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Sentinel-1 - Emits
COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 2 of 76 Intentionally blank EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 3 of 76 Contents 1. INTRODUCTION ...........................................................................................................................................5 1.1 Scope .....................................................................................................................................................5 2. APPLICABLE DOCUMENTS ........................................................................................................................5 2.1 Normative Documents............................................................................................................................5 2.2 Informative Documents ..........................................................................................................................5 3. ACRONYMS AND ABBREVIATIONS ...........................................................................................................6 4. DEFINITIONS ..............................................................................................................................................34 4.1 System..................................................................................................................................................34 4.2 C-SAR Instrument ................................................................................................................................36 4.3 Spacecraft and Platform.......................................................................................................................42 4.4 Ground Segment ..................................................................................................................................45 4.5 Lifetime .................................................................................................................................................52 5. BACKSCATTERING MODEL......................................................................................................................54 5.1 Terrain ..................................................................................................................................................54 5.2 Ocean ...................................................................................................................................................54 6. REFERENCE FRAMES ..............................................................................................................................56 7. SPACECRAFT NOMINAL MODES & POINTING DEFINITIONS...............................................................60 8. PHASE AND AMPLITUDE ERRORS..........................................................................................................62 8.1 Absolute Within Pulse Errors................................................................................................................63 8.2 Relative Within Pulse Errors.................................................................................................................63 8.3 Pulse to Pulse Errors over Coherent Subaperture...............................................................................63 8.4 Stability over time intervals...................................................................................................................65 9. OTHER DEFINITIONS ................................................................................................................................66 10. ECSS TERMS ...........................................................................................................................................69 10.1 ECSS-E-10-02A .................................................................................................................................69 10.2 ECSS-E-10-03A .................................................................................................................................70 10.3 ECSS-E-20A.......................................................................................................................................74 11. COMMERCIAL ..........................................................................................................................................75 EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 4 of 76 Intentionally blank EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 5 of 76 1. INTRODUCTION 1.1 Scope This document lists acronyms, abbreviations and definitions relevant to the Sentinel-1 SES programme context. Acronyms and abbreviations appear as a single list in alphabetical order in section 3. Specific Sentinel definitions appear in section 3. Also included are the definitions of the Backscattering Model, Reference Frames and spacecraft Modes and Pointing taken from IRD01. In addition, definitions from certain ECSS standards are given. The document concludes with some commercial definitions. 2. APPLICABLE DOCUMENTS 2.1 Normative Documents None 2.2 Informative Documents IRD01 ES-RS-ESA-SY-0001 issue 1.1 System Requirements Document IRD02 H. Fiedler, E. Boerner, J. Mittermayer, G. Krieger. “Total Zero Doppler Steering”. Paper submitted for patent. German Aerospace Center (DLR) EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 6 of 76 3. ACRONYMS AND ABBREVIATIONS A A/D AAA AB ABCL ABD AC ACCD ACF ACG ACK ACQ AD AD ADC ADD ADP AF AFT AGC AHA AHT AIT AIV AIVT AL ALOS AM AME AMI AN ANC AND ANSI Ant AO AOCS AOS AOS AOS APE APG API APID APM APO APSYS AR Analogue to Digital Active Array Antenna Arbitration Board As Built Configuration List Airborne Demonstrator Alternating Current Accumulation Charged Coupled Device Archive and Catalogue Facility Analyse, Change, Generate Acknowledgement Spacecraft Acquisition Mode Analogue to Digital Applicable Document Analogue to Digital Converter Architectural Design Document Acceptance Data Package Acquisition Facility Abbreviated Function Test Automatic Gain Control Actuator Hinge Assembly Accurate Housekeeping Temperature Assembly Integration and Test Assembly, Integration and Verification Assembly, Integration, Verification and Test Acceptance Levels Advanced Land Observing Satellite Amplitude Modulated Attitude Measurement Error Active Microwave Instrument ANalog acquisition interface Analogue conditioned Alphanumeric Displays American National Standards Institute Antenna Announcement of Opportunity Attitude and Orbit Control System Acquisition of Signal Advanced Orbiting Systems Availability Of Signal Absolute Pointing Error Antenna Pattern Generator Application Program(ming) Interface Application Process Identifier Antenna Pattern Modelling Antenna Pattern Optimisation Software Antenna Pattern Synthesis Software Acceptance Review EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 ARB ARE AS ASAR ASCII ASH ASIC ASM ASM ASR AST ASW ASY AT ATM ATOX ATP ATS ATT AU AWG B b B B/U BA BAQ BATT BB BB BBE BBIC BC BCT BD BER BEX BGA BIT BLD BM BNR BOL BP BPS/bps BPSK BR BRC BRP BST S1-LI-ASU-PL-0011 Issue 1 Page 7 of 76 Anomaly Review Board Absolute Rate Error Antenna Subsystem Advanced Synthetic Aperture Radar (sensor onboard ENVISAT) American Standard Code for Information Interchange Acquisition and Safe Hold Application Specific Integrated Circuit Assembly Manager Attitude Steering Mode Array Switching Regulator Autonomous Star Tracker Application Software Assembly Acceptance Level Test Atmospheric Atomic Oxygen Automatic Test Procedure Acquisition and Transcription System Attitude Astronomical Unit American Wire Gauge bit Byte (eight bits) Backup Baffle and Thermal Hardware Block Adaptive Quantisation Battery Baseband Breadboard Base Band Equipment BBE Interconnect Bus Controller Beam Control Table Block Diagram Bit Error Rate Beam Expander Ball Grid Array Built In Test Bilevel Digital Balance Mass Bus Non Regulated Beginning Of Life Basic Product Bits per Second B-Phase Shift Keying (modulation method) Bus Regulated Basic Repeat Cycle Back Relief Pressure Beam Steering Table EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 BSW BUSW BW C C&C CAB CAD CADM CADU CAE CAF Cal CAN CAPS CAT CBCP CBH CBS CBS CCB CCD CCE CCGA CCN CCS CCSDS CD CD CD, CD-R CDAS CDKP CDMU CDR CD-ROM CDS CE CE CE CEOS CESS CESS CETeF CF CFE CFI CFRP CGE CHAMP CHKA CHT S1-LI-ASU-PL-0011 Issue 1 Page 8 of 76 Basic Software Boot-up S/W Bandwidth Command and Control Change Appeal Board Computer Aided Design Configuration And Data Management Channel Access Data Unit Computer Aided Engineering Cluster Angewandte Fernerkundung Calibration Controller Area Network C-SAR Antenna Power Supply Category Current Baseline Cost Plan Cat Bed Heater Cost Breakdown Structure Standard OBDH Bus Coupler (French version) Configuration Control Board Configuration Control Document Control Circuit Encoding Ceramic Column Grid Array Contract Change Notice Command & Control Subsystem Consultative Committee for Space Data Systems Coefficient of Drag Collision Detection Compact Disk – Recordable Command and Data Acquisition Station Critical Design Key Point Control and Data Management Unit Critical Design Review Compact Disc Read Only Memory Correlated Double Sampling Central Electronics Chip Enable Conducted Emissions Committee on Earth Observation Satellites Coarse Earth and Sun Sensor Central Electronics Subsystem Central European Test Facilities Catalogue Facility Customer Furnished Equipment Customer Furnished Item Carbon Fibre Reinforced Plastic Calibration Ground Equipment CHAllenging Mini-satellite Payload Short-tem History Housekeeping Archive Coarse Housekeeping Temperature EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 CI CI CI CI-DDR CIDL CIL CIP CIR CI-TRR CL CLCW CLS CLTU CM CM CM CMCF CMD CME CMOS CMP CMS CNC CoC CoG CoM COMMS COMP COP CORE COS COTS CP CP CP CP CPDU CPS CPT CPU CQFP CR CR CRB CRC CRC CRD CRESS CRP CS S1-LI-ASU-PL-0011 Issue 1 Page 9 of 76 Cloud Imager Configuration Item Critical Items Critical Items Detailed Design Review Configuration Item Data List Critical Item List Catalogue Interoperability Protocol Consolidation Phase Intermediate Review Critical Items Test Results/Readiness Review Current Limiter Command Link Control Word Clear to Send Command Link Transmission Unit Centre of Mass Common Mode Configuration Management Central Monitoring and Control Facility Command Coefficient of Moisture Expansion Complementary Metal Oxide Semiconductor Configuration Management Plan Coordination and Management System Computer Numerical Control Certificate of Conformance/Conformity Centre of Gravity Centre of Mass Communications Complement Command Operation Procedure Common Radar Elements Checkout System Commercial Off-The-Shelf Central (or Control) Processor Change Proposal Cold Plate Commissioning Phase Command Pulse Distribution Unit Combined Propulsion Sub-system Comprehensive Performance Test Central Processing Unit Ceramic Quad Flat Pack Change Request Corner Reflector Change Review Board Cyclic Redundancy Code Cyclic Redundancy Check Customer Requirements Document CORE Radar Electronics Subsystem Contingency Recovery Procedure Chip Select EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 CS CSA C-SAR CSG CSI CSL CSN CSSRD CT CTC CTC CTE CTRL CTS CVCM CVD CVM CW CWL D DA DAC DAC DAM DAP DAS DAS DA-SP DAT DataNet DB dB DBMS DC DCE DCG DCL DCM DCN DCP DCR DCU DD DD&AIV DDF DDF DDVP DE DEC DEM S1-LI-ASU-PL-0011 Issue 1 Page 10 of 76 Conducted Susceptibilities Contact Surface Area C-Band SAR Clock Signal Generator Customer Source Inspection Configuration Status List Calibration Switching Network Customer Services Support Requirements Document Calibration Target Calibration Target Control Cost to Completion Coefficient of Thermal Expansion ConTRoL Coax Transfer Switch Collected Volatile Condensable Material Chemical Vapour Deposition Converter Module Continuous Wave Calibration Window Length Direct Access Digital to Analogue Converter Direct Access Customer Deployed Acquisition Mode Direct Access Partner Direct Access Station Direct Archive System Direct Access Service Providers Digital Audio Tape DLR/GSOC protocol layer Database decibel Database Management System Direct Current Data and Control Electronics Document Contents Guidelines Declared Components List Deployment Control Module Document Change Notice Deployed/Deployment Contact Point Document Change Request Deplyment Control Unit Design and Development Design, Development & Assembly, Integration and Verification Dependability Data File Design Definition File Design, Development and Verification Plan Distributing Entity Digital Equipment Corporation Deployment Mechanism EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 DEM DEP DES DES DESA DEU DF DFR DFU DHS DID DIL DIL DIMS DIP DJF DL DLC DLR DM DM DMA DML DMM DMP DMPL DMSS DMU DMZ DOF DPA DPL DRA DRB DRB DRD DRD DRDL DRL DS DSID DSL DSPG DT DTAR