysis leads to non-self-adjoint boundary value problems. In this study, the aeroelastic modeling and critical and post-critical behavior analysis of the wings hosting arbitrarily placed masses and subjected to arbitrarily placed follower forces and also, subjected to general maneuvering conditions is considered. Furthermore, discussions about the combined effects of the maneuver induced forces, external masses, and follower forces in conjunction with airflow on the critical boundary and the post critical regions is presented. Bending without normal stress case on an isotropic micropolar beam Juan Alejandro Vazquez Feijoo, CIIDIR - Oax Instituto Politecnico Nacional, Mexico Microcontinua contains the best elasticity theories for description of the behavior of certain materials used for damping purposes such as the liquid crystal polymers that possesses large damping coefficients at all operation frequencies. This is a theoretical work aimed to been able to understand better this kind of materials under the engineering point of view. Based on the isotropic micropolar constitutive equations, the problem of a beam bearing an uneven force field is solved in the elastic range. It results in a case of a beam bending without the presence of normal stresses. The beam is simple clamped, a polynomial displacement field is assumed. The force field is introduced into the constitutive equations as a microcouple per unit of volume. The flexion is produced then by a shear stress produced because of the antisymmetric shear strain that characteristic of the micropolar media. Limit Cycle Oscillations of Very Flexible High-Aspect-Ratio Wings Justin W. Jaworski , Air Force Research Laboratory, Wright-Patterson AFB, OH Earl H. Dowell , Duke University, USA A nonlinear aeroelastic analysis is performed for a flexible high-aspect ratio wing representative of high altitude long endurance (HALE) aircraft. Such aircraft are susceptible to aeroelastic response to gusts and dynamic instabilities such as flutter, which can lead to large-amplitude limit cycle oscillations. Structural motions are modeled by Hodges-Dowell beam theory, which includes leading-order nonlinear elastic coupling. Aerodynamic forces are represented by the ONERA dynamic stall model with its coefficients 71 calibrated to computational fluid dynamics (CFD) data as an alternative to wind tunnel test data. Time marching computations of the coupled nonlinear beam and ONERA system highlight a number of features relevant to the aeroelastic response of HALE aircraft, including the sensitivity of the flutter boundary and limit cycle oscillations to aerodynamic CFD or test data, and the roles of structural nonlinearity and nonlinear aerodynamic stall in the dynamic stability of high-aspect-ratio wings. Aeroservoelastic Flight Control Design For Military Aircraft Weapon System Wolfgang Luber , Germany The aim of the aeroservoelastic flight control system design for a military aircraft weapon system is mainly to optimize for a given control law forward path and feedback structure the control law parameters like gains, phase advance filters and notch filters which cover all conditions in a full flight envelope for all envisaged aircraft configurations as external missiles, stores, bombs for all possible symmetric and asymmetric combinations. The control law gains and phase advanced filters which are derived during the optimization process are considered to be Mach number and altitude dependent whereas the structure filters i. e. notch filters may be constant or variables for all flight conditions and groups of the huge number of external store configurations. The design strategy of the Flight Control System development and the procedure is described which includes the modelling of the coupled system of the flight dynamics, the structural dynamics of representative selected external stores, the actuators and sensors as well as the effects of the digital advanced flight control system. Different external store examples are demonstrated which document the design procedure. The design of FCS notch filters is based upon a model of the aircraft describing the coupled flight dynamic, flight control dynamics and in addition on the structural dynamic behaviour measured by on groundand in flight structural coupling tests of a representative number of external store configurations. The paper outlines design procedures, design and clearance requirements, correlation tests and model update for on ground and in flight. Contributions on smart structures and materials for applications on aeroelasticity and power harvesting Flávio D. Marques, Carlos De Marqui Jr., Volnei Tita School of Engineering of São Carlos, Brazil The study of Active Fiber Composites (AFC) in aerospace applications has increased due to the potential of manufacturing structures that satisfy high performance requirements needed in this area. Intelligent structures can be designed as sensors and actuators for applications such as structure health monitoring, aeroelasticity and power harvesting. A model of AFC composed of lead zirconate titanate (PZT) and polymeric matrix is studied. Numerical simulations using finite element method are presented, considering the AFC with different fiber arrangements. Piezoelectric composites can be classified into 14 types, depending on the nature of fiber distribution in the matrix, and divided in 3 groups: unimodal-periodic, bimodal-periodic or aperiodic, concerning the periodicity of fiber distribution and size of fiber crosssectional area. Simulations of relevant cases of the first group are presented. The AFC is modeled in a micro-mechanical view through Representative Volume Element, appropriately chosen for each fiber arrangement with suitable boundary conditions applied to make the unit cell provide the entire behavior of the piezoelectric composite. The material properties of each component of the composite are known, which permits to estimate the effective properties of the AFC by applying different loading cases to the unit cell. After that, the effective properties of PZT are used in aeroelasticity and power harvesting problems. 72 The influence of starting transients, aerodynamic definition and boundary conditions on elastic and viscoelastic panel and wing flutter Craig G. Merrett, Harry H. Hilton University of Illinois at Urbana-Champaign, USA In past and present elastic and viscoelastic analyses, the starting transient contributions of the deformations remain unresolved. Their important influence is due to the inherent memory and energy dissipation associated viscoelastic material behavior. While mathematically acceptable, physically simple harmonic motion (SHM), or any other function, cannot suddenly appear in their pristine states at the proverbial t = 0, nor can flight velocities instantaneously reach a finite value. The SHM is achieved in the deflection solution w(e x, t) ∼ exp (de + ı ω) when the flutter velocities and frequencies reach eigenvalues at de = 0. The SHM deflections must be preceded by a build-up during a preferably short time interval where db < 0 and V < Vf . Thus the buildup and possible short time resultant transient responses are chosen to be contained in the elastic portion of the relaxation modulus curve and no additional memory effects will be imposed on the SHM portion, provided any transient responses die out before relaxation begins. Analytical studies are undertaken to ascertain the effects on elastic and viscoelastic flutter of (1) starting transients due to changes in flight velocity, (2) boundary conditions and (3) unsteady aerodynamic force definitions. Panel flutter is considered and varied boundary condition effects are also studied. In addition to the various unsteady aerodynamic theories, the effects due to the presence of spatial deflection derivatives on pressure distributions are also examined. Necessary and sufficient conditions for the onset of flutter in the form of simple harmonic motion are also formulated and evaluated. Simulation results indicate that the inclusion of starting transients, deflection derivatives and distinct boundary conditions in the flutter analyses each produce significant increases and decreases in flutter velocities and frequencies. Reconstruction of Aerodynamic Loads Based on Inverse Analysis Toshiya Nakamura, Hirotaka Igawa Japan Aerospace Exploration Agency, Japan The data of operational load is quite useful in managing the structural integrity of an aerospace system. Identifying the aerodynamic load from finite number of measured strain data is not easy because the load distributes continuously on the structure surface which means the degree of freedom is infinity. A flexible interpolation method for continuous load distribution is proposed in the present study and the full-field continuous load is reconstructed from finite number of strain data using the conventional finite element method and pseudo-inverse matrix. The effects of measurement error are discussed where two methods of rank reduction and Tikhonov-Phillips regularization are employed to improve the accuracy of the inverse analysis. It will be shown that both two methods are effective but the determination of the proper rank and the regularization parameter are not easy. Aeroelastic Analysis of a Typical Section Using of Shape Memory Wire Actuator Vinı́cius Piccirillo, Brazil Luiz Carlos Sandoval Goes, ITA, Brazil José Manoel Balthazar , UNESP, Brazil Shape memory alloys (SMAs) provide a compact and effective actuation for a variety of mechanical systems. In this paper, a numerical simulation study of a three degree of- freedom airfoil, subjected to two-dimensional incompressible inviscid flow using a SMA is presented. SMA wire actuators are used to control the flap movement of a wing section. Through the thermo-mechanical constitutive equation of the SMA proposed by Brison, we simulate numerically the behavior of a double SMA wire actuator. Two SMA actuators are used: one to move the flap up and the other to move the flap down. Through the numerical results conducted in the present study, the behavior and characteristics of an SMA actuator with two SMA wires are shown the effectiveness of the SMA actuator. In conclusion, this paper shows the feasibility of using SMA wire actuators for flap movement, with success. 73 Research on Aileron Buzz Controling by Changing Boundary Layer Thickness Masato Tamayama, Japan Aerospace Exploration Agency, Japan Transonic unsteady aerodynamics on aileron buzz phenomenon has been studied in JAXA and some kinds of knowledge were acquired. If a shock wave oscillates on an aileron around its middle chord-wise location, the aileron acquires energy from surrounding flow and the possibility of aileron buzz occurrence will increase. As another knowledge, an existence of boundary layer on an airfoil surface influences the extent of shock wave oscillation: From the unsteady CFD simulations with forced aileron oscillation, a shock wave in an inviscid flow oscillates at more backward location than the one in a viscid flow. Inspired from these results, one idea was raised that to control boundary layer thickness around the airfoil might suppress aileron buzz occurrence. This idea has been tried by conducting CFD simulations analyzing Navier-Stokes equations. As the method to control the boundary layer thickness, air blowing and breathing from the airfoil surface are selected. The airfoil model is a two dimensional wing of NACA0003 airfoil cross-section with a 25% chord length aileron attached. In the conference, the results of these simulations will be presented. Dynamic Instability of Viscoelastic Plate in Supersonic Flow Botir Usmonov, Uzbekistan The present work is investigating the aero-elastic instability of a viscoelastic plates under compressive forces. The Bubnov-Galerkin method used to solve the governing equations. The quasi-steady aerodynamic loadings are determined using linear piston theory. The nonlinear integro-differential equation of the plate is transformed into a set of nonlinear algebraic equations through a Galerkin approach. The resulting system of the equations is analytically solved. The influence of elastic and viscoelastic properties and the compressive load characteristics of the plate material on the value of critical parameters are discussed. 74 MINISYMPOSIUM 2. Astrodynamics Organizers: Vivian Gomes, Antonio Prado (INPE, Brazil) This special session covers topics related to the orbital motion of artificial satellites, including spacecrafts that are orbiting the Earth, as well as the ones that go outside the vicinity of the Earth. The main topics include orbital maneuvers but also orbit determination and propagation, effects of perturbative forces, atittude determination and propagation, chaos and planetary motion. Escape Basins and Chaotic Saddles in the Planar Circular Restricted Three-Body Problem for the Earth-Moon System Sheila Crisley de Assis, Maisa de Oliveira Terra ITA, Brazil The goal of the present paper is to investigate the escape basins and the associated fractal invariant sets in the context of the planar circular restricted three-body problem (PCRTBP) for the earth-moon system. These exit basins and respective boundaries are intimately related with transport processes between the realms defined around each primary body, which can be important both in the context of space mission designs and in the dynamical investigation of natural systems. Given a value of the PCRTBP integral of motion, one of the five possible Hill regions (accessible regions) and respective transport channels are established. Considering an initial condition set around one of the two primaries, exits are defined according with the opened necks around the collinear equilibria. Escape basins are obtained for two cases: considering the primaries as punctual mass and treating them as finite bodies with the inclusion of their mean radii. These escape basins can reveal the existence of regular and fractal basin boundaries, associated with chaotic saddle and its invariant manifolds. The qualitative dynamical investigation through Poincare sections is performed in order to elucidate the obtained results. Artificial Satellites: Orbital Perturbations Rodolpho Vilhena de Moraes, UNESP/FEG, Brazil A brief comment about some scientific applications of artificial satellites is presented showing the necessity of precise orbital determination for the success of the mission. The main orbital perturbations: geopotential, atmospheric drag, tides, solar radiation pressure (direct and reflected), electric drag, third body perturbation, are described. Resonance’s effects are discussed. The equations describing the motion of artificial satellites are given considering conservative and nonconservative perturbations. Some original analytical solutions for the equations of motion are presented. Applications are done for real and hypothetical satellites. Orders of magnitudes for the perturbations are exhibited. Simulations show that resonance can produce important long period terms in the time variation of the orbital elements. For intervals shorter than one fourth of the period of the resonant term this could be regarded as a secular variation. Gravitational Capture under the Restricted Three-Body Problem Alexandre Lacerda Machuy Francisco, National Institute for Space Research - INPE, Brazil Antonio F.B.A. Prado, National Institute for Space Research - INPE, Brazil Teresinha de Jesus Stuchi , Universidade Federal do Rio de Janeiro, Brazil The objective of the present paper is to study the ballistic gravitational capture in a dynamical model that has the presence of three bodies. A temporary gravitational capture happens when a spacecraft (or any particle with negligible mass) changes from a hyperbolic orbit around of a heavenly body to an elliptic orbit without the use of any propulsive force in the system. The force responsible for this change in the orbit of the spacecraft is of the gravitational nature. In was made a numerical study of the gravitational capture. The mathematical model used to analyze this phenomenon is the restricted problem of three bodies. We used Neptune and Triton as the two primary bodies. This phenomenon is explained in terms of the integration of the perturbing forces with respect to time. Numerical simulations are performed to show the trajectories of the spacecraft. There are also graphs that have the purpose to obtain the 75 minimum consumption of fuel. Using extended Kalman filter and least squares method for spacecraft attitude estimation Roberta Veloso Garcia, National Institute for Space Research - INPE, Brazil Hélio Koiti Kuga, National Institute for Space Research - INPE, Brazil M.C. Zanardi , Faculdade de Engenharia de Guaratinguetá - FEG / UNESP, Brazil The purpose of this paper is to compare the attitude estimation results between the least squares method and the extended Kalman filter of an artificial satellite using real data of on-board attitude sensors. The attitude of satellite represents how the satellite is oriented in the space. The accuracy in the attitude determination impacts directly on the performance of the attitude control system and affects the interpretation of information obtained from the experimental payloads of the satellite. There are many methods to determine the attitude of a satellite. The choice of the method depends on the type of application, of the mission, and on the requirements to be satisfied, such as the real time processing and the precision. However, independent of the method chosen, a minimum set of measurements supplied by sensors on board the satellite are needed. Among estimations methods applied for nonlinear problems, two of them are traditionally picked out for attitude estimation: the least squares method and the extended Kalman filter. The first is an alternative for the estimation criterion of minimum variance, and yields instantaneous attitude determination, by processing the attitude sensors data (horizon and Sun sensors). However, the extended Kalman filter carries out the processing of such sensors measurements in real time, and its formulation accounts for the dynamic noise of the states, yielding a kinematic attitude determination, using additionally the gyro measurements. It is observed that the averages of the values of the attitude estimated by the least squares method are very close to the results for the extended Kalman filter. In this way it can be concluded that the algorithm of the extended Kalman filter converges to the least squares solution when fed with real data supplied by the attitude sensors. The FEFF Methodology for Proximity Maneuvering Spacecraft Formations Laura Garcia-Taberner , Universitat de Girona, Spain Josep J. Masdemont, Universitat Politecnica de Catalunya, Barcelona, Spain To have a robust and efficient optimal control technique avoiding possible collision risks is a main requirement in the maneuvers involving proximity of spacecrafts. In this work we develop a methodology to compute optimal reconfigurations for a formation of satellites in a given fixed time interval using a systematic approach. The FEFF methodology (Finite Elements for Formation Flight) models the trajectories of the satellites using finite elements in time. The problem is essentially set up as an optimal control problem, where the objective function is directly related to the delta-v expenditure of the satellites in their controlled trajectories. Geometry of controls depending on the orientation of the thrusters and weighted trajectories can also be considered, when for instance, fuel resources or other particular satellite conditions, are in better or worse state than in others. Once formulated, the problem is solved via a variational numerical method where collision avoidance and other types of constraints are introduced in a natural way. During the procedure mutual distances between spacecraft are checked and possible collisions are avoided. In this presentation we apply and study the costs, in terms of delta-v, of the FEFF methodology for reconfiguration of formations in the vicinity of libration points. The close approach between a planet and a cloud of particles Vivian M. Gomes, Antonio F.B.A. Prado National Institute for Space Research - INPE, Brazil The idea of the present paper is to study the swing-by maneuver between one of the planets of the Solar System and a cloud of particles. This is what happens when a fragmented comet crosses the orbit of a planet like Jupiter, Saturn, etc. We used the dynamical system that is formed by two main bodies (the Sun and one of the planets of the Solar System) and we assumed that they are in circular orbits 76 around their center of mass and a cloud of particles is moving under the gravitational attraction of these two primaries. The motion is assumed to be planar for all the particles and the dynamics given by the ”patched-conic” approximation is used, which means that a series of two-body problems are used to generate analytical equations that describe the problem. The main objective is to understand the change of the orbit of this cloud of particles after the close approach with the planet. It is assumed that all the particles that belong to the cloud have semi-major axis a ± da and eccentricity e ± de before the close approach with the planet. It is desired to known those values after the close approach. In particular, we will study the effects of the periapsis distance in this maneuver. Maneuvers control of a spacecraft through aerodynamics changes under the effects of the upper atmosphere Willer Gomes, Evandro Marconi Rocco, Valdemir Carrara National Institute for Space Research - INPE, Brazil In several missions it is necessary to perform orbital maneuvers. Aeroassisted maneuvers using atmospheric forces can be used to change the trajectory and velocity of a spacecraft. Several studies in this area have indicated that a significant fuel reduction can be achieved using aeroassisted maneuvers rather than fully propulsive maneuvers. Therefore, this allows an increase in the payload capacity of the vehicle. A spacecraft equipped with controllable aerodynamic plates have the ability to change their projected area and hence the aerodynamic forces suffered. In this context, the studies about the feasibility and efficiency of the spacecraft control system are very important. Therefore, this paper presents a simulation model which considers a closed-loop control system used to control the angle of attack of the aerodynamic plates during aeroassisted maneuver in the upper atmosphere. The proposed technique was validated through numerical simulations. The results showed the difference between the proposed maneuver and a propulsive one. Evaluation of the Fuel Consumption in Orbital Maneuvers with Time and Position Constraints Thais Carneiro Oliveira, Evandro Marconi Rocco, Antonio F.B.A. Prado National Institute for Space Research - INPE, Brazil The main goal of this work is to evaluate the total fuel consumption in a spacecraft transfer orbit procedure, using two-impulsive orbital maneuvers between elliptical orbits, with a time limit to perform the transfer, considering specifics positions on the initial and final orbits to start and finish the transfer. This is known as Lambert’s problem. The problem consists of calculating the transfer orbit that connects a point on the initial orbit to another point on the final orbit in a certain amount of time. To find the solution, an algorithm using a numerical method can be used. Therefore, the contribution of this work is the solution of the problem using universal variables in a algorithm which uses two computed search stages (rough and fine search). This approach allows achieving accurate results with a low CPU effort. This algorithm was implemented to provide a maneuver simulator capable to assist in the spacecraft mission analysis, seeking for the best combination of time and fuel consumption. Analysis of disturbing effects in the dynamical model of orbit determination using GPS Paula C.P.M. Pardal (1), Rodolpho Vilhena de Moraes (1,2), Hélio Koiti Kuga (1) (1) National Institute for Space Research - INPE, Brazil (2) UNESP - Univ. Estadual Paulista, Brazil The problem of orbit determination consists essentially of estimating parameters values that completely specify the body trajectory in the space, processing a set of information (measurements) from this body. Such observations can be collected through a tracking network on Earth or through sensors. The Global Positioning System (GPS) is a powerful and low cost means allowing the computation of orbits for artificial Earth satellites. The T/P satellite is an example of using this system for space positioning. The orbit determination of artificial satellites is a nonlinear problem in which the disturbing forces are not easily modeled, like geopotential and direct solar radiation pressure. Through an onboard GPS receiver it is possible to obtain measurements (pseudo-ranges) that can be used to estimate the state of the orbit. The main target here is to determine the orbit of an artificial satellite, using signals of the GPS 77 constellation and least squares algorithms as a method of estimation, with the aim of improving the performance of the orbits estimation process and, at the same time, minimizing the procedure computational cost. Perturbations up to high degree and order for the geopotential coefficients, direct solar radiation pressure, and sun-moon gravitational attraction were taken into account. It was also considered the position of the GPS antenna on the satellite body that, lately, consists of the influence of the satellite attitude motion in the orbit determination process. Pseudo-range measurements were corrected from ionospheric effects, although the accuracy on orbit determination is not expressive. An application has been done, using real data from the Topex/Poseidon satellite, whose ephemeris are freely available at Internet. The best accuracy obtained in position is shown for short period (2 hours) and for long period (24 hours) orbit determination. In both cases, the perturbations mentioned before were taken into consideration and the analysis occurred without selective availability on the signals measurements. Precise predicted extended ephemeris solution for GPS Rajendra P. Prasad , Space Mechanics and Control Division - DMC, INPE, Brazil Hélio Koiti Kuga, Space Mechanics and Control Division - DMC, INPE, Brazil Nagaraj Dixit, Texas Instruments Inc. - Bangalore, India After 3 decades of increasingly widespread use, Satellite navigation-based services have changed significantly. Global navigation satellite systems like GPS, GLONASS or the future systems like Galileo require precise orbit and clock estimates in order to provide high positioning performance. New technology enablers such as assisted GPS (A-GPS) the use of massively parallel correlation and the application of advanced positioning techniques have significantly enhanced the time-to-first-fix (TTFF) and sensitivity of todays receivers. A-GPS significantly improves GPS performance by taking advantage of an existing communications link to the device, whether wireless or via cradle, to download ”assistance data”, essentially a copy of what the GPS satellites are actually transmitting. This helps bypass the bulk of the initial GPS signal acquisition delays, thereby yielding faster TTFF, lower battery drain and higher sensitivity. The time taken to decode the ephemeris from the satellite signal forms a significant part of the TTFF. This time ranges from about 18-30 seconds at high signal levels ( 140dBm), to several minutes at low signal levels ( 148dBm). During very low signal levels scenario, decoding the ephemeris from the satellite signal may not be possible at all times. Providing the receiver with ephemeris from other means is thus important, as it bypasses the need for decoding the ephemeris from the satellite signal. This will (a) significantly decrease the TTFF, and (b) allow the receiver to give position fixes even with the satellites at very low signal levels. Traditional approaches to provide the receiver with ephemeris assistance have involved downloading the satellite ephemeris. However, this approach requires that the receiver has real time connectivity via either a mobile phone network or the internet. Extended Ephemeris is a key component of Assisted GPS (A-GPS) which enables GPS platforms to operate where direct satellite data is unavailable. The innovative implementation is developed in-house to allow for transmission over a multitude of communication media to deliver maximum availability and unparalleled accuracy. In this approach the receiver has algorithm capable of predicting extended ephemeris for a period of time (typically 3 to 6 days), with an availability of broadcast ephemeris which aids to predict precise ephemeris for the above duration. In this context precise Satellite orbit prediction molding was carried out and the software is designed on the server based approach initially. Ultimately the software shall be ported on to a chip. The initial results are very encouraging and the prediction accuracy in 6 days was better than 60m, which meets the requirements. These server based solutions further lower TTFF to the 6-15s range. The paper describes the need aspect, the orbit prediction modeling and description of chip based architecture along with typical case studies. Internal loading distribution in a statically loaded ball Mário César Ricci , National Institute for Space Research - INPE, Brazil A new, rapidly convergent, numerical procedure for internal loading distribution computation in statically loaded, single-row, angular-contact ball bearings, subjected to a known combined radial, thrust, and moment load, is used to find the load distribution differences between a loaded unfitted bearing at room temperature, and the same loaded bearing with interference fits which might experience radial temperature gradients between inner and outer rings. For each step of the procedure it is required the iterative solution of Z + 3 simultaneous nonlinear equations - where Z is the number of the balls - to yield exact solution for axial, radial, and angular deflections, and contact angles. Numerical results are 78 shown for a 218 angular-contact ball bearing. Closed Loop Control System Applied to Transfer Maneuvers Using Continuous Thrust Evandro Marconi Rocco, Eliel Wellington Marcelino, Antonio F,B.A. Prado National Institute for Space Research - INPE, Brazil This work considers the problem of controlling the trajectory during orbital transfer maneuvers, using a propulsive system capable of applying continuous thrust for a long period of time. Some non-ideality of the thrusters and their effects on the control system during the transfer orbit were analyzed. It was considered a control system in closed loop and low-thrust propulsion with high specific impulse. Through some simulations, it was possible to analyzed the deviation in the trajectory and evaluate the control system. Two cases were considered: velocity increment applied tangentially to the trajectory, with and without errors in the propulsion system. Therefore, a gradual increase of the semi-major axis was obtained. To validate the simulator, the results were compared with the literature. The results showed that the use of continuous thrust might present advantages for some space missions. It was also confirmed the requirement of a closed loop control system for these missions. Optimization of Low-Thrust Spiral Transfers between Two Given Orbits Alexander A. Sukhanov , Space Research Institute (IKI) of the Russian Academy of Sciences, Russia Power-limited low-thrust transfers between two given orbits in a strong gravity field are considered. In a general case such transfers are spiral, i.e. they include many revolutions around the attracting center, what makes the transfer optimization a difficult task. A simple and effective method for opimization of these multi-revolution transfers is suggested. This method is based on the linearization of the motion near reference Keplerian orbits and use of the Pontryagins maximum principle for the linearized problem. The suggested method allows calculation of three types of transfers, such as follows: • transfers from a given state vector to a given orbit with optimal entry position into the final orbit; • transfers from a given orbit to a given state vector and obtaining an optimal start position from the initial orbit; • transfers between two given orbits and obtaining optimal initial and final positions of the transfer trajectory. All of the three transfer types are considered. However, linear approach does not make it possible obtaining a global optimum. approximation is also considered and the respective solution of the problem is given. A second-order The suggested method demonstrates good convergence in the cases of a big number of revolutions and a big difference between the initial and final orbits in size, inclination and orbit types. The method is also applicable if there is a constraint on thrust direction and for the case of partly given final orbit; for example, when only energy or semi-major axis and eccentricity of the final orbit are specified. Numerical examples showing the high effectiveness and the wide applicability of the suggested method are given. Linear and second-order solutions are compared. Optimal Low-Thrust Limited-Power Transfers in a Non-central Gravity Field - Transfers Between Arbitrary Orbits Carlos Silveira, EMBRAER, Brazil Sandro da Silva Fernandes, ITA, Brazil This paper presents a study of optimal low-thrust limited-power trajectories in a non-central gravity field which includes the oblateness of the Earth (i.e., includes the second zonal harmonic J2 in the gravitational potential). Initially, the space trajectories optimization problem is expressed in Mayer form, with Cartesian elements - position and velocity vectors - as state variables. The concepts of Optimum Control Theory, namely, the Pontryagin Maximum Principle, a re then applied to this problem, providing a maximum Hamiltonian. The resulting formulation is afterwards modified by introducing a set of suitable orbital elements through a canonical transformation. A version of the Hori method - a perturbation technique based on Lie series - specific to semigeneralized canonical systems is then applied to 79 this new formulation, resulting in an averaged maximum Hamiltonian, which characterizes long duration transfers. A numerical solution for this problem is obtained for some transfers between arbitrary elliptical orbits, employing an algorithm based on the second variation method (neighboring extremals) to solve the two-point boundary value problem associated with the averaged Hamiltonian. The results obtained are compared to those provided by the same method for the undisturbed problem (central gravity field), in order to analyze the influence of J2 in the transfers considered. Innovative Dynamical Analysis of the Algorithmic Weak Stability Boundary Maisa de Oliveira Terra, Priscilla Andressa de Sousa Silva ITA, Brazil In this contribution, we rebuilt and analyze the Weak Stability Boundary (WSB) algorithmic definition with the inclusion of the moon and earth collisional sets and the explicit construction and subclassification of the associated unstable set generated by this definition. The WSB concept associated to lunar ballistic capture in the final portion of the earth-moon transfer orbit was introduced by E. Belbruno (1987 and beyond) in the context of alternative techniques proposed to design low energy transfer orbits, by exploiting the intrinsic nonlinear dynamics of three and four body problems in a more natural way. With the aim of clarifying the applicability of the WSB in realistic mission design, a refined investigation of the several possible stable-unstable transitions is performed by considering elucidative criteria based on three-body problem dynamical elements. A comparison of gravity-assisted maneuvers in different planets to optimize interplanetary missions Flaviane Venditti, National Institute for Space Research - INPE, Brazil Evandro Marconi Rocco, National Institute for Space Research - INPE, Brazil Antonio F.B.A. Prado, National Institute for Space Research - INPE, Brazil Alexander A. Sukhanov , Space Research Institute (IKI) of the Russian Academy of Sciences, Russia This work presents a comparison of different possibilities of gravity-assisted maneuvers on Mars, Jupiter and Saturn. The problem involving interplanetary trajectories can be formulated as a multi-objective problem due to the nature of the mission. The optimization problem is solved using a methodology based on the Non Inferiority Criterion (Pareto, 1909) and the Smallest Loss Criterion (Rocco et al. 2003), where all objectives are considered simultaneously, without reducing the problem to the case of optimizing a single objective. The three objectives to be optimized are: fuel consumption, in other words, the DV; the duration of the mission; and the waiting time on Earth for launch, The trajectory is divided into three parts, where the first and the last one are inside the sphere of influence of a planet, and the intermediate part is a heliocentric phase. This methodology is called Patched Conics. Several simulations were obtained using the Transfer Trajectory Design Programs (Sukhanov, 2004), analyzing the best way to reach Pluto using gravity-assisted maneuvers. For this purpose a few planets were tested with different combinations of dates for the maneuvers, launch and arriving windows. Then a conclusion of which planet is best suited for the chosen dates was obtained. References: Pareto, V. Manuale di economia politica com una introduzione alla scienza sociele. Milão: Societa‘ Editrice Libraria, 1909. Rocco, E. M. Manutenção orbital de constelaço es simétricas de satélites utilizando manobras impulsivas ótimas com vı́nculo de tempo. São José dos Campos. 178 p. Tese (Doutorado em Engenharia e Tecnologia Espaciais / Mecânica Espacial e Controle) - Instituto Nacional de Pesquisas Espaciais, 2002. Sukhanov, A, ”Users Guide for Transfer Trajectory Design Programs”. Manual técnico, IKI, Moscou, Rssia, 27pp, 2004. Venditti, F.; Rocco, E.M.; Prado, A.F.B.A.; Sukhanov, A., ”Gravity-Assisted Maneuvers Applied in the Multiobjective Optimization of Interplanetary Trajectories”. IAC 2009- 60th International Astronautical Congress. Daejeon, Republic of Korea, October 12-16, 2010. 80 MINISYMPOSIUM 3. Spacecraft Attitude Dynamics and Control Organizer: Luiz Carlos DeSouza (INPE, Brazil) Space mission success depends on adequate dynamics investigation and control system performance. Besides, future advanced space missions will involve control system design technique with novel architectures, technologies, and algorithms to solve the Spacecraft Attitude Dynamics and Control System problems. This session is open to papers with topics ranging from dynamics theoretical formulations to innovative control systems design that will advance the state of the art, reduce the cost of applications, and speed the convergence to hardware, numerical, or design trade solutions. Combined Attitude and Solar Tracking (CAST) System for Spacecraft Mohd Faizal Allaudin, Renuganth Varatharajoo University Putra Malaysia The spacecraft solar panel Sun tracking mechanism is utilized as an attitude control system. This is done by manipulating the tracking control of both the solar panels along the spacecraft pitch axis to generate torque in order to counter-act the external disturbance along this axis. The two solar panels are rotated at different speeds in order to generate the required torque. Matlab Simulink was used to evaluate the system where the inputs are Sun tracking function and attitude reference while the outputs are the solar panel rotation angle due to Sun tracking and spacecrafts pitch attitude. The governing equations together with the onboard attitude and solar tracking architecture are established. The architecture is the numerically tested. The simulation results are discussed especially from the attitude control standpoint. The integrated system complies very well with the reference mission requirement. Fly-by guidance approach for rendezvous and capture of non-cooperating targets Gilberto Arantes Jr., University of Bremen, Germany Ananth Komanduri , University of Bremen, Germany Daniel Bindel , University of Bremen, Germany Luiz de Siqueira Martins-Filho, Universidade Federal do ABC, Brazil Non-cooperative satellites include a vast category of spacecrafts which have lost their control or operational capabilities due to erroneous orbit injection or/and component failure. Space debris and Near-Earth Objects (NEO) belong to those class of non-cooperating targets as well. Space missions like Orbital Express launched in 2007 open up a new era in space - on-orbit servicing - which is defined by repair, retrieval, maintenance, and rescue of satellites on orbit. The development of technologies for autonomous rendezvous and docking plays an important role for the mitigation of space debris problem. A fundamental challenge of on-orbit servicing is the safe approaching of the spacecraft to an unstable/uncontrollable target. In this case the target satellite is not able to cooperate with the service satellite during the rendezvous and capture phases. This work focuses on the guidance functions that can handle a satellite possibly rotating and lacking the ability to maintain its docking port or grasping fixture aligned with the on-orbit servicing requirements. The viability and suitability of the fly-by approach are tested through numerical simulations and preliminary sensibility analysis. The results show that the fly-by method can be an interesting guidance alternative for rendezvous and capture of non-cooperating targets. Attitude Synchronization for swarms of Pico-Satellites using Consensus Algorithms Sid Ahmed Attia , Ariel Pratomo TU-Berlin, Germany In this paper, we consider the problem of attitude synchronization for a swarm of pico-satellites. The approach proposed consists of two distinct stages. The first stage consists in using a feedback linearization technique that allows transformation of the satellite equations of motion to a set of decoupled double integrator dynamics. The second stage consists then in applying consensus algorithms for the linearized dynamics. An exchange of information between the different pico-satellites to synchronize the attitudes is carried out at this level. The obtained law is thus formulated for the transformed system. Inverse 81 transform is then applied to extract the real control inputs to the pico-satellites. Simulation results for the BeeSat platform are included for both cases of ideal communication links and for links with packet loss and compared to state of the art approaches. Integer ambiguity resolution in attitude determination using GPS measurements Leandro Baroni , Hélio Koiti Kuga National Institute for Space Research - INPE, Brazil If three or more GPS antennas are mounted properly on a platform and difference of GPS signals measurements are collected simultaneously, the baselines vectors between antennas can be determined and the platform orientation defined by these vectors can be calculated. Thus, the prerequisite for attitude determination technique based on GPS is to calculate baselines between antennas. For accurate attitude solutions can be obtained, carrier phase double differences are used as main type of measurements, including all independent combinations of antenna positions. Baselines between antennas must be determined in millimeter level of accuracy. The use of carrier phase measurements leads to the problem to determine precisely the ambiguous integer number of cycles in the initial carrier phase (integer ambiguity). To increase confidence and accelerate the process by limiting the search space, three types of restrictions can be established from the knowledge of antenna system fixed geometry. In this work was implemented and tested algorithms for ambiguity resolution allowing accurate real-time attitude determination using measurements given by GPS receivers in the uncoupled form, which is, estimating baselines independently from each other, and in coupled form, which the platform orientation (Euler angles) is obtained through processing all baselines. The results showed that LSAST method performance is similar to LAMBDA as the number of epochs which are necessary to resolve ambiguities, but with processing time significantly higher. The final result accuracy was similar for both methods, better than 0.1◦ to 0.2◦ , when considered baselines decoupled form. Fine maneuver control for spacecraft simulator by reaction wheels using sliding mode speed controller Mohammad Hossein Beheshti, Iran This work addresses the attitude control of a triaxial spacecraft simulator by applying variable structure control theory to design a set of proper speed controllers for reaction wheels in presence of unknown disturbances and parametric uncertainties. The controller goal is to change the rotational speed of reaction wheels to adjust the spacecraft simulator in desired course. The mathematical models of satellite simulator consisting of a rigid base body and three reaction wheels as actuator are developed. Variable structure control theory is then applied to synthesize a set of linear controllers that deals with both nonlinearities in the equations and disturbance sources. Based upon sliding mode control theory, this speed controller is independent from static friction model of reaction wheels, so that the difficulty of getting an accurate model is avoided. The simulated model response to wheel speed shows that the sliding mode speed controller is effective and the attitude error could be reduced in comparison to PID speed controller. Modeling a Reaction Wheel Valdemir Carrara, National Institute for Space Research - INPE, Brazil It is well known that reaction wheels, that have special role in satellite attitude control, present a nonlinear behavior in low angular velocities, due to static and Coulomb friction torques. In general these non-linearities are neglected by the control system, as the control law can easily treat then as an ordinary error. Therefore attitude errors tend to increase during the zero crossing of the wheels angular velocity. Solutions have been implemented in onboard computers, like robust control, or the use of distinct gains in low angular velocities to minimize the error, or to keep the wheel operating in only one sense, to avoid zero crossing. This paper aims to model the non-linear, zero crossing behavior of a reaction wheel, and to use this mathematical model to derive the control action, i.e. the electrical current imparted to the wheel motor. To do so, a 0.65 Nm wheel was tested in a lab environment to collect the necessary data to obtain the parameters of the model. The new control model was then tested in an air-bearing table and the results were compared to the normal PID controller. Results showed that the new model significantly affected both the error and control performance. 