DTC DTED-1/2 DTM DTS DTS S1-LI-ASU-PL-0011 Issue 1 Page 11 of 76 Digital Elevation Model Spacecraft Deployment Mode Data Exchange Server Data Encryption Standard X-Band SAR Demonstrator Detection Electronic Units Dissemination Facility Detection Front-end Radiator Detection Front end Unit Data Handling System Design and Interface Document Deliverable Item List Dual In-Line Data and Information Management System DIPlexer Design Justification File Downlink Data Length Code Deutsches Zentrum für Luft- und Raumfahrt e.V. Development Model Differential Mode Defence Mapping Agency Declared Materials List Digital Multimeter Dump (attribute that identifies data originating from mass memory) Declared Mechanical Parts List Data Management Subsystem Digital Mock-Up De-militarised Zone (Network Security Term) Degree of Freedom Destructive Physical Analysis Declared Processes List Dual Receive Antenna Delivery Review Board Distribution and Regulation Board Detection Raw Data Document Requirements Definition Detection Raw data Link Document Requirements List Digital Serial acquisition Data Structure ID Document Status List Distributed Star-Point Grounding Data Take Distributed Target Ambiguity Ratio Direct TeleCommand Digital Terrain Elevation Data (in accuracy levels 1 and 2) Digital Terrain Model Data Transfer System (GSOC) Deployment Test System EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 DU DUT DUT DV DVB DVD-R DWP E E/V E2E EAC EAD EADS EAF EAP EBB EC EC-BAQ ECC ECC ECEF ECI ECL ECO ECP ECR ECSS ED EDAC EEC EEE EEE EEPROM EES EfM EFM EFN EGRP EGRS EGSE EHAR EHB EIA EICD EIDP EIRP EIRP EM EMC EMCS S1-LI-ASU-PL-0011 Issue 1 Page 12 of 76 Detection Units Design Under Test Device Under Test Delta Velocity Digital Video Broadcast Digital Video Disk - Recordable Data Window Position EnVironmental (Design and Test) End To End Estimate at Completion Electrostatic Arch Discharge European Aeronautic Defence and Space Company Event Detection and Action Execution Function Existing Acquisition Product Elegant Bread-Board External Calibration Entropy-Constrained Block Adaptive Quantisation Event Control Code Error Correction Code Earth Centred Earth Fixed Earth Centred Inertial Emitter Coupled Logic Engineering Change Order Engineering Change Proposal Engineering Change Request European Co-operation for Space Standardisation External Data Interface Error Detection and Correction Enhanced Ellipsoid Corrected Electrical and Electronics Engineering Electrical, Electronic and Electromechanical Electrically Erasable and Programmable Read Only Memory (E2PROM) End to End Simulator Electrical functional Model Encryptor Formatter Module Elevation Feed Network Electrical Ground Reference Plane Electrical Ground Reference Structure Electrical Ground Support Equipment Electrical Harness Error Handbook Electronics Industries Association Electrical Interface Control Document End Item Data Pack Earth Integrated Receive Power Effective Isotropic Radiated Power Engineering Model Electro-Magnetic Compatibility EGSE & Mission Control System EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 EMI EN ENL EO EOC EOL EOM EOS EOWEB EPP EPPL EPROM EPS EQM EQSOL ERS ERT ES ESA ESA MM ESA/ESRIN ESATAN ESD ESE ESOC ESP ESRIN ESTEC ETRS EU EUT EV EVT F FA FAAD FAR FAR FAR FCL FCP FCT FCT FCV FD FDIR FDL FDLL FDLU FDLY S1-LI-ASU-PL-0011 Issue 1 Page 13 of 76 Electro-Magnetic Interference System & Engineering Equivalent Number of Looks Earth Observation End of Charge End Of Life Electro-Optic Modulator Earth Observing System Earth Observation on the WEB (Web Gateway of ISIS and MUIS) Electrical Preparatory Programme European Preferred Parts List Electrically Programmable ROM Electrical Power System Engineering Qualification Model Equipment Switch Off Line European Remote Sensing Satellite Earth Received Time Electrical Systems European Space Agency ESA Multi-Mission European Space Agency in Italy ESA Thermal Analysis…. Electrostatic Discharge DLR/GSOC Enhanced System Environment European Space Operations Centre Electrical Support Programme European Space Research INstitute European Space Technology Centre European Terrestrial Reference System Electrical Units Equipment under Test EnVironmental (Design and Test) Environmental and Test Functional Analysis Flight Attitude Anomaly Detector Flight Acceptance Review Frame Acceptance and Reporting Frame Analysis Report Foldback Current Limiter Flight Control Procedure Flight Control Team Full Characterisation Test Flow Control Valve Flight Dynamics Failure Detection, Isolation and Recovery Flight Design Load Flight Design Limit Load Flight Design Load Ultimate Flight Design Load Yield EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 FDS FDV FDVV FE FEC FECW FEM FESS FET FFM FFT FFTECBAQ FGSE FHP FIFO FLE FLL FM FMECA FOF FOP FOS FOT FOV FPGA FPM FPO FPT FR FRD FRED FRO FRR FRU FS FSR FTA FTP FVV FW FWHM G GA Ga As Gbyte GCC GCN GCN-P GCOS S1-LI-ASU-PL-0011 Issue 1 Page 14 of 76 Flight Dynamics System Fill/Drain Valve Fill & Drain/Vent Valve Finite Element Forward Error Correction Frame Error Control Word Finite Element Model Front End Subsystem Field Effect Transistor Flip Flop Mechanism Fast Fourier Transform Fast Fourier Transform-Entropy Constrained Block Adaptive Quantisation Fuelling Ground Support Equipment First Header Pointer First In, First Out Fuel Loading Equipment Flight Limit Load Flight Model Failure Modes Effects and Criticality Analysis Flight Operations Facility Flight Operations Plan or Procedures Flight Operations Segment Flight Operations Team Field of View Field Programmable Gate Array Fine Pointing Mode Focal Plane Optics Full Functional and Performance Test Final Review Functional Requirements Document Framed Raw Expanded Data FRont Optics Flight Readiness Review Front end Repeater Unit Flight Spare Free Spectral Range Fault Tree Analysis File Transfer Protocol Fill and Vent Valve Firmware Full Width at Half Maximum General assembly Gallium Arsenide Gigabyte Ground Control Centre Ground Communications Network Ground Communication Network PGS Global Climate Observing System EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 GCS GDI GDIR GDP GDS GEC GFRP Ghe GHz GIP GLOBE GLONASS GMES GMFE GMM GMT GNC GND GNSS GOP GOS GPIO GPS GPWG GRACE GRC GRD GRP GS GS, G/S GSBD GSCDR GSE GSICD GSN GSOC GSOM GSOPR GSOV GSPDR GSRR GSRS GSS GSTL GSTS GSTS-M&C GSTS-ME GSTS-SSC GSTS-SSC GSTVVR S1-LI-ASU-PL-0011 Issue 1 Page 15 of 76 Ground Communications Subnet Grounding and Isolation General Design and Interface Requirement Global Data Pool DLR/GSOC Ground Data System Geocoded Ellipsoid Corrected Glass Fibre Reinforced Plastic Helium Gas Gigahertz Gateway Interoperable Protocol Global Land One-KM Base Elevation Data GLObal'naya Navigatsionnay Sputnikovaya Sistema (Russian GPS) Global Monitoring for Environment and Security Generic Modular Front End Geometric Mathematical Model Greenwich Mean Time Guidance, Navigation & Control Ground Global Navigation Satellite System Ground Operations Plan Global Observing System General Purpose Input Output Global Positioning System Grid Point Weight Generator Gravity Recovery and Climate Experiment Greenwich Rotating non-inertial co-ordinates (earth centred) Graphic Display (line plot) Glass Reinforced Plastic Ground Station Ground Segment Ground Segment Baseline Definition (Document) Ground Segment Critical Design Review Ground Support Equipment Ground to Spacecraft Interface Control Document Ground Station Network German Space Operations Centre Ground Segment and Operations Manager Ground System and Operation Principles and Requirements Ground Segment Operational Validation Ground Segment Preliminary Design Review Ground Segment Requirements Review Ground Segment Requirements Specification Ground Segment Supplier Ground System Test Leader Ground Station System Ground Station System - Monitoring and Control Ground Station System - Mission Exploitation Ground Station System - Space Segment Control Space Segment Control Station Ground Segment Technical Verification and Validation Review EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 GSTVVRR GT GT GTC GTP GUI Ground Segment Technical Verification and Validation Readiness Review Green Tag Ground Target Geocoded Terrain Corrected Generic TM processor Graphical User Interface H H H/K or HK H/W or HW HA HAR HCI HDBK HDDT HDF HFA HH HiSEEN HK HKOBS HKTM HLOS HMI HP HPC HPC HPR HPT HR HR HRDS HRM HRX HS HSIA HTTP HV HW or H/W Hz Horizontal Polarisation Housekeeping Data Hardware Hazard Analysis Harness Human-Computer Interaction Hand Book High Density Data Tape Hierarchical Data Format History File Archive Linear Polarisation, horizontal at transmit, horizontal at receive High Speed ESA EO Network Housekeeping Housekeeping and observation HouseKeeping TeleMetry Horizontal Line of Sight Human-Machine Interface Heat Pipe High Priority Command High Power Command Hardware Problem Report High Power Transistor Harness Institut für Hochfrequenztechnik und Radarsysteme High Rate Data Stream Hold-down and Release Mechanism High Rate Data Extracted Parameters Heat Sink Hardware/Software Interaction Analysis Hyper Text Transfer Protocol Linear Polarisation, horizontal at transmit, vertical at receive Hardware Hertz I I I I/F I/O IABG IAM IBR IC IC/ICAL In-phase Input InterFace Input/Output Industrieanlagen Betriebs-Gesellschaft Initial Acquisition Mode Instrument Baseline Review Instrument Core Internal Calibration S1-LI-ASU-PL-0011 Issue 1 Page 16 of 76 EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 ICB ICD ICDR ICE ICF ICF ICG ICH ICM ICM ICM ICS ICS ICU ICV ID IDD IDE IDRB IEB IEC IEEE I/F IF IFE IFESS IFM IFOV IFU IGP IGRF IGS ILZPF IM IMD IMF IMO IMR IMRC IMU INS InSAR INT Int IO or I/O IOCS IOD IOF IOGT IOOR S1-LI-ASU-PL-0011 Issue 1 Page 17 of 76 Internal Control Bus Interface Control Document/Drawing Instrument Critical Design Review Integrated Central Electronics Instrument Calibration Facility InterChangeable Format Instrument Command Generator Instrument Command History Instrument Control Module Instrument Command and Monitoring bus Instrument Control and Monitoring Instrument Calibration Segment Instrument Operations and Calibration Segment Instrument Control Unit Inter Centre Vector Identification, Identity Integration, Design and Development Identifier Extension Instrument Delivery Review Board Instrument External Baffle International Electrotechnical Commission Institute of Electrical and Electronics Engineers Interface Intermediate Frequency Intermediate Frequency Equipment Integrated Front End Subsystem Interferometer Instantaneous Field-Of-View Interface-to-Units Module ICS (2) Guide Protocol International Geomagnetic Reference Frame International GPS Service Ingestion and Level 0 Processing Facility Isostatic Mount Isostatic Mounting Device Remote Sensing Technology Institute Inverted Mode Operation Instrument Master Reference Instrument Master Reference Cube Inertia Measurement Unit (Gyro) Institute of Navigation, University Stuttgart Interferometric Synthetic Aperture Radar Interrupt Internal Input/Output Interoperable Catalogue System In-orbit Delivery Instrument Operations Facility I/O for General functions Sentinel-1 In-Orbit Operations Review EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 IOPS/IOS IOPT IOST IOT IP IP IPDU IPFD IPSU IPU IR IRD IRD IRF IRQ ISA ISDN ISLR ISO ISP IST ISV ISVF ISVV ITRF ITT ITU IU IUT IVR IVV/IV&V Instrument Operations Segment I/O for Propulsion chain Sentinel-1 I/O for Servicing equipment Sentinel-1 In Orbit Testing Intellectual Property Internet Protocol Instrument Power Distribution Unit Input Flux Density Instrument Power Supply Unit Instrument Processing Unit Infra-Red Informative Reference Document Interface Requirement Document Impulse Response Function Interrupt Request Industry Standard Architecture Integrated Services Digital Network Integrated Sidelobe Ratio International Organisation for Standardisation Instrument Source Packet Integrated System Test Independent Software Validation Instrument Software Validation Facility Independent Software Verification and Validation International Terrestrial Reference Frame Invitation To Tender International Telecommunications Union Integer Unit Item Under Test Instrument Verification Integration, Verification and Validation J JEDEC JTAG Joint Electron Device Engineering Council Joint Test Action Group K k K K1 kbps kHz KIP KIP KMF KO 1024 multiplier prefix Kelvin Control Room 1 Kilo bit per second Kilo Hertz Key Inspection Point Key Inspection Point Key Management Facility Kick-Off L L0 L1b LA LAF LAN Processing Level 0 according to CEOS definition Processing Level 1b according to CEOS definition Launcher Long Term Archiving Facility Local Area Network S1-LI-ASU-PL-0011 Issue 1 Page 18 of 76 EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 LAR LAT LAU LB LCC LCDA LCE LCL LCLK LDO LDTS LED LEO LEOP LET LHCP LIDAR LISN LLI LMCF LN2 LNA LO LOS LOS LOV LRR L-SAR LSB LT LTAN LTDB LTP