82 Reduced order attitude dynamic model of a satellite with reaction wheels and appendages Valdemir Carrara, National Institute for Space Research - INPE, Brazil Satellite attitude simulation is largely employed during planning, design, integration, test and operation of a space mission. Qualification tests of the attitude control subsystem require substantial modeling effort in order to assure simulator fidelity. Nevertheless, equations of motion based in rigid body assumption are still used due to its simplicity and reliability. Body flexibilities are considered only when explicitly required. Although dynamic models that include reaction wheels and eventually nutation dampers are commonly employed in simulators, they lack the effects of appendages, like the rotation of solar panels, articulated robotic arms, booms, and mass movement in the satellite motion. When such effects are considered in the dynamic model, they increase the order and the complexity of the differential equations, due to the change in the satellite center of mass position caused by appendage motion. In order to avoid model complexity the angular momentum can be written with respect to a fixed point instead of the center of mass, which in turns make necessary to invert a 3(A+W) + 6 matrix to evaluate the angular velocities of a satellite with A appendages and W reaction wheels. Also, the torque in each appendage joint should be known, which requires motor, bearing and joint control modeling. This work presents a new approach to solve both the increasing of model order and unknown torque. Taking the angular moment relative to the center of mass the resulting differential equations can be written directly in angular velocity variables, which reduces the order to 3(A+W) + 3. Assuming also that the appendages acceleration are known (which is more realistic than the joint torque), then order of the dynamic model is reduced to mere 3W + 3. The resulting reduced order but complex model is presented in this work. Differential Games of Stabilization Ximena Cubillos, Brazil Susana Dias, Portugal Luiz Gadelha, Brazil Anna Guerman, Portugal Georgi Smirnov , University of Minho, Brazil Pontryagin’s theory of linear differential games [1] is a natural tool to solve local stabilization problems under conditions of uncertainty. In this work we develop stabilization methods based on the differential games approach. Differential games of stabilization [2] have some special characteristic features distinguishing them from other differential games. We discuss theoretical and computational aspects of this class of differential games. The main area of applications considered in this work is attitude stabilization of spacecrafts with unknown mass properties, mobile and flexible elements [3]. Bibliography: [1] L. Pontrygin, Linear Differential Games of Pursuit, Mathematics of the USSR-Sbornik, 40, 1981, pp. 285-303. [2] G. Smirnov, Introduction to the Theory of Differential Inclusions, Graduate Studies in Mathematics, vol. 41, American Mathematical Society, 2002. [3] K. Yamada and S. Yoshikawa, Adaptive Attitude Control for an Artificial Satellite with Mobile Bodies, Journal of Guidance, Control and Dynamics, vol. 19, No. 4, 1996, pp. 948-953. Performance Comparison of Attitude Determination Algorithms in a Microcontroller Platform Ricardo Oliveira Duarte, Universidade Federal de Minas Gerais, Brazil Luiz Siqueira Martins-Filho, Universidade Federal do ABC, Brazil Hélio Koiti Kuga, Instituto Nacional de Pesquisas Espaciais, Brazil This paper presents a study concerning the practical implementation and the performance analysis of attitude determination procedure for artificial satellites implemented in a microcontroller environment. Three different algorithms were selected and implemented in a microcontroller platform. The three algorithms were compared according to numerical precision, CPU cycles, program and data memory required. The algorithms considered to calculate the attitude were the TRIAD, the Q-Method and the QUEST. Each of them requires at least two measurement vectors, in our system, given by the Earth magnetic field and the sun directions to calculate the attitude. The attitude representation in the project 83 was parameterized using the quaternions. The main goal of this project is the development of an embedded system for application in Brazilian satellites. This project is supported by the UNIESPAO Program of the Brazilian Space Agency - AEB and has a purpose to obtain a processing system able to properly calculate the attitude using an architecture based on low-cost COTS components provided with faulttolerance techniques. The whole embedded system is composed by a three axis solid state magnetometer, a photo-position sensor as a solar sensor and a PIC microcontroller. Attitude Control of Spacecraft Using Three Axis Magnetorquer Only Ahmad Faraag , Egyptian Space Program, Egypt Ahmad Raffie, Egyptian Space Program, Egypt Ahmad Bahgat, Faculty of Engineering, Cairo University, Egypt The problem of satellite detumbling after separation from launcher and attitude acquisition of a small satellite using magnetic actuators only is considered, a comparison between commonly used attitude control algorithms is presented. Simulation results are also given to show a qualitative comparison between the used algorithms. IMU Calibration Procedure for a Redundant Tetrahedral Gyro configuration with Wavelet De-noising Élcio Jeronimo de Oliveira, IAE/DCTA, Brazil Waldemar de Castro Leite Filho, IAE/DCTA, Brazil Ijar Milagres da Fonseca, INPE, Brazil The aim of this paper is to present a calibration procedure applied to an inertial measurement unit (IMU) composed by a triad of accelerometers and four gyros (FOG) in a tetrad configuration. The procedure takes into account a technique based on Least-square methods and wavelet de-noising to perform the best estimate of the sensor axis misalignments. The wavelet analysis takes place in order to remove high and undesirable frequency components via multiresolution signal decomposition analysis applied to accelerometer and gyro signals. Equations for the least-square methods and wavelets analysis are presented, and the procedure is verified experimentally. Preparation of Uniformly Distributed Onboard Guide Star Catalog Masood Ur Rehman Attitude determination accuracy of an autonomous star sensor for continues operation, depends upon many factors. The essential component of the star sensor is the onboard guide star catalog (GSC), which serves as the accurate inertial reference. The optimal selection of stars for GSC from the master star catalog (MSC) mainly depends upon the spectral response, visual sensitivity limits and Field of View (FOV) of the star sensor. The optimal GSC selection under memory and computational constraints requires having a constant number of stars in any random boresight direction (BS). Therefore stars selected for GSC must be uniformly distributed on the whole celestial sphere, whereas, natural distribution of stars is highly non-uniform. Many methods which produced nearly uniformly distributed GSC have been proposed in literature. In this paper a new approach is proposed to construct uniformly distributed GSC which emphasizes brightest stars to enhance the life time performance of star tracker for deep space missions. The comparison of statistical results demonstrates that results of the proposed scheme are promising. The propose scheme extends the life time performance of the star tracker by selecting brightest stars throughout entire celestial sphere. In addition, the selected stars are geometrically well separated which is beneficial for attitude determination accuracy of the star tracker. On the modeling of a flexible spacecraft attitude motion considering fuel sloshing Vahid Rezvani A complete three dimensional attitude motion of a flexible spacecraft considering the effect of sloshing in not fuel-filled tank has been investigated in this study. The problem of modeling such complex spacecraft configuration has found crucial applications in complicated space missions, such as interplanetary missions where huge amount of fuel and large flexible pads must be carried out. The spacecraft consists of a central rigid box with two flexible pads, and a spherical tank located at the center of the rigid box. To present 84 sloshing effects in the zero gravity condition without thrust consideration, an equivalent mechanical mass spring model has been developed. In this way, the spacecraft is modeled as a flexible multi body system and based on the Lagrangian equation, the mathematical model of system is derived. Afterwards, the simulation results of a typical model are computed and compared to those of a non-flexible spacecraft with fuel sloshing and rigid model consideration. The main novelties of this work are to develop a three dimensional equivalent mechanical model for fuel sloshing and to present the effects of both pad vibration and fuel sloshing on the angular responses. 85 MINISYMPOSIUM 4. Mathematical Applications in Electrical, Aerospace and Control Engineering Organizer: Ahmad Sabihi (Sharif University of Technology, Tehran, Iran) The aim of this session is to disseminate recent developments of mathematical applications in electrical and aerospace engineering, control, mechanics, electromagnetic fields, and radar cross section engineering. The session also surveys new contributions in applied mathematics and engineering sciences. Aircraft Generalized Dynamic Inversion Control Abdulrahman Hasan Bajodah, Ismail Hameduddin King Abdulaziz University, Saudi Arabia The new and evolving paradigm of generalized dynamic inversion (GDI) is applied to aircraft maneuvering control design, through the development of a new multiple constraint formulation. The flexibility of GDI in utilizing nullspace of the controls coefficient matrix is exploited to eliminate the problems of excessive control effort and limited performance that are associated with classical dynamic inversion. Scalar deviation functions of the aircraft state error variables are differentiated along the aircraft mathematical model solution trajectories, and linear time varying stable dynamics in these deviation functions are manipulated to obtain linear algebraic constraint equations in the control vector. The constraint equations are inverted using the Greville formula, resulting in the control law. The particular part of the control law drives the states to their desired values, and the auxiliary part acts to stabilize the vehicles inner dynamics by means of the null-control vector. The null-control vector is constructed via a novel class of positive semidefinite Lyapunov functions and nullprojected Lyapunov equations. The closed loop control system is assessed by performing a fully coordinated simultaneous heading-velocity change maneuver. The new type of GDI control laws shows to require low control effort, in addition to providing excellent transient response and reasonable steady-state tracking accuracy. Passive Thermal Control with Pulsating Heat Pipe Liomar de Oliveira Cachuté, Roger Ribeiro Riehl National Institute for Space Research INPE / Space Mechanics and Control Division DMC, Brazil Passive thermal control on aircrafts and spacecrafts is a major issue on modern equipments once the thermal loads on avionics and other electronics installed on these vehicles have increased dramatically over the last decade. The need for heat dissipation is such an issue that a slight increase on the operation temperature of certain electronics might present a severe damage on its performance, yielding to the equipment shutdown. Constant temperature control for a given heat load that might be varying along time is a complicated thermal problem to be solved, especially on applications where conventional pumping systems cannot be used. In this specific case, the use of passive thermal control devices that operate by means of capillary forces (such as regular heat pipes and loop heat pipes) and by means of slug/plug generation (such as pulsating heat pipes) are widely used with reliable operation. Heat pipes and loop heat pipes have been used for spacecrafts thermal control since the 70s but the application of pulsating heat pipes is still require investigations towards the definition of design and operational parameters. The objective of this work is presenting a brief investigation on a pulsating heat pipe operating with different working fluids and orientations, where its performance is analyzed and discussed. The results indicate that the pulsating heat pipe is able to operate at any orientation with reliable control of the heat source temperature. Hybrid Tracking Control of Fixed Wing Aerial Vehicles Ilse Camacho Cervantes, Fany Mendez Vergara Institute for Scientific and Technological Research of San Luis Potosi (IPICYT), Mexico In this paper, we introduce a coordinated guidance-tracking hybrid controller in order to control velocity, position and attitude of various fixed wing aircrafts. The proposed controller is able to adapt its operation depending on the trajectory, altitude, and external perturbations. The adaptive mechanism is activated via the satisfaction of a set of prescribed restrictions which are both security and performance based. 