LTSM LV LV LVA LVAU LVDS LVLH LVS Launch Acceptance Review Lot Acceptance Testing Spacecraft Launch Mode Local Bus Library Configuration Control Launcher Coupled Dynamic Analysis Leak Check Equipment Latching Current Limiter Low (rate) CLocK Low DropOut Large Data Transfer Service Light Emitting Diode Low Earth Orbit Launch and Early Operations/ Launch and Early Orbit Phase Linear Energy Transfer Left Hand Circular Polarisation Light Detection And Ranging Line Impedance Simulation Network Long Lead Items Local Monitoring and Control Facility Liquid Nitrogen Low Noise Amplifier Local Oscillator Line Of Sight Loss Of Signal Local Orbit Vector Launch Readiness Review L-band Synthetic Aperture Radar Least Significant Bit Long Term (Requirement) Local Time Ascending Node Long-term Database Long-term Planning = Strategic Planning Long-term System Monitoring Latch Valve Launch Vehicle Launch Vehicle Adapter Launch Vehicle Authority Low Voltage Differential Signalling Local Vertical Local Horizontal Launch Vehicle System M M M&C MAG MAIT MAP Mbps MByte MC Mega 1024k multiplier prefix Monitoring and Control Magnetometer Manufacturing, Assembly, Integration and Test Multiplexed Access Point Mega bit per second MegaByte Marginally Compliant S1-LI-ASU-PL-0011 Issue 1 Page 19 of 76 EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 MCM MCMD MCPC Mcps MCS MD MDFE MDVE MEC MEIP MEOP MES MF MGD MGSE MGT MHz MIB MIB MICD MIMO MIN MIP ML ML MLC MLI MM MM MM&C MMA MMC MMFU MMI MMIC MMU MOC MOCD MOD MODIS MoI MOIS MoS MOS MOSFET MOT MOTL MOU MPCB MPF S1-LI-ASU-PL-0011 Issue 1 Page 20 of 76 Multi Chip Module Macrocommand Master Channel Frame Count Mega Complex Samples Per Second Mission Control System Mass Dummy Mission Dependant Filter Equipment Model Development and Verification Environment Mission Exploitation Centre Maximum Expected Inlet Pressure Maximum Expected Operating Pressure Mission Exploitation System Maintenance File Multi Look Ground Range Detected Mechanical Ground Support Equipment Management File Megahertz Minimum Impulse Bit Mission Information Base (TM/TC display database) Mechanical Interface Control Document Multivariate Input Multivariate Output Minimum Mandatory Inspection Point Master Library Memory Load Memory Load Command Multi-Layer Insulation Mass Memory module Mass Memory board Mission Management and Control Memory Metal Alloy Mission Master Catalogue Memory & Formatting Unit Man-Machine Interface Monolithic Microwave Integrated Circuit Mass Memory Unit Mission Operations Centre Mission Operations Concept Document Mission Operations Director Moderate Resolution Imaging Spectroradiometer Moment of Inertia Mission Operations Information System Margin of Safety Mission Operations Segment Metal Oxide Silicon Field Effect Transistor Mission Operations Team Mission Operations Team Lead Memorandum of Understanding Materials & Processes Control Board Mission Planning Facility EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 MPS MPS MRB MRR MRT MS MS MS MS MSC MSAR MSB MST MSU MT MTF MTL MTM MTP MTQ MTR MTTR MUIS Mission Planning System Mission Planning and Scheduling System Material Review Board Manufacturing Readiness Review Mission Readiness Test Main Structure Material Specification Mechanical Systems Microsoft Message Sequence Chart Multi-frequency SAR Most Significant Bit Mission Simulation Test Main Supply Unit Mid/Medium Term (Requirement) Modulation Transfer Function Mission Timeline Magnetometer Main Test Processor MagneTorQuer Mid-term Review Mean Time to Repair Multi-Mission User Information Services N N&R N/A NAP NAPEOS NASA NB nBAQ NC NC NCH NCI NCR NCTRS NDA NDIU NEs0/NEσ0 NESZ NIR NM NOCC NOP NRB NRD NRE NRT NRZ Nominal and Redundant Not Applicable New Acquisition Product Navigation Package for Earth Observation Satellites National Aeronautics and Space Administration Narrow Band Number of BAQ bits Not Compliant / Non Conformance Not Connected Noise Characterisation Non Critical Items Non-Conformance Report Network Controller Transport and Routing System Non-Disclosure Agreement Network Data Interface Unit Noise Equivalent Sigma Nought Noise Equivalent Sigma Zero Near Infra-Red Normal Mode Network Operations Control Centre Non-Operating Non-Conformance Review Board Normative Reference Document Non-Recurring Expenditure Near-Real Time Non Return to Zero S1-LI-ASU-PL-0011 Issue 1 Page 21 of 76 EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 NRZ-L NRZ-L NSG NSM NTC NVRAM NWP Non Return to Zero Level Non-Return to Zero Logic Neustreliz Ground Station Non-Structural Mass Negative temperature coefficient Non-volatile Random Access Memory Numerical Weather Prediction O OAP OBC OBCP Off Axis Parabola On-Board Computer On-Board Control Procedures OBCP OBDH OBMF OBRT OBS OBSM OBSP OBSW OBT OBTM OC OCC OCD OCI OCM OCS OCS ODB ODL OE OFFRED OHS OIRD OL OLTF OLVLH OM OOL OP OP OPA OPD OPG OPS ORB ORR OS OSE OSF Original Baseline Cost Plan On Board Data Handling (On board computer) On Board Monitoring Function On Board Reference Time Observation On Board Software Maintenance Observation period Onboard Software On-Board Time On Board Telemetry Ordering Control Operational Control Centre Output Command Driver OCS Catalogue Interface Orbit Control Mode Open GIS Catalogue System Operation Control System Operational Data Base Operator Directive Language Output Enable Offline Reduced Parameter Processing Order Handling System Operations Interface Requirements Document Off-Line Open Loop Transfer Function Offset Local Vertical Local Horizontal ESA Order Model Out of Limit Ouptput Operating Procedure Long-term Operational Products Archive Optical Path Difference Online/Offline Product Generation Operations Orbit Operational Readiness Review Operating System Off-line Simulation Environment On-Board Statistics Function S1-LI-ASU-PL-0011 Issue 1 Page 22 of 76 EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 OT OVP OVR OVRR Operating Tool Operational Validation Plan Operational Validation Review Operational Validation Readiness Review P PA PAC PAD PADF PAP PAP PAS PBL PBS PC PC PC PCB PCB PCC PCDU PCI PCM PCOT PCR PCS PDE PDE PDF PDF PDKP PDL PDL PDM PDR PDS PDT PDU PE PEAS PF PFCI PFD PFM PFR PG PGS PHA PID PIF Product Assurance Processing and Archiving Centre Part Approval Document Processing Archiving and Distribution Facility Planned Acquisition Product Product Assurance Plan Performance Analysis System Planetary Boundary Layer Polarizing Beam Splitter Partially Compliant Personal Computer Production Control Parts Co-ordination Board Printed Circuit Board Pulse Coded Calibration ( = PN Gating) Power Conditioning and Distribution Unit Peripheral Component Interconnect Pulse Code Modulation Power Converter for Sentinel-1 Propagation Correction Requirements Payload Control System Pointing Drift Error Pressurisation/Depressurisation Equipment Portable Document Format (Adobe) Probability Density Function Preliminary Design Key Point Proof Design Load Packet Data Length Pre-Development Model Preliminary Design Review Processing and Dissemination System Payload Data Transmission Power Distribution Unit Protective Earth Performance Evaluation and Analysis Software Platform Potential Fracture Critical Items Power Flux Density Proto-flight Model Problem/Failure Reporting Pressure Gauge Payload Ground Segment Passive Hinge Assembly Processor Identifier Proton Irradiation Facility S1-LI-ASU-PL-0011 Issue 1 Page 23 of 76 EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 PIND PL PL PLE PLGSE PLL PM PM PM PM PM PMAC PMD PMF PMP PMP PN POBS POD PoD PODF Pol POV p-p PPB PPDU PPF PPL PPLE PPS PR PRC PRF PRI PROM PSA PSD PSK PSLR PSM PSM PSS PSS PSTRU PSU PSVF PT PT PTAR PTC S1-LI-ASU-PL-0011 Issue 1 Page 24 of 76 Particle Impact Noise Detection Payload Product Library Propellant Loading Equipment Payload GSE Phase Locked Loop Phase Modulation Processor Module Progress Meeting Project Management Propulsion Module Payment Milestone Achievement Certificate Propellant Management Device Processing Management Facility (Mechanical) Parts, Material, and Processing Project Management Plan Pseudo Noise Project Organisation Breakdown Structure Precise Orbit Determination Push-off Device(s) Precise Orbit Determination Facility Polarisation Precise Orbit Vector peak-to-peak Primary Power Bus Platform Power Distribution Unit Pre-Processing Facility Preferred Parts List Pressurant & Propellant Loading Equipment Pulse Per Second Progress Report Propagation Correction Pulse Repetition Frequency Pulse Repetition Interval Programmable Read Only Memory Part Stress Analysis Power Spectral Density Phase Shift Keying (modulation method) Peak Sidelobe Ratio Power Switching Module Processing System Management Portable Satellite Simulator Power Sub System Primary Structure Power Supply Unit Platform Software Validation Facility Performance Test Pressure Transducer Point Target Ambiguity Ratio Positive temperature coefficient EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 PTR PTV PTX PUP PUS PVR PVT PW PWK PWM PWR Q Q Q/L QA QC QCW QE QL QM QML QOS QPL QPSK QR QRB QRR QSL QSL QT R R/T RAD RAM RAMS RB RBE RCM RCS RCS RCS RCT RD RDA RDM RE REC REF Rep RF S1-LI-ASU-PL-0011 Issue 1 Page 25 of 76 Post Test Review Position Time & Velocity Pressure Transducer Parameter Update Process Packet Utilisation Standard Product Verification Position, Velocity, Time Packet Wire Pipework & Fasteners Pulse Width Modulator Power Quadrature phase Quick-Look Quality Assurance Quality Control Quasi-Continuous Wave Quantum Efficiency Qualification Load Qualification Model Qualified Materials List Quality of Service Qualified Parts List Quadrature Phase Shift Keying Qualification Review Qualification Review Board Qualification Readiness Review Qualification Status List Quasi-static Load Qualification Level Test Real-time (data) Rate Anomaly Detector Random Access Memory Reliability Availability Maintainability Safety Requirements Baseline Rigid Body Element Radiometric Correction Module Radar Cross Section Reaction Control System Reference Coordinate System Reaction Control Thruster Reference Document Long-term Raw Data Archive Radiation Design Margin Radiated Emissions Receive Error Count Reference Repetition(s) Radio Frequency EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 RFA RFC RFCS RFCT RFD RFDU RFE RFEA RFG RFHS RFI RFP RFP RFQ RFW RH RH RHCP RIBV RID RIMR RK RM RMA RMS RMU ROD ROI ROM ROM RP RPE RPG RPT RRA RRA RRE RS RS RS R-S RSA RSD RSS RT RT RT RTL RTN RTR S1-LI-ASU-PL-0011 Issue 1 Page 26 of 76 Request for Approval Radiofrequency Compatibility RF Cable Set RF Compatibility Tester Request for Deviation Radio Frequency Distribution Unit Radio Frequency Electronics Radio Frequency Equipment Assembly Routing Flow Guide RF Hybrid Splitter Request For Information Reduced Functional and Performance Test Request For Proposal Request For Quotation Request for Waiver Relative Humidity Right Hand Right Hand Circular Polarisation Random Impulse Bit Variation Review Item Discrepancy Reference Instrument Master Reference Replay Key Reconfiguration Module Rate Monotonic Analysis Root Mean Square Rate Measurement Unit Review of Design Region of Interest Read-Only Memory Rough Order of Magnitude Retarder Plate Relative Pointing Error Radar Parameter Generator Reduced Functional and Performance Test Required Reference Architecture Risk Reduction Actions Residual Rate Error Radiated Susceptibilities Receiving Station Requirement Specification Reed Solomon Relay Status Acquisition Requirements Specification Document Root Sum Squared Red Tag Room Temperature Remote Terminal Register Transfer Level Return Remote Transmission Request EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 RTS RU RVT RW RW RWA RWU Rx RXD Rx-H RX-SR Rx-V S S/C or SC S/W or SW SA SA SAAD SAD SADM SAF SAM SAR SARCON SARM SARP SARS SAS SAT SATL SATP SATR SBDL SBRT SBY ScanSAR SCAR SCC SCD SCDB SCET SCI SCIDL SCL SCMP SCOE SCOE SCOE SCOS SCOS S1-LI-ASU-PL-0011 Issue 1 Page 27 of 76 Request to Send Reconfiguration Unit Radiation Verification Test Reaction Wheel Read and Write Reaction Wheel Assembly Reaction Wheel Unit Receive® Receive Data Receive mode for horizontal polarisation Receiver Selection Review Receive mode for vertical polarisation Spacecraft Software Solar Array Structured Analysis Sun Attitude Anomaly Detector Solar Array Deployment Mechanism Solar Array Drive Mechanism Spacecraft Safe Mode Stowed Acquisition Mode Synthetic Aperture Radar SAR Product Control Software Solar Array Rotation Mechanism SAR Processor Solar Array Release Subsystem SAR Antenna Subsystem Satellite Team Satellite Team Lead Software Acceptance Test Plan Software Acceptance Test Reports Standard Balanced Digital Link Start of Burst Reference Time Spacecraft Standby Mode Synthetic Aperture Radar in Wide Swath Mode Software Criticality Analysis Report Space Components Coordination. Scrolling Display Spacecraft Database Spacecraft Event Time Science (Payload) Software Configured