86 The nature of the controller is hybrid because the system dynamics is modeled continuously with the interaction of an adaptive discrete control action which defines the next active behavior of aircraft. Features of the control are so that security and performance restrictions may be state or trajectory dependent. Additional restrictions can be easily included as long as the entire state space has assigned a single closed-loop dynamics in a finite number of state partitions. Here, conditions of stability are studied as well as their dependence with control gains, control bounds, and switching restrictions. Numerical simulations in a Cessna 182 are used for illustrating the proposed control method. Experimental work is developed to illustrate some of the control features in a scaled aircraft. Finite volume solution of compressible magnetohydrodynamics equations Sergio Elaskar, Livio Maglione, Mariano Martinez Argentina Flow studies related to an electrically conducting gas that moves in a magnetic field have been developed. The objectives of theses studies are to solve 1D and 2D, time-dependent, viscous and resistive magnetogasdynamics, or compressible magnetohydrodynamics, flows and 3D time-dependent, ideal magnetogasdynamics flows. Its numerical approach is based on a finite volume technique and to compute the numerical fluxes across cells interfaces, an approximate Riemann solver coupled with the Total Variation Diminishing (TVD) scheme proposed by Harten and Yee is utilized. Besides implementing the eigensystem technique and the eigenvectors normalization for the magnetogasdynamics equations, a new sonic fix for the Harten-Yee scheme is applied. The computational code has been tested with the simulations of the magnetogasdynamics Riemann problem and of the Hartmann flow. At the present, this code is being applied to simulate the internal plasma dynamics of solar post-flare loops and of the dark inflow in post-flare-supra-arcade. Finite volume simulation of supersonic flows Sergio Elaskar, José Tamagno Argentina A TVD scheme has been implemented on a non structured 3D finite volume formulation for solving the Euler equations. To simultaneously, achieve adequate accuracy in smooth flows, high resolution at flow discontinuities and to avoid spurious oscillations, different flux limiter functions are applied in a waveto-wave basis. This technique implements compressive limiter functions in waves from the family two to four and diffusive limiter functions in waves one and five, thus, the robustness of the TVD scheme is preserved and a reduction of the numerical viscosity can be achieved. This sort of adaptive scheme has satisfactorily been applied to the slip interface between two parallel flows and to supersonic flows over an airfoil and a blunted bi-conic body. The code has also been used to compute the flow around re-entry bodies. Finite rate chemical effects can be introduced accounting for source terms in the Euler equations. Such source terms representing the chemical kinetics and vibration relaxation are often large, making the algorithm too stiff to be advanced explicitly. To avoid this stiffness an implicit treatment of the sources terms is implemented. To describe the hydrogen-oxigen-nitrogen mechanism 13 chemical species and 33 one step chemical reactions are employed. Position and Vibration Control of a Nonlinear Slewing Flexible Structure Considering FluidStructure Interaction André Fenili , Cayo Prado Fernandes Francisco Universidade Federal do ABC, Brazil Position and vibration control of a nonlinear flexible beam-like structure in slewing motion is investigated here. A DC motor is used as actuator and the movement of the motor axis provides the slewing motion. The flexible structure is mathematically modeled considering linear curvature and clamped-free boundary conditions. A cubic nonlinearity resulting from the coupling between the angular displacement of the motor axis and the flexible vibration of the beam is considered. One also includes in the mathematical model a drag force acting along the beam length. This force is modeled through the Rayleigh dissipation function. For position of the slewing axis and elimination of vibration in the beam the nonlinear control method named State Dependent Riccati Equation (SDRE) is applied to the DC motor axis. Sufficiently 87 large angular displacements and velocities are considered in order to the system to undergo nonlinear behavior. For small and for large initial angles (here considered as position errors) the system response converges satisfactorily to the desired final states. Design and Simulation of Intelligent Aircraft Longitudinal Autopilots Using Particle Swarm Optimization Algorithms Mostafa Lotfi Forushani, Iran Bahram Karimi, Amir Kabir Univesity and Technology, Iran Ghazanfar Shahgholian, Islamic Azad University Najafabad, Iran Alireza Karami Horestani, Iran Proportional-Integral-Derivative (PID) controller is still widely used in control and aerospace engineering. All the aircrafts benefit from a PID controller in Autopilot Control System for Longitudinal and LateralDirectional axes. The PID controllers are associated with their PID gains which can either be tuned manually or optimized by the methods like Particle Swarm Optimization (PSO) to get better control and enhancement in the performance. Particle Swarm Optimization is a powerful stochastic evolutionary algorithm that is used to obtain the global optimum solution in search space. This algorithm introduces mutation operator with adaptive mutation probability into the PSO algorithm as well as it replaces those particles which fly out the solution space with new generated random particles during the searching process. Here, PSO algorithm is successfully applied to Altitude Hold (AH) in longitudinal axis autopilot control of an aircraft. Our system is simulated by MATLAB programming based on Particle Swarm Optimization algorithm. Furthermore, the advantage of PSO algorithm in controlling parameters and performing the system is compared with traditional PID tuning method as Ziegler Nichols tuning rule. The results show good agreement and promising. A Micro-Tuning-Fork Gyroscope Coupling with an Electrodynamic Engine Ana Rosa Klinke, J.M. Balthazar, Luiz Palacios Felix, F.R. Chavarete, UNESP: Univ. Estadual Paulista, Rio Claro - SP, Brazil Nowadays, the technology of micro-electro-mechanical systems (MEMS) has many applications on Engineering Sciences. This technology allows that the movement to be expressed by a function of microscale ranging devices. However, the design of such mechanical systems can be quite challenging due to nonlinear effects which may strongly affect the dynamics behavior. The MEMS problem studied here is composed of an inverted pendulum fixed in a suspension space of mass movements having two degrees of freedom. The physical model under study is implemented by coupling between the electrodynamic engine and the system of inverted pendulum. This implementation concludes a model of a micro-tuning-fork gyroscope coupling with an electrodynamic engine. The numerical simulations are then carried out and one can obtain the vibration modes of the MEMS model. This model is excited by a sinusoidal voltage which applied to an electro-dynamic engine. The study also shows an interdependence of the inverted pendulum and the engine dynamics so that the pendulum motion influences on the vertical excitation supplied by the engine. Pseudo-stochastic-chaotic systems in Engineering Applications Hilda Angela Larrondo, Luciana De Micco Facultad de Ingenieria - Universidad Nacional de Mar del Plata, Argentina The statistical properties of chaotic systems made them capable play the role of stochastic sources in many applications. In this paper we review a number of engineering applications: chaotic spread spectrum communication systems, chaotic electromagnetic compatibility improvement, chaotic noise, chaotic sampling, etc. In many of these applications chaotic systems must work as pseudo random number generators. Several processing techniques used to improve the stochastic behavior of chaotic systems behave are evaluated by means of information theory quantifiers. The effect of discretization over randomness is also considered. 88 Solving the Sitnikov Equation by Means of the Fourier Expansion Mojtaba Dehghan Manshadi, Mohammad Farahani, Mohammad Ali Vaziry Iran In this paper, the problem of a zero mass body oscillating perpendicular to a plane in which two heavy bodies of equal mass orbit each other on Keplerian ellipses is considered. The zero mass body intersects with the primaries plane at the systems barycenter. This problem is universally known as the Sitnikov Problem. The authors solve the Sitnikov problem using the Fourier Expansion. Furthermore, the created analytic solution is compared to results obtained from numerical integration of the exact equation of motion. Conclusions of comparison show a good agreement. The results also show that increasing in amount of eccentricity and the derivation of amplitude in the initial condition status, the decision time of solving the problem decreases but increasing the number of the sentences of the Fourier expansion, it grows up. Robust SDC Parameterization for a Class of Extended Linearization Systems Sam Nazari, Bahram Shafai Northeastern University, USA We consider nonlinear regulation of systems with parametric uncertainty. Under mild conditions, these systems can be brought into a pseudo-linear form known as extended linearization. Under this formulation, conventional linear control synthesis methods can be applied. One popular technique that mimics the LQR method of optimal linear control is referred to as the State Dependent Riccati Equation (SDRE) approach. SDRE control relies on a nonunique factorization of the system dynamics known as the State Dependent Coefficent (SDC) parameterization. Under system uncertainty, each SDC parameterization will produce its own radius of stability in a region of interest in the state space. In this paper a method to compute the radius of stability in a special class of systems is used to obtain the SDC parameterization which results in the maximum radius of stability for the original nonlinear system in the region of interest. Finally, the approach is demonstrated on a testbed Segway Robot. On the Nonlinear Dynamics and Control of Modal Interactions Resulting from the Longitudinal and Lateral Flight of an Aircraft Rodrigo Bassinello Ramazotti, UNESP-Bauru, Brazil In this study, we analyze the nonlinear dynamic behavior of an aircraft in flight longitudinal and lateral shifts and interactions with one another. The aim of this study is to improve performance of the aircraft, cargo release, artifact weapons, releasing supplies in cases which a high degree of flexibility and survival reliability are needed. We conduct the analysis of the bifurcational behavior of the aircraft F-8 ”Crusader”. Before developing the research, a project namely Linear Optimal Control is proposed to stabilize the oscillations of angle of attack considering the critical regions of nonlinear behavior of the aircraft. The variation of longitudinal and lateral speeds of the aircraft aiming the numerical simulations in a virtual wind tunnel are also included. On the Electromagnetic Waves and Propagation in Relativity-Quantum Space Ahmad Sabihi, Sharif University of Technology, Tehran, Iran Relativity-quantum space refers to a type of space representing characteristics of the Einstein’s relativity and quantum theory of particles. Einstein gave a theory, namely special theory of relativity in 1905. In this theory, he claimed that the velocity of light is a measurable quantity which holds a constant value in all inertial frames of references. Also, he presented the theory of photoelectric effect having said light shows particle-like property. Light also shows wave-like property. The author wishes to do an investigation showing electromagnetic waves can also have both wave and particle-like properties. Here, a survey of the theories such as: Quantum Mechanics, Wave-Particle Duality, Homogeneous and Inhomogeneous Electromagnetic Wave Equations, Maxwell’s Equation in Curved Space-time, Quantum Electrodynamics, Quantum Chromodynamics, and Gravitational Waves will be accomplished by the Author. 89 Comparision of PO Approximations with FDA Method to Obtain RCS of Simple Shapes Ahmad Sabihi, Sharif University of Technology, Tehran, Iran Mohammad Ali Vaziry Z., Amir Kabir University of Technology, Iran Here, the Authors compare the Radar Cross Section (RCS) of some simple shapes such as: Cylinder, Sphere, Rod, Rectangle, and Right-Triangle by Physical Optics (PO) approximations with computed RCS values of same shapes by Fast Decomposing Algorithm (FDA) method. On the Laser Cross Section of Various Targets Ahmad Sabihi, Sharif University of Technology, Tehran, Iran Mohammad Ali Vaziry Z., Amir Kabir University of Technology, Iran This Paper surveys Laser Cross Section (LCS) prediction methods of various objects as sphere, flat plate, corner reflector, and complex targets as an aircraft. Here, it is found expressions for total LCS of a flat circular disk of optional radius. A Non-Model Based Damage Detection Technique Using Dynamically Measured Flexibility Matrix Mehdi Salehi, Saeed Ziaei-Rad, Mostafa Ghayour, Mohammad Ali Vaziri-Zanjani Iran Although many damage detection methods have been developed to detect damage in a structure using measured modal parameters, most of them have to make use of modal data of the structure for the intact state as baseline or a correlated finite element model. For beamlike structures, curvature techniques as mode shape and flexibility curvatures have been applied for localizing damage. An approximate flexibility matrix can be derived using a lot of number of vibration modes whose columns are referred as flexibility shapes. In this paper, a damage localization method is developed based on changes in flexibility shapes as well as its curvature. Differential Quadrature Method (DQM) is implemented in order to obtain the curvatures of flexibility shapes. As shown before by other authors, this method is sufficient for modeling damage. To reduce error values due to experimental data differentiation, a moving curve fit method as well as DQM is implemented on flexibility shapes. The proposed method is validated by numerical and experimental case studies. Smart beam deflection behavior due to two or more SMA wires attachment Hamid Salehi, Saeed Ziaei-Rad, Mohammad Reza Zakerzadeh, Mohammad Ali Vaziry Zanjani Iran This paper is concerned with the deflection behavior of an Euler-Bernoulli beam when two Shape Memory Alloy (SMA) wires are attached to it. In real application of SMA as an actuator for shape control purposes, the number of actuators is not limited to one. In order to solve the problem, first, the large deflection formulation of a beam under two applied forces is derived. Then, the thermomechanical behavior of wires with the load deflection behavior of the beam is coupled and governing equations are extracted. Finally, the measurement is carried on the SMA wires to obtain the parameters associated to the utilized thermomechanical model for the SMA wires. Several case studies are then accomplished and the results are discussed in details. An Hierarchical Approach for the Structural Damage Identification Leonardo B. L. Santos, National Institute of Space Research - INPE, Brazil Leonardo D. Chiwiacowsky, Universidade do Vale do Rio dos Sinos (UNISINOS), Brazil Haroldo F. Campos Velho, National Institute of Space Research - INPE, Brazil The use of global techniques for damage identification is based on the fact that the presence of a fault will cause changes in the structural properties of the system, which in turn lead to a change in its dynamic response. The changes in the structural properties could be assessed by measures in the time, frequency or modal domains. To solve this inverse problem - Structural Health Monitoring - is possible to use, for example, methods from the Calculus of Variations, with the Conjugate Gradient Method (CGM 90 Alifanov approach) in the form of adjoint equation. The central objective