Item Data List Subcarrier Lock Software Configuration Management Plan Satellite Check-Out Equipment Spacecraft On-Board Electronics System or Special Check-Out Equipment Software Coding Standard Spacecraft Operations System EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 SCOT SD SD SDD SDE SDE SDES SDID SDL SDLC SDP SDS SDVE SE SEB SEE SEGR SEL SEP SES SET SEU SFTP SGM SI SiC SID SIK SIM SiO2 SIS SISO SITP SITR SK SK SLC SLE SLK SM SM SMA SMD SMD SMDT SME SMF SMF SMK SMP S1-LI-ASU-PL-0011 Issue 1 Page 28 of 76 Special Terms of Tender Serial Data Structured Design Software Design Document Science Data Electronics Software Development Environment Software Design Standard System Design and Interface Document Specification and Description Language Serial Data Link Communication Software Development Plan Satellite Design Specification Software Development and Validation Environment System Engineering Single Event Burn-Out Single Event Effect Single-Event Gate Rupture Single Event Latch-Up Single Event Phenomena Sensor Electronics Subsystem Single Event Transient (Analogue) Single Event Upset Secure File Transfer Protocol Safe Guard Memory Système International Silicon Carbide Structure ID Structure Integration Kit Satellite Interface Mounts Silicon Oxide (Silica) Satellite Interface Structure Scalar Input Scalar Output Software Integration Test Plan Software Integration Test Reports Spare Kit Session Key Single Look Complex Space Link Extension Structure Lifting Kit Safe Mode Structure Model Sub-Miniature Assembly Standard Microcircuit Drawing Surface Mounted Device Space Mission Design Tool Small or Medium sized Enterprise Software Maintenance Facility System Management Facility Structure Mating Kit SW Management Plan EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 SNR SODAP SOE SOL SOM SoW SP SPA SPAP SPARD SPF SPR SQA SRAM SRD SRD SRDB SRF SRKP SRM SRP SRR SRS SRUD SS SS(n) SSB SSC SSC SSC SSF SSG S-SiC SSLR SSM SSMM SSO SSPA SSTRU ST ST-1 or S-1 STD STE STF STM StM STP STRU STS SUM S1-LI-ASU-PL-0011 Issue 1 Page 29 of 76 Signal to Noise Ratio Switch-on and Data Acquisition Phase Sequence Of Events Switch Off Line Spacecraft Operations Manager Statement of Work Source Packet Software Product Assurance Software Product Assurance Plan Software Product Assurance Requirements for Subcontractors Single Point Failure Software Problem Report Software Quality Assurance Static Random Access Memory Software Requirements Document System Requirements Document Spacecraft Reference Database Spectral Response Frequency System Requirements Key Point Spacecraft Normal Mode Solar Radiation Pressure System Requirements Review Spacecraft Requirement Specification Software Reuse Document Secondary structure Sub-Swath number n Setting Selector Bus Single Look Slant Range Complex Source Sequence Count Space System Customer Steady State Firing Synchro Signal Generator Sintered Silicon Carbide Spurious Side Lbe Ratio Second Surface Mirror Solid State Mass Memory Sun-synchronous orbit Solid State Power Amplifier Secondary Structure Short Term (Requirement) Sentinel-1 Standard Software Test Environment Spectral Transfer Model Structure and thermal model Structure Model Short Term Planning Structure Star Tracker Support Software User Manual EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 SUTP SUTR SVC SVF SVF SVT SVVP SW or S/W SWL SWST Sync T T T/R TAP TAP TAR TAT TB TB/TV TBA TBC TBD TBI TBS TByte TC TC TC/TF TCA TCA TCC TCM TCP TCS TCS TCSEH TCU TDM TDS TE TEC TEC TEC TEL Temp Comp TF TFD TFG S1-LI-ASU-PL-0011 Issue 1 Page 30 of 76 Software Unit Test Plan Software Unit Test Reports Service Call SAR Verification Facility Software Verification Facility System Validation Test Software Verification and Validation Plan Software Sampling Window Length Sampling Window Start Time Synchronisation Test Transmit/Receive Telemetry Acquisition Processor Test Access Port Tape Archiver – Unix file format Trans Atlantic Terrestrial Cable Thermal Balance Thermal Balance/Thermal Vacuum To Be Agreed To Be Confirmed To Be Defined To Be Issued or To Be Included To Be Specified Terabyte Telecommand Terminal Count Telecommand Transfer Frame Test Connector Active Thrust Chamber Assembly Telecommand Clock Timing Control Module Transfer Control Protocol Telecommand Stream Thermal Control Subsystem Thermal Electrical Hardware Set Tile Control Unit Time Division Multiplexed Telemetry Data Stream Test Equipment Thermo-Electrical Cooler (Peltier cooler) Total Electron Count Transmit Error Count TELescope Temperature Compensation Transfer Frame according to CCSDS Total Fixed Delay Transfer Frame Generator EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 TFOV TFT TG TGU TH TICD TID TIF TLE TLM TM TMC TMDD TMFE TML TMM TMTC TMTF TN TOPAS TOPS TPL TQD TR TRB TREF TRF TRK TRM TRP TRP TRR TS TSP TSR TSX TT&C TTAG TTL TTR TV TVD TWTA Tx TxA TXD Tx-H TxM Tx-V U S1-LI-ASU-PL-0011 Issue 1 Page 31 of 76 Total Field-Of-View Thin Film Transistor Trajectory Generator Transmit Gain Unit THermistor Thermal Interface Control Document Total Ionising Dose Transponder Interface Two Line Elements Telemetry Telemetry Period of Master Clock Telemetry Deformatter and Decryptor Telemetry Formatter and Encryptor Total Mass Loss Thermal Mathematical Model Telemetry-TeleCommand Telemetry Transfer Frame Technical Note Technology Development for On-Board SAR-Processor and Storage Demonstrator Terrain Observation Progressive Scanning Transmit Pulse Length Telemetry Query Display Transmit/Receive Test Review Board Reference Temperature Spacecraft Transfer Mode Tracking Transmit-Receive Module Temperature Reference Point Temperature Reference Point Test Readiness Review Technical Specification Twisted Shielded Pair TerraSAR TerraSAR-X Telemetry, Tracking & Control (/Command) Time Tag (command) Transistor Transistor Logic Telemetry Telecommand and Reconfiguration Thermal Vacuum Total Variable Delay Travelling Wave Tube Amplifier Transmit(ter) Transmitter Assembly Transmit Data Transmit mode for horizontal polarisation Transmit module Transmit mode for vertical polarisation EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 UART UFP UI UK UPS URD USB USF USR UTC UTDF UTM UUT UV V V V&V Val VC VCA VCD VCDU VCFC VCID VCM VCS, VC7 VDA VDS VH VHDL VHSIC VIP VIS VME VPL VPN VSAR VSWR VV W WAN WARC WBS WCA WCRP WD WDE WFE WGS WMO S1-LI-ASU-PL-0011 Issue 1 Page 32 of 76 Universal Asynchronous Receiver and Transmitter Uncertainty for Flight Prediction User Interface United Kingdom Universal Polar Stereographic User Requirements Document Universal Serial Bus User Service Facility Useful Spectral Range Universal Time Code Universal Tracking Data Format Universal Tranverse Mercator Unit Under Test Ultra-violet Vertical Polarization Verification and Validation Validation Virtual Channel Virtual Channel Assembler Verification Control Document Virtual Channel Data Unit Virtual Channel Frame Count Virtual Channel Identifier Virtual Channel Multiplexer Virtual Channel (CCSDS standard) Vacuum Deposited Aluminium Drain-Source voltage Linear Polarisation, vertical at transmit, horizontal at receive Very high speed integrated circuit Hardware Description Language Very High Speed Integrated Circuit Verification Input Parameters Voice Intercom System Velocity Measurement Error Visible Panty Line Virtual Private Network Versatile SAR Voltage Standing Wave Ratio Linear Polarisation, vertical at transmit, vertical at receive Wide Area Network World Administrative Radio Conference Work Breakdown Structure Worse Case Analysis World Climate Research Programme Watch Dog Wheel Drive Electronics Wave Front Error World Geodetic System World Meteorological Organisation EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 WP WPD WRS WS WWW X XCAL XDA XFE XML XO Y YPM S1-LI-ASU-PL-0011 Issue 1 Page 33 of 76 Work Package Work Package Description World Reference System Workstation Word Wide Web External Calibration X-Band Downlink Assembly X-Band Front End eXtensible Markup Language Crystal Oscillator Yaw Pointing Mode EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 34 of 76 4. DEFINITIONS 4.1 System Constants and Units Measurement units are defined in the SI system. Sentinel-1 System The end-to-end space and ground segment infrastructure that acquires, generates and delivers both single (C-band) space-borne SAR basic products (Level 1B). Sentinel-1 Spacecraft The C-band spacecraft component of the Sentinel-1 System, comprising the Sentinel-1 Payload supported by the Sentinel-1 Platform, together with the spacecraft-level functions structure, thermal, propulsion, and spacecraft mechanisms. Sentinel-1 Platform The platform component of the Spacecraft, providing the typical electrical platform functions only, i.e. attitude determination and control, navigation (GNSS), power generation distribution and storage, spacecraft-level FDIR and software, telemetry tracking & control (TT&C) and measurement data link functions provided by the bus. Sentinel-1 Payload The payload component of the Spacecraft, providing the C-band SAR instrument. Sentinel-1 Launcher The launch vehicle required for delivery of the Sentinel-1 Spacecraft to its nominal orbit. Sentinel-1 Ground Segment The ground segment infrastructure component of the Sentinel-1 System, comprising control, reception and processing facilities capable of generating basic products (Level 1B). Order to Acquisition Time Time, from placing an order, to create a data product centred at an arbitrary location to the next possible acquisition of the raw radar signal data by the satellite. As an order can be placed at any time in the orbit cycle the appropriate values for 5% probability of compliance and for 95% probability of compliance are specified when the product location is arbitrarily selected within the requested access area. In all cases where two access or processing times are identified, the less demanding one is associated with 95% of required data-sets and the more demanding one with 5%. Revisit Time The Revisit Time is the time between two consecutive possible observations of the same target in the full performance incidence angle range at a particular latitude. 95% revisit time is the 95 percentile of the revisit time of all points at the specified latitude (or at equator if not explicitly specified). EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 35 of 76 Quality of Service A mechanism to provide to the user a statement of the expected performance of the system in terms of accuracy, timeliness and completeness. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 36 of 76 4.2 C-SAR Instrument This section lists instrument definitions and SAR terms, many of which are taken from IRD01 - System Requirements Document. Across track direction The across track direction is defined as normal to the along track direction in the tangent plane at the geodetic sub-satellite position. Along track direction The along track direction is parallel to the projection of the Spacecraft velocity on the tangent plane to the Earth at the geodetic sub-satellite position. Ambiguity Ratio The unambiguous zone is defined in the across-track direction by the nominal swath width and in the alongtrack direction by the total processed Doppler bandwidth. The ambiguous zone is outside this area. Calibration Calibration is the procedure for converting the instrument measurement output data into the required physical units. After calibration, the output data must be within a known tolerance, consistent with all performance requirements, everywhere across the swath, around the orbit, over the dynamic range and over the lifetime of the instrument. Calibration is based on characterisation measurements performed onground before launch and in-flight. Characterisation Characterisation is the direct measurement, or analytical derivation from measurement, of a set of technical and functional parameters, over a range of conditions (e.g. temperature) to provide data necessary for calibration, ground processor initialisation and verification. Characterisation can be performed either before launch on-ground or in-flight. In-flight, at least all those parameters have to be determined that may have varied since on-ground characterisation or which have not been measurable on-ground. In-flight characterisation may be based either on data derived from facilities built into the instrument (internal calibration) and/or on external sources (external calibration). Chirp Slope This defines the Chirp frequency versus time response which must be achieved over the Resolution Bandwidth (see later entry). Cross-polar Isolation • Vertical polarisation is defined as that electric field having the peak component Ev of the electric field vector in a plane containing the satellite local vertical and the direction of propagation. • Horizontal polarisation is defined as that electric field having the peak component Eh of the electric field vector in a plane orthogonal to this one and also