of this research is to significantly increase the speed of the method developed by Chiwiacowsky et al, 2005 which has been used for the damage identification. The new strategy for attacking the problem is based on the application of an hierarchical search to evaluating the different areas where damage may be present, starting with a coarse discretization and promoting gradual refinement only in the areas where the possibility of damage was not discarded. Preliminary results has shown that, in case of random (non-correlated) distribution of damage, the hierarchical approach can be until twenty-three times faster than the traditional search. On the Active Vibration Control and Stability of the Tubular Structures by Piezoelectric Patch-Like Actuators Sergey N. Shevtsov , South Center of Russian Academy, Russia Michail B. Flek, Rostvertol, Russia Vladimir A. Acopyan, Institute of Mechanics & Applied Mathematics, Russia Vladimir N. Axenov, Don State Technical University, Russia We present some theoretical and real-world approaches to design and implement smart vibration control of aircraft tubular structures which are controlled by feedback with power PZT patches. Experimental tests show that active vibration control and stability of a control loop may be lost at some parameters of vibration and feedback. To determine the causes of instability, a flexible tubular structure with surfacebonded PZT patch actuated is modeled by PD controller using Euler-Bernulli beam theory. Emphasis in this study is given to the effect of actuator size and location based on the observability, controllability, and stability of the control system. Using finite element transient analysis of a beam structure of bonded PZT patches controlled by feedback, linear function of local strain and strain velocity of strain gauge placement is developed. Such action work mode can be stable both at relatively small feedback and narrow frequency band. Also, due to nonlinear nature of a coupled electro-mechanical distributed control, the suppressed vibration mode shape can be transformed to vibration of other forms. We approach to a new method for all actively controlled PZT patches driven at a narrow frequency band, filtering preferentially on the first eigenfrequencies. Moreover, installed shunted passive PZT patches will damp high vibration frequencies, while simultaneously the stability of the control loop increases. Finally, we present some experimental results obtained by a scaled (1/7) helicopter rotor. On the Modification of Node Swapping Method in graph partitioning Omid Talebi, Ahmad Sabihi, Pejman Khadivi Iran In this paper, the authors propose a new algorithm for the Node Swapping Method in graph partitioning. Here, the proposed algorithm modifies that method so that any number of graph or network’s nodes can be partitioned into any optional number of subsets (preferably into a divisible respect). The application of given method on the some random graphs is also validated by well-known Complete Search Method. The final conclusions show a good improvement in time processing and error values with respect to the other old methods. On an Optimal Linear Control Design Applied to a Non-Ideal and Ideal Structure controlled through MR Damper Angelo Marcelo Tusset, UFTPR, Brazil Fábio Roberto Chavarette, UNESP - Ilha Solteira, Brazil Jorge L.P. Felix, UNIJUI, Brazil José Manoel Balthazar, UNESP - Rio Claro, Brazil This paper presents the control strategies of non-linear dynamics of a particular structure coupled (or uncoupled) to an essentially nonlinear oscillator using a magnetorheological (MR) damper. We make use of an optimal linear control design for reducing the amplitudes and energy consumption of the MR damper oscillations derived from both ideal and non-ideal mathematical models. The authors approach to a model in order to control the mechanical and electrical parts of the systems by the MR damper using 91 the two different methods. Firstly, we formulate and resolve the control problem in order to design the linear feedback dumping force controller. Then, the control dumping force functional values are converted to electrical control signals by a proposed mathematical model. The numerical simulations accomplished show that the presented method is so effective in controlling the non-linear dynamics of a particular structure. Also, using the proposed MR damper, one is able to determine electric current values applied to the control system. Semi-Lagrangian Reachability Analysis for Aircraft Safe Flight Envelope Determination Eddy van Oort, Delft University of Technology, The Netherlands To prevent aircraft loss-of-control incidents, knowledge of the safe maneuvering envelope is of extreme importance. The safe maneuvering envelope can be determined by means of reachability analysis from a known safe set, for example the set of all trim states. Implicit surfaces provide a convenient way to describe sets because of their ability to inherently handle merging and pinching of sets. Level set methods add dynamics to implicit surfaces, and the evolution can be tracked by the viscosity solution of a Hamilton-Jacobi partial differential equation. Unfortunately, uniform grid based solvers for level set methods suffers greatly from the curse of dimensionality. Additionally, for Eulerian methods the time step is limited by the Courant-Friedrich-Lewy condition. This combination makes application to aircraft dynamics too computationally demanding. In this paper an alternative method is used based on a Semi-Lagrangian solution method on adaptive kd-tree grids. This method allows a larger timestep, and adapts the grid as required during the evolution of the implicit surface. The method is applied to several examples in two- and three dimensions. The results are compared with an Eulerian solution method. Based on the results conclusions are drawn and future research directions are formulated. Spacecraft Trajectory Optimization Using State Parameterization and Interval Analysis Elwin de Weerdt, Q.P. Chu , J.A. Mulder Delft University of Technology, Faculty of Aerospace Engineering, The Netherlands Trajectory optimization of spacecraft has been an active research field for many years. Many solvers are based on local optimizers (gradient based, heuristic methods) therefore lacking the guarantee of finding the global optimum within finite time. A novel optimization algorithm is introduced based on interval analysis which does provide this guarantee. Moreover, all optimal solutions in the solution set will be found. State parameterization is used to transfer the infinite dimensional trajectory optimization problem into a finite dimensional, static optimization problem. By using state parameterization instead of the commonly used control parameterization one can prevent explicit integration of the dynamics. Instead the dynamics are used to derive the control trajectories based on the state trajectories via the equations of motion. Preventing explicit integration reduces the computational load significantly. The proposed solver (optimization and parameterization) is validated using three examples: the orbit transfer problem (Hohmann transfer), rendezvous and docking problem (using Hill-Clohessy-Wiltshire equations), and formation flying with large inter-satellite distances. The results demonstrate that the proposed solver can indeed produce guaranteed optimal trajectories for linear and non-linear complex problems. 92 MINISYMPOSIUM 5. Multidisciplinary Design and Optimization in Aerospace Industry Organizers: Ali Kamran, He LinShu, Amer Rafique (BUAA, China) Multidisciplinary Design Optimization (MDO) is an emerging field in aerospace engineering that attempts to introduce a structured methodology to locate the best possible design in a multidisciplinary environment, through the application of optimization algorithms. MDO can be considered to be a discipline in and of itself with an intention of acting as an agent to bind the other disciplines together. Papers are sought that address topics in development or application of MDO methodology, Multidisciplinary Analysis, and optimization methods. MDO applications of interest address aerospace and mechanical systems for use in Aerospace Industry that may incorporate any number of enabling technologies. Papers are also sought on Space Propulsion System design and Optimization. This includes design, optimization and application of solid rocket motor and liquid engine systems and subsystems. Information Entropy as a Tool for Innovation Projects Fuzzy Front End Decision Luis Wwaack Bambace, National Institute for Space Research - INPE, Brazil Project decisions The Suh Entropy axiom links the success probability to information entropy and also too usable and total variable field. With trial success probability, binomial distribution, detailed work breakdown structure and time-motion study is possible to compare design alternatives in terms of developing effort regardless of the level of organization of the project team. The total number of design variables in specification, processes, trade off, regulation and so on less the number of fundamental variables in the item and less available equations gives the number of totally unknown degrees of freedom the main part of entropy in designs that are new to the developers. This together with residual lack of information due to failures in documentation, for instance obtained with Mils and Jelinski-Moranda models give and extra entropy part. This tool together with parallel development, and Real Options information value, and detailed probability calculations of development trees allows new concept with intrinsic advantages and few complementary solutions and possible ad-ons to it to be compared with traditional solutions with a large number of ad-ons in terms of project reliability, easing Fuzzy Front End Decisions. New heuristic approach for the multiobjective nonidentical circle packing problem José Carlos Becceneri, National Institute for Space Research - INPE, Brazil In this paper we present a heuristic for the multiobjective nonidentical circle packing problem (MNCPP), where none of the pairs of circles overlap (a bi-dimensional space are considered). We considered two important objectives for allocation of instruments or pieces of equipment in a spacecraft or satellite: to minimize the radius of the circle containing all of the objects and the imbalance (attempts to minimize the non-equilibrium of mass of all objects around the central point). In this new heuristic, the circles are sorting the mass and the radius of each circle, trying to get a viable solution that minimizes the imbalance. Next, an evolutionary algorithm is used to improve the best solutions met previously. The results are compared with test cases already known in the literature and future works are suggested. Nonlinear Stability and Optimization Techniques Arthur Cave, USA As is well known, the engineering and applied sciences, the physical and mathematical sciences, and other areas are all somewhat interrelated and dependent to some extent upon stability and optimization techniques. Selected nonlinear stability and optimization techniques are briefly reviewed in terms of their contrasts and inherent relationships with one another. Then examples, different than those developed in ICNPAA-2000, ICNPAA-2002, ICNPAA-2004, ICNPAA-2006 and ICNPAA-2008 are developed to illustrate the techniques. The application areas considered are combinations of the following: 1) Mechanics and Circuits, 2) Estimation and Control, 3) Signal Processing and Communications, 4) Computational Methods. 93 Optimization of an Aeronautical Composite Structure through a Parallel Multilevel Approach Leonardo Dagnino Chiwiacowsky, Universidade do Vale do Rio dos Sinos - UNISINOS, Brazil Paolo Gasbarri, Università di Roma La Sapienza, Italy Haroldo Fraga de Campos Velho, Instituto Nacional de Pesquisas Espaciais, Brazil Arthur Tórgo Gómez, Universidade do Vale do Rio dos Sinos - UNISINOS, Brazil Optimal design of complex engineering systems, such as aircraft composite structures, can often be accomplished only by decomposition techniques. In general, it is characterized by a multidisciplinary task, usually involving multiple objectives, with many design variables and several constraints associated to each one of the disciplines taken into account. One of these techniques is represented by the multilevel approach, where the complex problem of multidisciplinary optimization is solved based on the idea divide and conquer. The original problem is split into several smaller subproblems, making the new configuration inherently suited for parallel and distributed computing. In this paper, the optimal design of a composite wing-box is addressed by using a parallel two-level scheme, where a stochastic method is used to solve each problem level. At the second level, since the changes in the components of one of the subproblems have no influence on the solution of the others, they can be solved simultaneously. In addition, also the stochastic method used in the solution of each problem level is applied in a parallel form. Simulation results have shown that, beyond the reduction of the computation time, the parallel version has provided better results if compared with those provided by the serial version. Efficient Shock Capturing Scheme for Transonic Aerodynamics Hasan Junaid Hasham, China The aim of the paper is to validate the Implicit Finite Difference Method (FDM) based NND scheme to solve Navier-Stokes Equation (NSE). The NND scheme is a sort of TVD scheme with limiter functions. In this case the spatial discretization is 2nd order accurate and the temporal accuracy is also 2nd order accurate. To accelerate the convergence of the coupled system, pseudo-time stepping technique was used. Algebraic turbulence model is used to account for the viscous flow effects. The discretization of residual, namely the spatial derivatives, is very critical to the accurate simulation of transonic flow. The viscous terms are centrally differenced as usual. However, the convection terms are differentiated with NND scheme. The flux vector splitting is done based on the eigenvalues. For positive eigenvalues, backward differencing is used and for negative eigenvalues, forward differencing is used. The steady state solution of this unsteady NSE is performed using Implicit LUSGS. To accelerate convergence pseudo time stepping has also been used. The test case chosen for validation is that of NACA0012 airfoil which is solved on C-type grid with grid density of (x, η) 258 x 43. The results compare well with the published data. Review of Reduced Order Models for CFDCSD Interaction Problems Hasan Junaid Hasham, China Typically a design team would be required to evaluate thousands of parameters so as to finalize the most optimal design. Similarly for stability analysis the evaluation of various flow conditions are required to obtain the complete result. In transonic flight regime these analyses generally require the use of very large high fidelity models which incur large computational cost. To overcome this Reduced Order Models (ROMs) are used. A ROM is any low-order model (small number of DOFs) that retains the characteristics and dynamics of the original system. Another advantage of the ROMs is that they provide any insight to the physics of the problem itself. Many ROM techniques have been used however they are basically classified into two categories. First is finding the global modes of the system and projecting the full system on to the reduced space formed by these modes. The other category is where the system is given input(s) and the outputs are measured. Transfer functions are evaluated to relate the inputs to the outputs. Within these two categories there are many variants in this paper only the ROM techniques that are used in CFDCSD interaction problems of Computational Aeroelasticity are reviewed. 94 Optimal PID Controller Tuning in Missile Design Based on PSO Algorithm Alireza Karami Horestani, Mostafa Lotfi Forushani, Mohamad Hoseinyar Iran In the present paper, a new approach is performed to optimize the tuning of PID controller in missile control system. In fact, the behavior of an aerospace vehicle, such as a missile can be described with a set of non-linear differential equations by assuming six degrees of freedom (three ones for linear motions and the rest for angular motions) around x, y and z axes. Regarding this complexity, designing an effective controller in missiles has been one of the most challenging subjects in optimal control context. On the other hand, the recent optimization methods in parameters tuning of the PID controllers have converted it into one of the most useful methods in missile designing. Here, the PSO algorithm which is one of the most powerful tools in the field of global optimization used for a various range of problems is successfully applied for longitudinal axis control of a missile using MATLAB simulation for optimal tuning of PID controller. At the end, the results of simulations are visualized in figures. Accordingly, the overall system performance has been considerably enhanced due to this new methodology. Effectiveness optimization for a surface-to-air missile system based on MDO Jiang Huan, Chen Wanchun Beijing University of Aeronautics and Astronautics (BUAA), China A multi-tier trajectory optimization framework for a surface-to-missile system is proposed based on the Multi-Tier Optimization Process (MTOP) theory for the system effectiveness optimization. The entire multi-tier trajectory optimization framework is divided into pre-launch phase, the midcourse trajectory optimization, the terminal homing phase and the warhead damaging process. A tier can be seen as a subsystem, the multi-tier trajectory optimization problem is essential a multidisciplinary design optimization (MDO) problem. A solution of the multi-tier trajectory optimization framework is presented based on the MDO theory and methods through discipline analysis and system analysis. The Global Sensitivity Equation (GSE) method and All-in-One method are used to solve the system effectiveness optimization problem, and the results obtained by these methods are given and analyzed. Design and Optimization of Slotted Tube Grain Configuration using Simulated Annealing Ali Kamran, Liang Guozhu Beijing University of Aeronautics and Astronautics (BUAA), China Simulated Annealing is applied in optimization of Slotted Tube grain configuration. We propose CAD based geometry calculation function, to increase calculation accuracy, integrated with a simple ballistic model to calculate performance. CAD representation encapsulate all of the geometric entities pertinent to the grain design in a parametric way, allowing manipulation of grain entity (web), performing regression and automating geometrical data calculations. Average thrust is the impetus driver on performance, so considered as objective of grain design process. It is demonstrated with a constrained optimization for Slotted Tube grain using simplified internal ballistics model that maximizes average thrust for minimal deviations from neutrality. Design and Optimization of Star Grain Configuration using Simulated Annealing Ali Kamran, Khurram Nisar, Amer Farhan Rafique, Qasim Zeeshan Beijing University of Aeronautics and Astronautics (BUAA), China Grain Design is most imperative in completing the design of any Solid Rocket Motor (SRM). Recently authors have considered the grain design and optimization using evolutionary optimization techniques but still the potential of using meta-heuristic search algorithms like Simulated Annealing (SA) for the design and optimization of SRM grains has not yet been gauged. This paper presents a design methodology for efficient design of complex Solid Rocket Motor (SRM) Grains involving computationally intensive analysis with number of design variables. A technique has been proposed to design and analyze the Star grain geometry and thereafter extract optimal solution of the SRM grain using Simulated Annealing (SA). Maximum Thrust has been computed as the objective function with constraints of burning time and propellant mass while remaining within fixed length and diameter of grain. The performance of proposed methodology is investigated in this paper for the designing, analysis, performance prediction 95 and optimization of 2 D grain design using Star configuration for Solid Rocket Motors that can be used for various missile systems and space launch vehicles. The results show that all desired functions have been achieved and an optimal design has been attained qualifying all ballistic parameters. Sensitivity analysis of an aircraft shell panel with geometry imperfections Airton Nabarrete , Francisco Scinocca Instituto Tecnológico de Aeronáutica - ITA Frequency response analysis of an aircraft shell panel subject to geometry imperfections using a probabilistic approach was evaluated. A stochastic finite element model was developed and implemented applying the Monte Carlo Method to perform several spectral distributions and obtaining non-deterministic results. This work extends the previous results obtained with the buckling instability analysis for an aircraft plate panel. In this research, the investigation considers the variations for the shell panel geometry and material properties. In order to observe the major contributors, a sensitivity analysis was performed. The modal results and the frequency response function variations are presented. Experimental Study of Laminar Horseshoe Vortex Using PIV Zaw Zaw Oo, Muhammad Yamin, Hua Zhang China The study provides topological analysis of juncture flows generated by the cylindrical body mounted on a flat plate using PIV (Particle image velocimetry) technique. Various vortex structures are predicted for ReD (Diameter Reynolds number) ranging from 500 to 2500. The vortex structures and their variation with the change of ReD is discussed in detail. Experiments were conducted to investigate the effect of various Reynolds number and the variation of the height of the cylinder aspect ratio (H/T) on hydrodynamics performance of three-dimensional flat plate and circular cylinder. Both steady and periodic laminar horseshoe vortex flows generated upstream of a cylinder/flat plate juncture is presented. As the flow approaches the cylinder, the adverse pressure gradient produces three-dimensional boundarylayer separation, resulting in the formation of laminar horseshoe vortices. The standard or classical type of laminar horseshoe vortex topology is identified. Trajectory Optimization of Air Launched Satellite Launch Vehicle using Genetic Algorithm Amer Farhan Rafique, Beijing University of Aeronautics and Astronautics (BUAA), China Powered flight phase dictates the performance of any launch vehicle. Good ascent guidance can help in reducing cost, reducing load indicators, and consequently increase its performance. The powered flight of Air Launched Satellite Launch Vehicle is divided in several phases. After a short horizontal launch phase, the vehicle undergoes a launch maneuver by introducing a carefully selected Angle of Attack profile. Flight Program is optimized under the constraints of the maximum allowed AOA, lateral and axial overloads. The main focus of this study is the endo-atmospheric phase of the ascent trajectory. To analyze the ascent fight-path, a three degree-of-freedom 3DOF trajectory model is modeled in SIMULINK. Genetic Algorithm is used to optimize the Flight Program, as it is better suited in view of the efficiency of global search performance. In this paper the proposed design optimization approach is applied to design the trajectory of Air Launched Satellite Launch Vehicle and the performance index is the altitude achieved. The method described in this paper provides the designer with a simple yet powerful approach to the ascent trajectory optimization. Development of a new algorithm for optimization of closed-loop liquid rocket engines Davood Ramesh, Iran The reduction of Liquid Rocket Propulsion System (LRPS) conceptual design costs in conjunction with an increase in engines performance caused to develop a noticeable engineering software to simulate and optimize LRPS with staged combustion cycle and oxidizer rich pre-burner. An enabling static mathematical modeling core feature of this tool has the ability to rapidly produce closed solutions for engine power balance and engine independent parameters (combustion chamber pressure, combustion chamber mixture ratio, expansion ratio of turbine nozzle and etc.) with respect to maximize performance (specific impulse as objective function) of LPRS and managed to select optimum regime. 96 Finally, it must be finalized selection of optimum regime or optimum parameters. The developed algorithm has applied for RD-253 engine, and results have compared with the modified RD-253. According to the developed algorithm, a software is written in the modern engineering, object-oriented Compaq visual Fortran 6.6 programming language. Execution times are approximately 5 to 10 seconds. Robust Design Optimization of Booster Phase Energy Management of Dual Thrust Propulsion System Muhammad Aamir Raza, Northwestern Polytechnical University Xian, China The regularization of energy management program of dual thrust solid rocket motor is considered. Indepth analysis of energy constituting parameters in booster phase of dual thrust solid rocket motors shows that there is uneven rise and fall in chamber pressure. Among other factors, this pressure behavior is found to be associated with the design variables constituting the grain geometry in booster phase. The uncertainty and variation in grain geometry causes loss in booster energy in terms of maximum average thrust and total impulse. A robust design frame work is proposed based on hybrid optimization of Genetic Algorithm followed by Simulated Annealing. To increase the optimization efficiency, design of experiment employing uniform Latin Hypercube Sampling is used. The sensitivity analysis is done using Hadamard matrices approach. The optimal design solution is perturbed with different variation levels to reach robust design optimization using random Monte Carlo simulation. The suggested scheme shows excellent results to ameliorate the design space to reach the right set of design parameters which is insensitive to booster phase performance. Parametric Design Approach for Aero-performance of Hypersonic Reentry Body Muhammad Amjad Sohail, Yan Chao, Zahid Maqbool Beijing University of Aeronautics and Astronautics, China This research effort presents the parametric studies of different shapes of reentry vehicle with different radii and cone half angles. Higher order low dissipative scheme verifies the simulated results with experimental data. All simulations are at high Mach number and shock parameters determined using shock capturing technique. The patterns of shock waves and aerodynamics performance are studied for varying radius and cone angle. We performed simulations for 12 geometries, with varying tip and base radius, at Mach 5.9 and angle of attack -4, -2, 0, 2, 4, 6, 8, 10, 12 deg. Based on results, we intend to compute the aerodynamics coefficients and best lift to drag ratio geometry. Inviscid and Viscous Computation on Aerodynamic Characteristics of a Conventional Projectile with and without Fins Configuration by using Flux Difference Scheme Muhammad Amjad Sohail, Yan Chao, Zahid Maqbool M. Yamin Younis, Muhammad Afzal, Mukkarum Hussain Beijing University of Aeronautics and Astronautics, China The performances of Inviscid model, viscous turbulence K-ω SST turbulence model and high order low dissipative Flux difference scheme of Roe are evaluated against experimental flow fields at different geometries and angle of attacks at supersonic Mach numbers. Inviscid and viscous effects on cylindrical body with and without fins are described and discussed in detail. The numerical predictions include lift, drag and pitching moment coefficients at different angle of attacks and Mach number. Most significantly, this research provides a sensitivity study on the accuracy of the solutions with respect to the effects of free stream turbulence, grid resolution, grid spacing near the wall, initial conditions, numerical methods and free stream Mach number effects on compressible flows. Comparison of two geometries, cone cylinder and cone cylinder with fins is provided in order to study the effects on the aerodynamics characteristics by the addition of the lifting surfaces and the same is compared with the available experimental data. For the present study supersonic flow is simulated at Mach number 4 and the angle of attack is varied. First calculation are done on inviscid modeling and using Flux difference scheme of Roe which is first order accurate but limiters are used to get higher order accuracy and suppress the oscillations in high pressure gradient flows and in discontinuity regions. First order scheme produces oscillations and unstable solutions in discontinuities and shocks. Then results obtained from these inviscid calculations are under predicted so viscous turbulent modeling of K-ω SST model of Menter is used to capture the viscous and turbulence effect of flows. It was observed that inclusion of viscous effect increase the accuracy of 97 the solutions and results have very good agreement with the experimental results. Roe TVD scheme and limiters are successfully implemented for supersonic flows and hyperbolic equations. Three different types of limiters are used here to get second order accuracy and to stable the solutions near shock and in discontinuous regions. Cone-cylinder body (with and without fins) is used for the above methodology to simulate the flows for inviscid and viscous flows and results for both these two cases are obtained at mach 4 and at different angle of attacks. The results have very good agreement with experimental results. Comparison Study of Geometrically and Numerically Regression of the Star Grain Design for SRM Soe Hlaing Tun, Xiang Hong Jun Beijing University of Aeronautics and Astronautics (BUAA), China When the neutral burning characteristic with respect to time is needed in a mission, star grain geometry of solid propellant is used. Most of the grain regression is done by the geometric evolution analysis during its combustion. In this study, we present the comparison of the regression of two dimensional star grain geometry of a solid rocket motor by geometrical and numerical approach. In the geometric evolution technique, it is required to predefine the evolution zones to estimate the internal ballistics of the rocket motor before the grain regression occurs. But using the numerical method, no predefined zones are needed while it gives close result to that of the previous one. Both methods are based on the principle that burning will occur in the normal direction of the solid propellant surface. Implementation, Validation and Testing of an Inverse Design Tool for Redesigning NACA 65-410 Wing Profile Árpád Veress , András Nagy , József Rohács BME, Department of Aircraft and Ships, Hungary Two dimensional Euler equations based compressible flow solver has been implemented, validated and extended for inverse design applications. The inverse design method, as usual, consists of three main steps; direct, inverse and wall modification algorithm. The emphasis has been placed on the developments of an accurate, robust and fast method with the capability of providing solutions for a wide range of target pressure distributions as it is going to be a part of the optimization tool in the next steps. In case of the inverse design problems, the existence of the geometry belongs to an arbitrary target pressure distribution is not straightforward. There are several problems, e.g. the cross over of the pressure and suction side, which are often a part of the solution. Numerical investigations have been completed to find the basic mechanism of the unwanted phenomena and a practical solution has been proposed to overcome the problem. NACA 65-410 profile has been used for the validation over the wing and cascade flows. The inverse design method with the proposed improvements is tested by imposing several arbitrary target pressure distributions around the wing profile. The lift coefficients of the original and redesigned geometry are compared with each other. Study on Random Initial Point Trajectory Planning for Missile Borne Unmanned Air Vehicle Wang Wei, Wang Hua, He LinShu Beijing University of Aeronautics and Astronautics (BUAA), China As the location and velocity direction of the initial point for missile borne unmanned air vehicles projected from missile is random, the hierarchical trajectory planning idea is proposed: global trajectory planning off-line first and then partial trajectory planning on-line. A partial trajectory planning method is presented, in which a geometric analysis method is adopted in the horizontal plane and cubic spline method is adopted in the vertical plane to plan the beginning part of the trajectory on -line. It can satisfy the dynamic constraints for the initial and cut-in point, and it is simple and quickly, so as to meet real-time request. The simulation results show that the proposed method is efficient and has a certain engineering value. 98 Optimization of Free-Flying Time between Two Joined Stages for Solid-Fuel Ballistic Missile Htoo Hlaing Win, LinShu He Beijing University of Aeronautics and Astronautics (BUAA), China Optimization of free-flying times between two consecutive stages to enhance the overall range of threestage solid ballistic missile conceptual design is presented herein. Free-flying time is of great importance in enhancing final range of missile. For a given optimized mass of vehicle, the range is maximized by considering different free-flying times between first stage burn-out and second stage ignition as well as between second stage burn-out and third stage ignition. Mathematical modeling is performed in SIMULINK. Genetic Algorithm is used as optimizer to get the optimum settings of free-flying times for maximum range. Application of Sensitivity Region Based Robust Design Approach in MDO of Flight Vehicle Ma Ying, He LinShu Beijing University of Aeronautics and Astronautics (BUAA), China A novel robust design method was applied to multi-disciplinary design optimization of a flight vehicle. Math model of the robustness method based on concept of worst case sensitivity region (WCSR) was introduced. The proposed system was divided into five sub-disciplines according to design mission, namely structure, weight, aerodynamics, propulsion and trajectory. Analysis models were established in different professional tools. MDO model was built by integrating sub-disciplines into one framework. The dataflow in the framework was described. Traditional optimization method and WCSR based robustness method were both conducted. The robustness scheme was found without any presumed probability distribution of design variables, and compared to the traditional optimum scheme. The objective variation of robust scheme was limited in acceptable range while the system feasibility was maintained. The novel robustness method is suitable for typical robust optimization problem of flight vehicle design, in which the probability distribution and gradient information are not available. Integrated Multidisciplinary Design and Multi-Objective Optimization Approach for Space Launch Vehicle Naeem Zafar, He LinShu School of Astronautics, BeiHang University, China This paper proposes an approach for the integrated design and optimization of space launch vehicle, wherein the structure/weight, aerodynamics, propulsion and the trajectory system design are performed simultaneously. The integrated design problem is posed as an optimization problem in which all the discipline parameters constitute the design variables, which are used to optimize the multi-objective function, thereby resulting in an optimal overall design. The approach is demonstrated by application to the integrated design of a four stage solid launch vehicle. This work addresses three objectives for the design process: the minimization of total liftoff weight, total constraint violation and the minimization of differences between the actual and desired orbital parameters. The mission is to deliver predefined payload to the low earth (circular) orbit. An existing, real world system has been used to validate the multistage launch vehicle system model. Constraint Handling Approach using Multi-Objective Evolutionary Optimization Naeem Zafar, He LinShu School of Astronautics, BeiHang University, China This paper presents a new constraint handling scheme based on non-dominated sorting and crowding distance sorting theme. The proposed method treats the constraints as objective functions and handles them using the concept of NSGA-II. The approach does not require the use of a penalty function and it does not need niching to maintain diversity in the population. We validated the algorithm using several test functions taken from the specialized literature and compared the results with respect to algorithms representative of the state-of-the-art in the area. Results indicate that proposed scheme is a highly competitive alternative to solve constraint optimization problem. 99 Index ABBATE, Horacio A., 36 ABDELLA, Kenzu, 33 ACOPYAN, Vladimir A., 91 ADESINA, Olufemi Adeyinka, 47 AFZAL, Muhammad, 97 AKCA, Haydar, 40 ALCORTA-GARCIA, Maria Aracelia, 51 ALEYAN, Omar Ali, 33 ALLAHVIRANLOO, Tofigh, 33 ALLAUDIN, Mohd Faizal, 81 AMARAL, Ricardo Franco, 70 AMIRI, Shahin Nayyeri, 33 ANAVATTI, Sreenatha, 41 ANGUIANO-ROSTRO, Sonia Guadalupe, 51 ARAKAKI, Julio, 57 ARANTES Jr., Gilberto, 81 ARAUJO, Wagner Leite, 64 ASATO, Osvaldo Luis, 57 ASHOURIAN, Mohsen, 62 ATTIA, Sid Ahmed, 81 AXENOV, Vladimir N., 91 AZADI, E., 51 AZADI, M., 51 BAGHDADI, Mohamed Nadjib, 69 BAHGAT, Ahmad, 84 BAJODAH, Abdulrahman Hasan, 86 BALAKRISHNAN, A.V., 28 BALAKRISHNAN, S.N., 28 BALINT, Agneta Maria, 34 BALINT, Stefan, 34, 38 BALKAN, Demet, 38 BALTHAZAR, José Manoel, 28, 35, 67, 70, 73, 88, 91 BALVEDI Jr., Eulo Antonio, 69 BAMBACE, Luis Wwaack, 34, 93 BARBANTI, Luciano, 67 BARONI, Leandro, 82 BARROS, Graiciany P., 64 BECCENERI, José Carlos, 93 BEHESHTI, Mohammad Hossein, 82 BELGACEM, Fethi Bin Muhammad, 34 BENDIKSEN, Oddvar O., 69 BHOSALE, Bharat Namdeo, 45 BIDEL, Antonio L., 70 BINDEL, Daniel, 81 BISWAS, Anjan, 45 BRONZI, Anne Caroline, 49 BUENO, Atila Madureira, 35 CACHUTÉ, Liomar de Oliveira, 86 CAMARGO, Vanessa Avelino Xavier de, 35 CAMPOLINA, Daniel, 65 CAMPOS, Tarcisio Passos Ribeiro, 64 CANTU, Hector Flores, 51 CAO, Ma, 50 CARDOS, Vladimir, 51, 52 CARRARA, Valdemir, 77, 82, 83 CARVALHO, Leopoldo Bulgarelli, 35 CASTÃO, Kleber Augusto Lisboa, 70 CASTRO, Luis, 67 CAVALHEIRO, Andre Cesar Martins, 59 CAVATONI, André, 65 CAVE, Arthur, 93 CERVANTES, Ilse Camacho, 86 CHAO, Yan, 97 CHAVARETE, F.R., 88 CHAVARETTE, Fábio Roberto, 91 CHIWIACOWSKY, Leonardo D., 90, 94 CHU, Qi-Ping, 62, 92 CLAEYSSEN, Julio R., 70 COPETTI, Rosemaira D., 70 COSTA, Antonella Lombardi, 64–66 COSTA, Cristiano da Silva, 58 COSTA, Esdras Teixeira, 35 COVACHEV, Valery, 40 COVACHEVA, Zlatinka, 40 COVEI, Dragos-Patru, 49 CUBILLOS, Ximena, 83 CUNHA, Renan, 65 DA FONSECA, Ijar Milagres, 84 DA SILVA, Clarysson A. Mello, 65, 66 DA SILVA, Roberto Gil Annes, 69, 70 DAMASCENO, Berenice Camargo, 67 DE ASSIS, Sheila Crisley, 75 DE MARQUI Jr., Carlos, 72 DE MICCO, Luciana, 88 DE MORAES, Rodolpho Vilhena, 75, 77 DE OLIVEIRA, Élcio Jeronimo, 84 DE OLIVEIRA, Pedro P.B., 35 DE VISSER, Cornelis, 60 DE WEERDT, Elwin, 92 DEL RIO, Ezequiel, 53 DIAS, Márcio Souza, 59 DIAS, Susana, 83 DIMBOUR, William Edmond, 56 DIXIT, Nagaraj, 78 DONOSO, Jose Manuel, 53 DOS SANTOS, Fábio Luis Marques, 36 DOWELL, Earl H., 71 DUARTE, Ricardo Oliveira, 83 DUMITRACHE, Alexandru, 52 DUMITRESCU, Horia, 51, 52 ELASKAR, Sergio, 53, 87 ERDOGAN, Fevzi, 47 FANG, Jiancheng, 43, 44 FARAAG, Ahmad, 84 FARAHANI, Mohammad, 89 FARHAT, Nabil H., 40 FAZELZADEH, S. Ahmad, 51, 71 FEIJOO, Juan Alejandro Vazquez, 71 FELIX, Jorge L.P., 91 FELIX, Luiz Palacios, 88 FENILI, André, 87 FERNANDES, Sandro Da Silva, 29, 79 FILHO, Diolino Jose dos Santos, 57–59 FILHO, Edmundo Alberto Marques, 40 FILHO, Waldemar de Castro Leite, 84 FLEK, Michail B., 91 100 FORUSHANI, Mostafa Lotfi, 60, 88, 95 FRANCISCO, Alexandre Lacerda Machuy, 75 FRANCISCO, Cayo Prado Fernandes, 87 FRUNZULICA, Florin, 52 GADELHA, Luiz, 83 GARCIA, Roberta Veloso, 76 GARCIA-TABERNER, Laura, 76 GARRATT, Matthew, 41 GASBARRI, Paolo, 94 GHAYOUR, Mostafa, 90 GHIA, Karman, 42 GHIA, Urmila, 42 GILBERTI, Mauricio, 65 GIRAUDO, Pedro S., 36 GIULIATTI WINTER, Silvia, 29 GOES, Luiz Carlos Sandoval, 36, 70, 73 GOMES, Vivian M., 76 GOMES, Willer, 77 GOMEZ, Arthur Tórgo, 94 GONZALEZ, Leandro, 36 GUERMAN, Anna, 83 GUOZHU, Liang, 95 HADZIBEGANOVIC, Tarik, 41 HAMEDUDDIN, Ismail, 86 HASHAM, Hasan Junaid, 94 HERRERA-VALENCIA, Edtson Emilio, 49 HILTON, Harry H., 73 HORESTANI, Alireza Karami, 88, 95 HOSEINI, Hanif Sadat, 71 HOSEINYAR, Mohamad, 60, 95 HOSSEINI, Ebrahim, 62 HOVAKIMYAN, Naira, 29 HUA, Cao Yi, 50 HUA, Wang, 98 HUAN, Jiang, 95 HUNTER, Joyce A., 36 HUSSAIN, Mukkarum, 97 IGAWA, Hirotaka, 73 JAGADEESH KUMAR, M.S., 49 JAWORSKI, Justin W., 71 JESKE DE FREITAS, Joslaine Cristina, 57 JESUDASON, Christopher Gunaseelan, 55 JULIA, Stéphane, 59 JULIA, Stephane, 57 JUN, Xiang Hong, 98 JUNQUEIRA, Fabricio, 57–59 KALOYANOVA, Valentina, 42 KAMRAN, Ali, 95 KARIMI, Bahran, 88 KASAYNOV, Vladimir Alexandrovich, 61 KASLIK, Eva, 41 KENNERLY, Sam, 37 KHALIQUE, Chaudry Masood, 45 KIRR, Eduard-Wilhelm, 55 KLINKE, Ana Rosa, 88 KOMANDURI, Ananth, 81 KORGUL, Artur, 37 KORGUL, Rafal Andrzej, 37 KUGA, Hélio Koiti, 40, 76–78, 82, 83 KUKREJA, Sunil L., 30, 63 LARRONDO, Hilda Angela, 88 LASIECKA, Irena, 30 LIANG, Jin, 56 LIMA, Francisco Welington, 41 LINSHU, He, 98, 99 LIU, Fengshan, 46 LOWENBERG, Mark, 42 LUBER, Wolfgang, 72 LUISO, Javier E., 36 MACAU, Elbert, 31 MAGLIONE, Livio, 87 MAJEE, Narayan Chandra, 41 MANSHADI, Mojtaba Dehghan, 89 MAQBOOL, Zahid, 97 MARCELINO, Eliel Wellington, 79 MARQUES, Flávio D., 72 MARTIN, Olga, 52 MARTINEZ, Mariano, 87 MARTINS-FILHO, Luiz de Siqueira, 81, 83 MASDEMONT, Josep J., 76 MATTHEIJ, Robert M.M., 31 MECITOGLU, Zahit, 38 MELO, Jose Isidro Garcia, 58, 59 MERRETT, Craig G., 73 MILUTINOVIC, Janko, 37 MIYAGI, Paulo Eigi, 57–59 MOKHTARI, Abolfazl, 42 MOPHOU, Gisèle, 56 MULDER, Bob, 62 MULDER, J.A., 92 MWONGERA, Victor Mwenda, 42 N’GUÉRÉKATA, Gaston Mandata, 56 NABARRETE, Airton, 61, 96 NAGY, András, 43, 98 NAGY, Endre, 60 NAKAMOTO, Francisco Yastami, 58 NAKAMURA, Toshiya, 31, 73 NANNAN, Zhang, 50 NARAYANA, Mahesha, 50 NAZARI, Sam, 89 NAZIDI, Abbas, 71 NETO, Atair Rios, 40 NISAR, Khurram, 95 NOVOZHILOV, Vasily, 37 OLIVEIRA, Thais Carneiro, 77 OMEIKE, Mathew Omonigho, 48 OO, Zaw Zaw, 96 PARDAL, Paula C.P.M., 77 PEREIRA, Claubia, 64–66 PESSOA, Marcosiris Amorim de Oliveira, 58 PICCIRILLO, Vinı́cius, 73 PIQUEIRA, José Roberto Castilho, 35 POKRAJAC, Dragoljub, 37 POPESCU, Mihai, 53 PRADO, Antonio F.B.A., 75–77, 79, 80 PRASAD, Rajendra P., 78 PRATOMO, Ariel, 81 PUTTANNA, Vishwanath Kadaba, 50 101 RABELO, Marcos, 56 RAFFIE, Ahmad, 84 RAFIQUE, Amer Farhan, 95, 96 RAMAZOTTI, Rodrigo Bassinello, 89 RAMESH, Davood, 96 RAMOS, Wemerson Leonardo, 35 RAZA, Muhammad Aamir, 97 REHMAN, Masood Ur, 84 REIS, Patrı́cia A.L., 64 REZVANI, Vahid, 84 RIBEIRO, Marcos Wagner Souza, 35 RICCI, Mário César, 78 RIEHL, Roger Ribeiro , 86 ROCCO, Evandro Marconi, 77, 79, 80 ROHÁCS, József, 43, 61, 98 ROJAS, Edixon, 67 ROY, Amiya Busan, 41 SABIHI, Ahmad, 38, 89–91 SAITOH, Saburou, 68 SALEHI, Hamid, 90 SALEHI, Mehdi, 90 SAMAL, Mahendra Kumar, 41 SANGARASHETTAHALLY, Ashoka B.G., 50 SANTOS, Leonardo B. L., 90 SATHISH KRISHNAN, P.S., 61 SCINOCCA, Francisco, 61, 96 SERPA, Alberto Luiz, 36 SHAFAI, Bahram, 89 SHAHGHOLIAN, Ghazanfar, 88 SHEVTSOV, Sergey N., 91 SIBILSKI, Krzysztof Slavomir, 43 SIDDHESHWAR, Pradeep Ganapathi, 49, 50 SIDDIQUI, Saman Mukhtar, 43, 44 SILVA, Anabela, 68 SILVA, Fabiano Cardoso, 66 SILVA, Núbia Rosa, 59 SILVA, Priscilla Andressa de Sousa, 53, 80 SILVEIRA, Carlos, 79 SINGH, Suresh G., 49 SIVASUNDARAM, Seenith, 41 SMIRNOV, Georgi, 83 SOHAIL, Muhammad Amjad, 97 SQUILLANTE Junior, Reinaldo, 59 STROE, Ion, 53 STUCHI, Teresinha de Jesus, 75 SUKHANOV, Alexander A., 79, 80 TURKMEN, Halit Suleyman, 38 TUSSET, Angelo Marcelo, 91 UDWADIA, Firdaus E., 31 UNGUREANU, Viorica Mariela, 54 USMONOV, Botir, 74 VALE, Liliane Nascimento, 59 VALETTE, Robert, 57 VAN KAMPEN, Erik-Jan, 62 VAN OORT, Eddy, 92 VARATHARAJOO, Renuganth, 81 VASSILYEV, Stanislav N., 32 VAZIRY, Mohammad Ali, 89, 90 VELHO, Haroldo Fraga de Campos, 90, 94 VELOSO, Maria Auxiliadora Fortini, 64–66 VENDITTI, Flaviane, 80 VERESS, Árpád, 98 VERGARA, Fany Mendez, 86 VIO, Gareth A., 62 WANCHUN, Chen, 95 WEI, Wang, 98 WHITE, Brian, 32 WIN, Htoo Hlaing, 99 WINTER, Othon C., 32 WYLLER, John, 41 WYNN, Aung Ko, 50 XIAO, Ti-Jun, 56 XIE, Dejun, 63 YAMIN, Muhammad, 96 YING, Ma, 99 YOUNIS, M. Yamin, 97 ZAFAR, Naeem, 99 ZAKERZADEH, Mohammad Reza, 90 ZANARDI, M.C., 76 ZAPICO, Eduardo N., 36 ZEESHAN, Qasim, 95 ZENG, Jie, 63 ZHANG, Guoping, 46 ZHANG, Hua, 96 ZIAEI-RAD, Saeed, 90 TALEBI, Omid, 91 TAMAGNO, José, 87 TAMAYAMA, Masato, 74 TANASIE, Loredana, 38 TEHRANI, Omid Sharifi, 62 TENGIZ, Ertan, 38 TERRA, Maisa de Oliveira, 53, 75, 80 TIMOFTE, Claudia, 54 TITA, Volnei, 72 TODOROV, Michail D., 46 TORRES, Mauricio Torres, 51 TRIGGIANI, Roberto, 55 TSUKAZAN, Teresa, 70 TUN, Soe Hlaing, 98 TUNÇ, Cemil, 48 102 ICNPAA10 has been organized with the support of Brazilian Institute for Space Research Coordenação de Aperfeiçoamento de Pessoal de Nível Superior Cambridge Scientific Publishers, Cambridge, UK Fundação de Amparo à Pesquisa do Estado de São Paulo International Federation of Information Processing International Federation of Nonlinear Analysts Map of INPE area Institute of Electrical and Electronics Engineers American Institute of Aeronautics and Astronautics Wolfram Research