containing the direction of propagation If the system operates in vertical polarisation and assuming no polarisation rotation due to atmospheric or scattering effects, the cross polar isolation in transmission is defined as ⎛ EvTx ⎞ X = 20 log10 ⎜⎜ Tx ⎟⎟ ⎝ Eh ⎠ EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE S1-LI-ASU-PL-0011 Issue 1 Page 37 of 76 Sentinel-1 where: EvTx is the vertical peak component of the electric field vector at transmit and E hTx is the corresponding horizontal peak component of the electric field vector Similarly the power ratio of vertical to horizontal channel which results from receiving an ideal plane wave polarised in horizontal direction (in target coordinate system) is denoted cross polar isolation in receive. When only a single value is specified it shall apply to receive and to transmit separately. C-SAR Electronics Subsystem (SES) The back end electronics component of the C-SAR Instrument, providing the radar control, IF/RF signal generation and receive data handling functions. C-SAR Data Link The on-board data handling and down-linking component of the Platform, providing measurement data C-SAR Antenna Subsystem (SAS) The active and passive antenna components of the C-SAR Instrument, providing the high power generation, signal detection, and beam-forming, radiating and calibration functions. C-SAR Instrument The C-band SAR Instrument component of the Sentinel-1 Payload, providing the SES and SAS radar front end and control electronics functions, and interface to mass storage and X-band down-linking functions. C-SAR Tile The repeatable, modular assemblies of the SAS that together constitute the active antenna components of the SAS. The C-SAR Tiles also provide partial structural support to the antenna (the rest being provided by the Payload Panel, the other structural component of the C-SAR Front End). Data Collection Angle Range Range of incidence angles for which basic products may be acquired albeit with relaxed performance. Distributed Target Ambiguity Ratio (DTAR) The distributed target ambiguity ratio is the ratio of energy contribution from a distributed target in the ambiguous zones to the energy contribution from a distributed target located in the unambiguous zone. The ratio is to be calculated using the Distributed Target Radar Cross Section Reference Model and it is specified as the ratio P’T/ΣPA, where: • P’T is the intensity of the radar response to a distributed target located within the unambiguous zone • ΣPA is the summed intensity of the radar responses to the respective distributed targets within the various ambiguous zones Distributed Target Radar Cross-section Reference Model The value represents a mean level, and allows clear separation of dynamic range and the contributions of point-target ambiguities in subsequent interpretation. The best-estimate radar cross-section model shall be agreed and then become part of this document. Dynamic Range Distributed Target The dynamic range for distributed targets is defined as the range of σ 0,max ) σ 0 values (extending from σ 0,min to of a uniform distributed target within each full performance swath over which the performance requirements are met. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 38 of 76 Dynamic Range Point Targets The dynamic range of a for point target is defined as the dB ratio between the greatest power to be recorded in a basic image product and the lowest local mean noise power in that image (noise levels may be variable and hence the lowest is identified). Equivalent Number of Looks (ENL) The equivalent number of looks over a uniform region of imagery is calculated as: ENL = µ2 σ2 = 1 qr2 Full Performance Angle Range Range of incidence angles over which basic products are required to meet all data quality parameters. Impulse Response Function (IRF) The impulse response function (IRF) is defined as the two dimensional response in the detected image to a point target located in the product coverage area, neglecting effects of background clutter and thermal noise. Integrated Side-lobe Ratio (ISLR) The ratio of energy within the main lobe of the IRF (defined as lying within a rectangle of size 2x and 2y centred on the peak, where x and y are the 3dB widths in range and azimuth) and the energy outside of this area integrated over a region bounded by sides 10 times longer. Inter-channel Phase Accuracy Inter-channel phase accuracy is defined as the 3σ phase error between any pair of elements of the Scattering matrix of a polarimetric product. Inter-channel Radiometric Accuracy Inter-channel radiometric accuracy is defined as the maximum rms error of the power of any element of the Scattering matrix of a polarimetric product normalised to the mean power of the largest element in the Scattering matrix. Looks (Range, Azimuth) Number of statistically independent looks accumulated in the respective direction during product generation. Minimum Swath Overlap For strip map products the image area is selectable from pre-defined swathes. Swath flexibility defines the overlap of adjacent selectable swathes in terms of percentage of swath width. The swath width is at least as large as the product coverage in across track direction. Natural Azimuth Looks In ScanSAR operation the azimuth integration time is split and the different beams are scanned in a pre-defined cycle. The number of natural looks corresponds to the number of scan cycles within a complete synthetic aperture. With increasing number of natural looks the burst duration and bandwidth decreases. Noise Equivalent Sigma Nought (NESZ) The NESZ is defined as the back-scatter coefficient σ0 (back-scattering cross section of a distributed target per unit area) of a distributed target within the product coverage for which the signal power level in the final image is equal to the noise power level (thermal noise plus quantisation noise), i.e., an image SNR of 0 dB. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 39 of 76 Peak Side-Lobe Ratio (PSLR) The peak side-lobe ratio is defined as the ratio of the peak intensity of the main lobe of the impulse response function (IRF) to the peak intensity of the most intense side-lobe inside a rectangular image area of 10x in the along-track and 10y in the across-track direction. x and y are the along-track and across-track resolutions in meters, respectively. In the event that the first side-lobe of the error free response is masked by the main lobe of the error included response (i.e. there is no minimum between the peak of the IRF and the first side-lobe position), then the intensity at the position corresponding to the first side-lobe in the error free case shall be used for peak side-lobe ratio determination. Pixel Localisation Accuracy The pixel localisation accuracy is specified as the standard deviation in the estimate of the position of a point target of sufficiently large cross-section, the estimate being the point equidistant between the –3 dB points of its detected impulse response measured in along-track and across-track directions. If the localisation error depends on location within the image (product coverage), the worst-case location is applicable. The pixel localisation accuracy refers to the system dependent accuracy therefore perfect knowledge and arbitrary dense sampling of target altitude and perfect knowledge of needed tie points need to be assumed. Point Target Ambiguity Ratio (PTAR) The point target ambiguity ratio is specified as the ratio PT/PA, where: • PT is the peak intensity of the radar response to a point target located within the unambiguous zone • PA is the peak intensity of the radar response to a point target of the same radar cross section as defined for PT but located within the worst ambiguous zone Polarisation Modes • • • Quad-pol: Quad-polarisation mode, operated with fully-interleaved pulse transmission and dual-channel reception (HH+HV+VH+VV) Dual-pol: Dual-polarisation mode, operated with selectable single-pol transmission and dual-channel reception (i.e. generating HH+HV or VV+VH) Single Polarisation: Transmission and reception in a) a single linear polarisation (HH or VV) or b) cross-polar polarisation (HV or VH) Product coverage Size of a Basic Product in terms of along-track * across-track extension. Swath width is the across track ground range which is imaged and over which the performance requirements have to be predicted and verified. Swath length is the along track distance which is imaged and over which the performance requirements have to be predicted and verified. Product Location Accuracy Product coverage location accuracy is defined as the maximum difference between the locations of the area specified in an acquisition order and that of the SAR image actually acquired. In other words, the product coverage location accuracy defines the maximum allowable deviation of the location of a recorded scene from the specified one. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 40 of 76 Radiometric Accuracy For a distributed target, the radiometric accuracy is defined as the worst-case uncertainty resulting from measurement of σ 0 of an uniform invariant distributed target situated anywhere in the operating dynamic range of the system, anywhere in the swath and anywhere in the orbit assuming that the standard deviation of the estimate of σ 0 associated with each measurement is zero (ignoring speckle). For a point target, the radiometric accuracy is defined as the worst-case 3> uncertainty resulting from measurement of the radar cross section, σ p , of a point target which lies in the range: σ 0 min ⋅ x ⋅ y < σ p < 75dB ⋅ m 2 where: • • σ 0 min is the value of NESZ at the bottom end of the specific dynamic range x ⋅ y are the measured spatial resolutions in the along track and across track directions respectively The point target may be located anywhere within the swath at any point within the orbit. The determination of absolute back-scattering values will in general involve calibration measurements over characterised reference targets to be referred to as external calibration. Two parameters are used in defining the radiometric accuracy: The worst-case errors due to all causes which produce errors that are invariant or vary slowly with respect to the orbit, The worst-case errors due to all causes, both those in a) and those that are independent from measurement to measurement of the target (e.g. due to different position within the swath). Changing propagation path characteristics shall be accounted for by assuming uncertainty concerning the presence or absence of rain. The required parameter for radiometric accuracy shall relate to parameter b) above. Parameter a) shall however be supplied for information. Radiometric Resolution The radiometric resolution of a Level 1 product is a measure of the ability to distinguish between uniform distributed targets with different backscattering coefficient. It is defined as the width of the probability distribution function of the signal power received from uniform distributed targets. It is measured on a uniform distributed target, large enough to ensure statistical accuracy, as: Rad Re s = 10 log10 (1 + q r ) qr = σ µ Where: µ , σ and qr are respectively the mean, the standard deviation and the normalised standard deviation (or coefficient of variation) of signal power over the selected distributed target. Radiometric Stability Radiometric stability is defined as the standard deviation of a data set that results from measuring the radar cross section of an invariant target, at different times, being of such magnitude that receiver noise is insignificant, with the system operating within its dynamic range. Perturbations due to the propagation path shall be neglected. There shall be no limitation on the position of the target inside the swath and along the orbit. The time scale applicable for this specification is the duration planned between external calibrations. Relative Phase Error The interferometric phase is defined as the phase difference resulting from the geometric path difference when observing the same target from different positions. The relative interferometric phase error is defined as the contribution to the phase difference between two measurements of the same target from different positions that is not resulting from the geometrical path difference. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 41 of 76 Relative Radiometric Accuracy Relative radiometric accuracy is defined as the standard deviation of a data set that results from measuring the radar cross section of equivalent targets at the same time at different locations within the product coverage. This includes stability effects within the time needed for the acquisition of the basic product. Resolution Bandwidth (RBW) This is the bandwidth over which the chirp must meet the phase and amplitude error specifications. RF Pulsewidth This corresponds to the 3dB bandwidth of the RF pulse. It is specified in the time domain but is related to the frequency domain due to the Chirp Slope (see entry ealier). ScanSAR Lower resolution, large area SAR imaging mode with several simultaneous beams and principally unlimited azimuth extent of acquisition. Spatial resolution The spatial resolution is specified as the width of the IRF where the intensity is 50% of the peak value. The spatial resolution is given in metres and divided into along-track and across-track resolution. Spurious Side-lobe Ratio (SSLR) The spurious sidelobe ratio is specified as the ratio of the peak intensity of the main lobe of IRF to the peak intensity of the most intense side-lobe outside a rectangular image area of 10x in the along-track and 10y in the across-track direction. x and y are the along-track and across-track resolutions in meters, respectively. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 42 of 76 4.3 Spacecraft and Platform Right-Looking Attitude, in which the front end co-ordinate system +Zas axis is tilted 28 degrees away from nadir in anti-Sun direction (+28degrees elevation angle). See Figure 5.2-1. Left-Looking Attitude, in which the front end co-ordinate system +Zas axis is tilted 28 degrees away from nadir in the Sun direction (-28degrees elevation angle). See Figure 5.2-1. Pointing Accuracy Pointing accuracy is the deviation of the actual pointing vector from the ideal pointing vector at any instant Instrument Line of Sight In case of a phased array, the instrument Line of Sight is normal to the plane determined by a best-fit of the actual surface defined by the instrument antenna phase centres. In stable conditions, i.e. during ground characterisation tests, it is related to the instrument optical reference cube axes through a customer furnished transformation matrix, defined during those ground characterisation and alignment tests. Electronic internal instrument pointing knowledge and electrical stability are excluded from this definition. Antenna Boresight Antenna Boresight is the direction of the maximum radiation of the antenna when the aperture illumination is set to uniform gain and phase for no beam-steering (i.e. in case of a phased array all sub-arrays would be set uniformly at nominal maximum amplitude and uniform phase distribution). If mechanical distortions induced by environmental loads are negligible, the difference between Line of Sight and Antenna Boresight for a phased-array is caused solely by drift or deviation of the sub-array settings. Instrument Mounting Interface Instrument Mounting Interface is the interface provided by the Spacecraft to the relevant instrument and associated mounting insert patterns. Antenna Elevation Angle The Antenna Elevation Angle (θel) is defined as the sum of the Mechanical Boresight Elevation Angle (θΜΒel) and the Electrical Elevation Angle (θΕel), which are defined as follows: • The Mechanical Boresight Elevation Angle θΜΒel (± 90º) is defined in the Yas * Zas plane as the angle between the negative direction of the L1 axis of the Local Relative Orbital Reference Frame (local nadir) and the +Zas axis of the Antenna Reference Frame, where positive angle is measured from the negative direction of L' (local nadir) towards the +Yas direction. • The Electrical Elevation Angle θΕel (± 90º) is defined in the Yas * Zas plane relative to the +Zas-axis with positive values towards the +Yas-axis. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 43 of 76 Antenna Azimuth Angle The Antenna Azimuth Angle, Φaz (± 90º) is defined in the Xas * Zas plane as the angle between the negative direction of the L' axis of the Local Relative Orbital Reference Frame (local nadir) and the +Zas axis of the Antenna Reference Frame, where positive angle is measured from the negative direction of L1 (local nadir) towards the +Xas direction. Total User Capacity The total user capacity is defined as the memory space available for storage and retrieval of user data excluding the memory space used for DMSS internal error detection and error correction (EDAC based on Reed-Solomon Code). Files Files are a set of one ore more memory segments which are allocated to store Instrument or ancillary date sets. Each file is identified by a unique file identifier. Instrument Data Set The Instrument Data Set are those instrument data which are obtained from an uninterrupted operation of the SAR instrument in a single measurement mode (generally, the data for one SAR Product). An Instrument Data Set is composed of a number of ESA PSS-04 source packets. The number and length of the source packets can be different for each Instrument Data Set. The length of the source packets is variable within one Instrument Data Set. The size of an Instrument Data Set can vary between 1 and the maximum number of free Memory Segments. Free in this context means: the Memory Segments are not allocated to files. Channel Data Access Unit (CADU) A CADU is the protocol data unit in which Telemetry Packets are embedded for transmission through the downlink data channel. Data Sizing Definitions For use in memory sizing only (not RF link) • • • 1kbit = 2^10 bits = 1024 bits 1Mbit = 2^20 bits = 1024 kbits = 1048576 bits 1Gbit = 2^30 bits = 1024 Mbits = 1048576 kbits = 1073741824 bits Reference Orbit Repeat Cycle The Reference Orbit Repeat Cycle is the predicted repeat cycle expected at the beginning of life of the spacecraft, used for comparison with subsequent repeat cycles in order to determine the orbital tube radius error of those cycles. It shall be agreed between the Prime Contractor and the Agency. Orbit State Vector The orbit state vector of the spacecraft is defined as the PVT data outputted by the GNSS receiver subsystem on-board when in its measurement mode. During outages of the GNSS receiver e.g. when not in its measurement mode, the orbit state vector of the spacecraft is defined as the PVT data outputted by the orbit propagation function of the Navigation Estimator in the AOCS. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 44 of 76 Vital (Mission Critical) Functions Vital (or Mission Critical) functions are those that, if not executed, or wrongly executed, could cause permanent mission degradation. Hazardous Functions Hazardous functions are those which when executed at the incorrect time could cause permanent mission degradation or damage to equipment, facilities or personnel. Permanent Mission Degradation Permanent mission degradation means, that nominal S/C function or performance can neither be achieved on the nominal nor on any redundant chain for the remainder of the mission lifetime. Reference Orbit (tbc) The following reference orbit is defined: • Type: Near-Polar-Sun-Synchronous • Mean Local Solar Time at ascending Node: 18:00 h (nominal) • Repeat Cycle: 12 days • Cycle Length: 175 orbits Defined for an epoch, the mean-keplerian orbital parameters for the reference orbit are: • • • • • • Semi-Major axis: 7070995 m Eccentricity: 0.001184 Inclination: 98.137° Argument of Perigee: 90° Longitude of Ascending Node: 279.248° Mean Anomaly: 269.924° EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 45 of 76 4.4 Ground Segment Acquisition Station A facility for acquiring satellite data and in some cases for archiving and performing production and shipment on demand. Data can be acquired only when the satellite (or the Data Relay Satellite) is seen by the station. Archive (near line) Part of the archive that needs automated manipulation of media to access archived data. Near line archive is generally implemented using high-density data tape robots. Archive (off-line) Part of the archive that needs human manipulation of data. Off-line archive is generally implemented on high density data tapes held on shelves. Archive (on-line) Part of the archive that can be accessed without any human or mechanised manipulation of archive media. On-line archive is generally implemented on high capacity computer disks Auxiliary Data Auxiliary data are data required to perform the processing of the SAR data that are not obtained from the SAR instrument itself. Auxiliary data encompass: • Data obtained from other parts of the platform, generally referred to as spacecraft “engineering”, “core housekeeping” or “subsystem” data: they include parameters such as on-board time, PVT vector, pressures, temperatures, etc… • Other data not available from on-board sources Background Mission A set of systematically implemented payload data acquisition rules. Examples of background missions are areas to be covered during specific periods of the year, like fields during the growing season, poles during ice formation, iceberg source areas during melting periods, etc. A background mission can also be linked to the acquisition campaign of a station, particularly for mobile stations Browse Products • • Subsets of data set other than the directory and metadata that facilitate user’s selection of specific data having the required characteristics. For example, for image data, browse data could be a single channel or multi-channel and is generally unique for each type of data. It depends on the nature of the data and on the criteria used for data selection within the related science discipline. Data produced primarily to provide other investigators with an understanding of the type and quality of available data. Typically, browse data sets are limited in size or resolution. The specific form of browse data depends on the type of instrument or discipline with which the browse data is related. Calibration Calibration is the activity of deriving correction factors to be used in ground processing to compensate for biases in the measured data. Calibration activities encompass: • Internal Calibration • External Calibration • Geophysical Calibration EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 46 of 76 Calibration (External Calibration) External Calibration is the derivation of correction factors through comparison with independent scales for compensation of overall system errors (within both the space and ground segments). Calibration sites on the ground are typically used for this, with either natural or man-made targets which have known parameters (e.g. location, back scatter). Calibration (Geophysical Calibration) Geophysical calibration involves the use of data to tune models which derive geophysical parameters e.g. wind speed, wind direction, wave height, soil moisture and atmospheric information. The extraction of these parameters from independent ground truth data and atmospheric information involves comparison with the product data and the generation of biases and scaling factors. Any detected systematic deviations are analysed and used to tune the geophysical models. Calibration (Internal Calibration) Internal calibration is the monitoring of functions and parameters within the instrument and the derivation of correction factors to compensate for errors of the internal equipment. The correction factors are applied as part of the ground processing. Catalogue A Catalogue system provides a service enabling the user to obtain detailed information about whole data sets, typically specific to a discipline, data centre or project. A catalogue also allows a user to identify and retrieve individual granules of the data set by specifying independent variable range(s). Having identified a set of granules, which may be of value, a user should be able to review a content of the granule (browse) and place an order for one or more granules. A catalogue is assumed to provide three primary services: Directory Service, Guide Service and Inventory service (see corresponding definitions)., supplemented by secondary application specific services, typically including browse and ordering. Catalogue – Local Catalogue A local catalogue is associated to a data set archived at a given site or centre. It reflects exactly the content of the archive to which it is associated. Catalogue – Master Catalogue The master catalogue is made of the sum of the catalogues held at distributed locations. It mirrors then the overall contents of the products archives within the whole ground segment. It includes in addition the catalogue of planned products, according to the actual data take schedule. The master catalogue is not directly accessible to users. Catalogue – User Catalogue The user catalogue is a copy of the master catalogue, from which records can be hidden to users. Data Product The result of the processing of remote sensing data. Products are specific to each mission and sensor combinations. A data product can be an entire acquisition strip (the data segment continuously acquired by a ground station) or a single frame (a subset of the acquisition strip of standard length as defined by the WRS). Data Take A data take is a continuous set of data acquired by the instrument operating in a given mode. Any change of instrument mode or e.g. incidence angle is triggering the start of a new data take. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 47 of 76 Data Take Segment A data take Segment (DT Segment) is a subset of a data take. A data take needs to be segmented if it cannot be dumped in a single pass over a given acquisition station. Dissemination Dissemination is the process allowing to distribute products and data to users. Dissemination can be made via electronic link (terrestrial or satellite based) or on physical media (CD-ROM, DVD, HDDT). Dissemination Plan For each facility in charge of disseminating products towards end users, the dissemination plan specifies the timely organisation of dissemination operations. Entity Combination of facility plus respective personnel or operations organisation Facility Combination of ground segment elements required to perform an operational task. Flight Operations All activities related to the planning, execution and evaluation of the control of the space segment when in orbit. Formatting The conversion of the format of the products held in the PGS archives (internal format) into a format readable on the user’s computer platform (external format). FOS Flight Operations Segment, the facilities responsible for the spacecraft monitoring and control activities. GMES Global Monitoring for Environment and Security. A joint European Commission and European Space Agency initiative. Granule A granule is the smallest subdivision of a L1B product that can be independently ordered, processed and distributed to a user. Ground Operations All activities related to the planning, execution and evaluation of the control of the ground segment facility. Ground Segment All ground segment facilities and personnel involved in the preparation or execution of mission operations. Ground Systems All ground infrastructure elements that are used to support the preparation activities leading up to mission operations, the conduct of mission operations and all post-operational activities. Instrument (data take) schedule The instrument (data take) schedule defines the timely utilisation of the on-board instrument over a given period of time, including time of sensing start and termination and specifying the sensing mode. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 48 of 76 Inventory Collection of items identically structured and providing values of attributes pertinent to that collection. EO inventories contain attributes like orbit/frame number, frame corner co-ordinates, acquisition time, quality, etc. Metadata Data about data contained in data sets, and which provide an understanding of the content and utility of the data set. Metadata may be used to select data for a particular application. Mission The specific function to be accomplished by a system as characterised by its expected products in terms of quantity, quality and availability. Mission exploitation Activity comprising the planning, utilisation and evaluation of the products of the space mission. Mission operation All activities related to the planning, execution and evaluation of the control of the space and ground segments during phases E and F of a space system, i.e. combination of flight and ground operations. Mission operations data Subset of mission information used to execute the in-orbit operations. Mission Planning Mission planning encompasses the whole set of activities / operations that are required to schedule the utilisation of the on-board instrument and to organise, monitor and control on the ground operations for data downlink, generation of products and their dissemination to the users. Mission products Products and services delivered by the space segment as the result of its in-orbit exploitation, e.g. science data. MPS Mission Planning and Scheduling. Includes all activities relating to the processing of planning input and planning requests, the resolution of planning conflicts and the planning of on-board and ground resources utilisation. It also includes the preparation of plans, schedules or timelines of operations as a result of the planning exercise. NRT Processing Near Real Time (NRT) Processing infers that processing of the mission products and their delivery to the requesting users occurs within a short time from sensing. In the Sentinel-1 case, the requirement is to acquire, process and deliver within 3 hours from sensing. Off-line processing Off-line processing refers to the non systematic (on-demand) processing of archived products to serve specific users requests EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 49 of 76 Orbit Data (Precise) Precise orbit data are highly accurate orbit data derived from GNSS raw data acquired on board (pseudo range data). They are used for accurate geo-referencing of products. Orbit Data (Predicted) The predicted orbit data provides the forecast of the spacecraft orbit vector (position and velocity) as a function of time, over a given period (ephemeris file) Orbit Data (Restituted) The restituted orbit provides the actual spacecraft orbit vector (position and velocity) as a function of time, as derived from the GNSS measurements performed on-board, or from specific orbit determination sessions (using for instance range Doppler measurements) Order Direction issued by a user to the PGS for the provision of one or several products or services, for which the customer will accept the charge if appropriate. Order – Complex Order Highest level of the orders placed by users that can eventually trigger the delivery of a large number of products over an extended period of time. Order – Coverage Order A coverage order is made of a set of basic products sensed at a time as close as possible to a user specified date that covers the whole area selected by the user (so that a mosaic product over the whole region of interest can be created). For a coverage order the user does not need to select the individual products that populate the order, instead the system will do the job for him. Order – Emergency Order An emergency order is an order which requires to generate and uplink a data take request in short notice, outside the nominal mission planning cycle. Order – Joint Order A joint order is made of a Sentinel-1 product and a product from one of the companion missions, covering the same geographical area and for which the time of sensing difference does not exceed a user specified time span. Order – Mission Order Mission-Orders are generally long-term, systematic orders for new acquisitions directly introduced in the system by the Mission Operator. The objective of mission orders is to ensure that key areas of interest are adequately covered based on the needs of selected driving applications. Order – Order Line The order line results from the decomposition of a complex order into single orders, each of them triggering the delivery of one single product. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 50 of 76 Order – Near Real Time (NRT) Order An order entailing downlink, processing and product delivery to the requesting users within less than 3 hours (TBC) from sensing. Order – Single Order A single order is an order that triggers the delivery of one single basic product to the user requesting that order. The product can either be generated from the archive or require a new acquisition. Order – Standing Order A standing order (or time series order) is made of a temporal (time series) set of basic products covering a user specified region of interest over a given period of time at a user specified frequency (e.g. regular acquisition – processing – delivery of data for a period of 6 months each week). In the case of a standing order, the user may specify his/her ROI, the time span of the order and the minimum/maximum frequency of acquisition / delivery.. Order – Subscription (from archive) Order A subscription orders is a mechanism allowing a user to request the systematic delivery of products from the archive over a given ROI and a given time period, whenever these products become available. Order – Time Series Order Same as “Standing Order” Order to Acquisition Time Time, from placing an order, to create a data product centred at an arbitrary location to the next possible acquisition of the raw radar signal data by the satellite. As an order can be placed at any time in the orbit cycle the appropriate values for 5% probability of compliance and for 95% probability of compliance are specified when the product location is arbitrarily selected within the requested access area. In all cases where two access or processing times are identified, the less demanding one is associated with 95% of required data-sets and the more demanding one with 5%. Payload Ground Segment The facilities responsible for the acquisition, archiving, processing and dissemination of the instrument data and basic products. Pointing Data Pointing data encompass the whole set of data required by a receiving station to point its antenna towards the anticipated location of the satellite above the horizon. They consist generally in AOS/LOS times and Two Line Elements (TLE) files providing azimuth and elevation data as a function of time. Priority Different priority levels are attached to users orders and to the requests resulting from their decomposition. These priority levels are used to establish the instrument data take schedule and to schedule the downlink, processing and dissemination operations on ground according to the available resources. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 51 of 76 Production Plan For each facility in charge of products generation, the production plan specifies the timely organisation of products generation activities. Raw Data The data received on ground from the satellite prior to the application of any processing algorithm Region Of Interest (ROI) Geographic area relevant for the process. In its more general form it can be defined for example as one or more (or a combination of): • rectangle (usually with sides aligned with the latitude / longitude grid) • circle • polygon • name (of a site, a region, a country, a town, a river, etc., or of multiple sites together, like volcanoes) Replay A Replay is a unit of data comprising one or several Data Takes or a Data Take Segment downlinked to a Ground Station during one ground contact period. (TBC). Replay Key A Replay Key (RK) is a decryption key linked to a given replay. Request A request is the lowest level of decomposition of an order. Four types of requests are defined within the system: • Data take requests, which relate to the continuous sensing of a given area by the on-board sensor operating in a given mode • Downlink requests which relate to the downlink of a data take segment towards a given receiving station • Processing requests which relate to the generation of a Level 1B product from newly acquired or archived Level 0 data • Dissemination requests which relate to the delivery to a user of a product after it has been processed Requests Data Base The Requests Data Base contains all users’ orders and their lower level decomposition into order lines and requests. It is the reference for the PGS operators to establish the instrument data take schedule and mission plan, and for the users to be kept informed about the status of their orders. Routine processing Routine processing refers to the daily systematic processing of all data received within a given time frame. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 52 of 76 4.5 Lifetime Spacecraft Beginning-of-Life The point at which spacecraft in-orbit commissioning activity ceases and the spacecraft useful lifetime (payload imaging operations) begins. Spacecraft End-of-Life The time at which the Spacecraft-specific (i.e. not System-level) operational performance (imaging) ceases to be compliant with Customer End-of-Life (EOL) requirements, or the time at which the specified duration for which the spacecraft operational performance (imaging) requirements are valid elapses, whichever is sooner. Spacecraft Useful Lifetime The Spacecraft Useful Lifetime is defined as the duration from the end of the Spacecraft Commissioning Phase, i.e. Spacecraft BOL, to the end of the useful payload operations, i.e. Spacecraft EOL. In-Orbit Payload Design Lifetime Total in-orbit duration of Spacecraft from Launch to Spacecraft End-of-Life. In-Orbit Platform Design Lifetime Total in-orbit duration of Spacecraft from Launch to the end of the controlled decommissioning orbital manoeuvre activities System End-of-Life The time at which the System-level (i.e. not Spacecraft-level) operational performance (imaging) ceases to be compliant with Customer End-of-Life (EOL) requirements, or the time at which the specified duration for which the system operational performance (imaging) requirements are valid elapses, whichever is sooner. System Lifetime (Mission Lifetime) The System Lifetime is defined as the duration from the end of the System Commissioning Phase to System EOL. The relationship between the above lifetime definitions is shown figuratively in Figure 4.5-1 below. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE S1-LI-ASU-PL-0011 Issue 1 Page 53 of 76 Sentinel-1 TerraSARL S/C Launch In-Orbit Platform Design Lifetime In-Orbit Payload Design Lifetime S/C Useful Lifetime S/C Beginning of Life S/C End of Life System Lifetime Commissioning Phase System Operational Phase System Commissioning Phase TerraSAR-L S/C Launch and Early Orbit Phase S/C Commissioning Phase TerraSAR-L S/C Development and Integration Phase Disposal Phase De-orbit manoeuvres Re-entry G/S available Figure 4.5-1: Relationship of Lifetime Definitions to Mission Phases EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE S1-LI-ASU-PL-0011 Issue 1 Page 54 of 76 Sentinel-1 5. BACKSCATTERING MODEL 5.1 Terrain The backscattering model to be used for terrain is the Short Vegetation Model based in F. T. Ulaby and M. C. Dobson. It is shown in dB in Table 4.1-1 and Figure 4.1-1, for the three polarisations (HH, HV and VV) and the incidence angles from 20° to 45°. Inc angle HH HV VV 20 -7.61 -15.59 -7.64 25 -9.07 -16.33 -8.98 30 -10.31 -16.95 -10.05 35 -11.32 -17.47 -10.92 40 -12.17 -17.90 -11.61 45 -12.86 -18.29 -12.19 Table 5.1-1 Backscattering coefficient of terrain C-band sigma0 for terrain 0.00 20 25 30 35 40 Sigma0 (dB) -5.00 HH -10.00 HV VV -15.00 -20.00 Incidence Angle Figure 5.1-1 Backscatering coefficient of terrain 5.2 Ocean For Ocean, the backscattering model to be used is shown in the following Table 5.2-1 and in Figure 5.2-1 and Figure 5.2-2. HH 20 deg 30 deg 45 deg VV 20 deg 30 deg 45 deg 2 m/s -2.49 -15.53 -27.77 4 m/s -0.41 -11.79 -23.54 6 m/s 0.75 -9.68 -21.06 8 m/s 1.54 -8.21 -19.29 10 m/s 2.13 -7.09 -17.92 12 m/s 2.60 -6.19 -16.79 14 m/s 2.99 -5.44 -15.84 -1.44 -13.46 -22.99 0.38 -9.42 -18.29 1.40 -7.11 -15.59 2.10 -5.51 -13.70 2.64 -4.29 -12.26 3.09 -3.31 -11.08 3.48 -2.49 -10.09 Table 5.2-1 Ocean Backscattering Model for C Band (5.3 GHz) EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE S1-LI-ASU-PL-0011 Issue 1 Page 55 of 76 Sentinel-1 Ocean Backscattering (HH) 5.00 0.00 Average NRCS (deg) 20 25 30 35 40 45 -5.00 2 m/s 4 m/s 6 m/s -10.00 8 m/s -15.00 10 m/s 12 m/s -20.00 14 m/s -25.00 -30.00 Incidence Angle (deg) Figure 5.2-1 Ocean Backscattering for C band (5.3 GHz) in HH polarisation Ocean Backscattering (VV) 5.00 0.00 Average NRCS (dB) 20 25 30 35 40 45 -5.00 2 m/s 4 m/s 6 m/s -10.00 8 m/s 10 m/s 12 m/s -15.00 14 m/s -20.00 -25.00 Incidence Angle (deg) Figure 5.2-2 Ocean Backscattering for C band (5.3 GHz) in VV polarisation] EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE S1-LI-ASU-PL-0011 Issue 1 Page 56 of 76 Sentinel-1 6. REFERENCE FRAMES These have been developed from ESA SRD Annex B. Further definition may be found in the AOCS Reference Frames Technical Note (to be issued). INERTIAL FRAME, GRAVITY MODEL AND REFERENCE ELLIPSOID An Earth Centred Inertial (ECI) reference frame will be used for orbit propagation, defined by the J2000 equatorial coordinate system as follows: the origin OJ2000 is at the centre of the earth, the XJ2000 axis is at the intersection of the mean ecliptic plane with the mean equatorial plane at the date of 01/01/2000 and pointing positively towards the vernal equinox, the ZJ2000 axis is orthogonal to the mean equatorial plane at the date of 01/01/2000 and pointing positively towards the north, the YJ2000 axis completes the right handed reference frame. The coefficients J0, J2, J3, J4 and J22 of the gravity model GEM-T1 (see RD2) will be used for the Sentinel1 satellite orbit propagation. An Earth Centred Earth Fixed (ECEF) reference frame defined by the reference ellipsoid WGS84 (see RD3) will be used for calculations of position, altitude and attitude. REFERENCE FRAMES Local Orbital Reference Frame (T, R, L) V R T L S/C CoG Geocentre The origin of the Local Orbital Reference Frame is the Spacecraft in-flight centre of mass G. The unit vector L is in the direction opposite to the Earth's centre, the geocentre. The unit vector R is perpendicular to L and in the vertical plane containing V such that: cos(V,R)>0, where V is the inertial velocity vector. The unit vector T completes the right-handed frame: T=RxL T, R, L being the pitch (Tangage), roll (Roulis) and yaw (Lacet) axes respectively. NOTE: Being P the inertial position and V the inertial velocity, the formulation can be written as: • • • L = P / |P|, T = V x L / |V x L|, R=LxT EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE S1-LI-ASU-PL-0011 Issue 1 Page 57 of 76 Sentinel-1 Local Relative Orbital Reference Frame (T’, R’, L’) V Earth reference ellipsoid (WGS84) R’ T’ L’ S/C CoG The Local Relative Orbital Reference Frame (T', R', L') has the same definition as the Local Orbital Reference Frame except for the local normal pointing as follows: The unit vector L' (local normal pointing) is parallel to the local normal of the earth's reference ellipsoid which is the WGS84 model as defined in (RD3) directed upward and crossing the Spacecraft centre of mass G (T', R', L') defines the absolute pointing of the Spacecraft for the Fine Pointing Mode (FPM) and Attitude Steering Mode (ASM) with T', R', L', being the pitch, roll and yaw axes respectively. Spacecraft Reference Frame (XSC, YSC, ZSC) The Spacecraft Reference Frame coordinate system is a right-handed Cartesian system designated by the standard subscript “SC” (e.g. Xsc). See Figure 6.1. This coordinate system is fixed to the Spacecraft and invariant for both stowed and deployed configurations: • The origin of the Spacecraft Reference Frame Coordinate System is within the Spacecraft to Launch vehicle separation plane, with the Zsc axis running through the geometric centre of the –Z spacecraft panel. • The Xsc axis is parallel to the long axis of the SAR antenna, and positive in the direction of the Spacecraft velocity vector when the spacecraft is in its nominal attitude • The Zsc axis is perpendicular to the P/L Instrument (Antenna, …) radiating/observing face and positive in the direction of P/L radiation/observation. • The Ysc axis is oriented in order to complete the right-handed orthogonal coordinate system. All mechanical and geometric parameters will ultimately be referenced to this axis system including unit positions and mass properties. Spacecraft panel coordinate systems will also be referenced to the “SC” axes and identified in the relevant Interface Control Documents/Drawings EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 58 of 76 Zsc Xsc L/V-S/C Separation Plane Launch Vehicle Figure 6.1 - Spacecraft Reference Frame Coordinate System EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE S1-LI-ASU-PL-0011 Issue 1 Page 59 of 76 Sentinel-1 Front-End Co-ordinate System The coordinate system of the Antenna Front End is defined by the axes Xas; Yas; Zas; shown below. The origin of this coordinate system is located on the geometrical centre of the radiator plane, at a distance from the spacecraft origin chosen by the Payload Prime. • +Xas-axis: length direction of the radiator (corresponds approximately to azimuth direction or flight direction) • +Zas-axis: normal to the radiator plane and positive in the direction of the radiator boresight • +Yas-axis: completes the right-handed set (thus positive corresponds approximately to elevation or across-flight direction away from the Sun) Yas Yas Xas Xas +θEel Zas -θEel Zas θ MBel Nadir • Yas Xas +φaz -φaz Flight Direction Zas Figure 5.2-1 Front-End Co-ordinate System EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 60 of 76 7. SPACECRAFT NOMINAL MODES & POINTING DEFINITIONS Fine Pointing Mode The commanded reference frame when in Fine Pointing Mode is defined as follows: • Xsg is in the orbit plane perpendicular to the local normal (outward direction) of the Earth reference ellipsoid, WGS84, closely aligned to the velocity vector direction. • Zsg is perpendicular to Xsg, rotated with respect to the local normal to the Earth reference ellipsoid, the angle corresponding to the antenna boresight, as specified in the nominal right-looking or the left-looking AOCS configurations. • Ysg completes the right-handed orthogonal co-ordinate system Xsg = Ysg x Zsg where Xsg, Ysg, Zsg is the Spacecraft Reference Frame (Xsc, Ysc and Zsc) translated to the actual Spacecraft centre of mass. The control law in Fine Pointing Mode is defined in the Local Relative Reference Frame (defined in section 5 above). Attitude Steering Mode The Attitude Steering Mode is defined for the radar echo signal to have zero Doppler shift over the whole access range.The commanded reference frame when in Attitude Steering Mode is derived from the Fine Pointing Mode commanded reference frame with the following changes: • • The compensation of Earth rotation effects is achieved by steering the Spacecraft (Xsg, Ysg and Zsg) so that the projections of the Xsg axis across the SAR antenna access swath on the tangential plane on the earth model surface, coincide with the projected relative velocity vectors (relative ground trace velocity vector) between such sub-satellite point and the earth model surface. The corresponding Zero-Doppler Attitude Steering Law is defined in IRD 02. The control law in Attitude Steering Mode is defined in the Local Relative Orbital Reference Frame (defined in section 5 above). As in Fine Pointing Mode, the absolute pointing of the Spacecraft for the Attitude Steering Mode is defined in the Local Relative Orbital Reference Frame, in T', R' and L' being the pitch, roll and yaw axes respectively, with respect to the defined Zero-Doppler Attitude Steering Law. Pointing Accuracy Pointing accuracy is the deviation of the actual pointing vector from the ideal pointing vector at any instant Instrument Line of Sight In case of a phased array, the instrument Line of Sight is normal to the plane determined by a best-fit of the actual surface defined by the instrument antenna phase centres. In stable conditions, i.e. during ground characterisation tests, it is related to the instrument optical reference cube axes through a customer furnished transformation matrix, defined during those ground characterisation and alignment tests. Electronic internal instrument pointing knowledge and electrical stability are excluded from this definition. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 61 of 76 Antenna Boresight Antenna Boresight is the direction of the maximum radiation of the antenna when the aperture illumination is set to uniform gain and phase for no beam-steering (i.e. in case of a phased array all sub-arrays would be set uniformly at nominal maximum amplitude and uniform phase distribution). If mechanical distortions induced by environmental loads are negligible, the difference between Line of Sight and Antenna Boresight for a phased-array is caused solely by drift or deviation of the sub-array settings. Instrument Mounting Interface Instrument Mounting Interface is the interface provided by the Spacecraft to the relevant instrument and associated mounting insert patterns. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 62 of 76 8. PHASE AND AMPLITUDE ERRORS The following provides a definition of the pulse and pulse-to-pulse phase and amplitude error types in the time domain. Let a series of N input chirps Si(t), be passed through a DUT at the appropriate PRF, giving the output chirps Yi(t) such that: ⎛t⎞ Si (t ) = Ai (t ) ⋅ e j⋅φi (t ) ⋅ rect ⎜ ⎟ ⎝T ⎠ i = 1,.2...., N ⎛t⎞ Yi (t ) = Bi (t ) ⋅ e j⋅θi (t ) ⋅ rect ⎜ ⎟ ⎝T ⎠ i = 1,.2...., N where N Ai (t ) φi (t ) Bi (t ) θ i (t ) T = = Number of pulses input waveform amplitude function = input waveform phase function = output waveform amplitude function = output waveform phase function = pulse length ⎛t⎞ rect ⎜ ⎟ = ⎝T ⎠ ⎧1 ⎨ ⎩0 −T / 2 ≤ t ≤ T / 2 elsewhere Define the function : X i (t ) = Yi (t ) Si (t ) ⎛t⎞ = Ci (t ) ⋅ e j⋅δ i (t ) ⋅ rect ⎜ ⎟ ⎝T ⎠ Amplitude deviation within pulse: Ci (t ) = C0,i + C1,i ⋅ t + C2,i ⋅ t 2 + N i (t ) Phase deviation within pulse δ i (t ) = δ 0,i + δ1,i ⋅ t + δ 2,i ⋅ t 2 + niphase (t ) Define normalised error terms: b1,i = c1,i c0,i b2,i = c2,i c0,i EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 63 of 76 8.1 Absolute Within Pulse Errors Amplitude linear error (peak to peak): ε iamp ,lin , pp = 20 ⋅ log10 (1 + b1,i ⋅ T ) Amplitude quadratic error: (peak to peak) ⎛ ε iamp ,quad , pp = 20 ⋅ log10 ⎜⎜1 + ⎝ b2,i ⋅ T 2 ⎞ ⎟ 4 ⎟⎠ Amplitude error due to ripple and noise (one sigma): ε iamp ,noise,1σ = 20 ⋅ log10 (1 + SD( N i (t ))) Phase linear error, in units of degrees (peak to peak): ⎛ 180 ⎞ ⎟ ⋅ δ1,i ⋅ T ⎝ π ⎠ ε iphase,lin , pp = ⎜ Phase quadratic error, in units of degrees (peak to peak): εi T ⎛ 180 ⎞ =⎜ ⎟ ⋅ δ 2 ,i ⋅ 4 ⎝ π ⎠ 2 phase , quad , pp Phase error due to ripples and noise , in units of degrees (one sigma): ⎛ 180 ⎞ phase ⎟ ⋅ SD (ni (t )) ⎝ π ⎠ ε iphase,noise+ ripple,1σ = ⎜ 8.2 Relative Within Pulse Errors For relative within pulse errors, the function Xi(t) is defined as: X i (t ) = Yi (t ) Si (t ) ⋅ Z i (t ) where Zi(t) is the function against which the relative errors are defined. The error components are then defined as for the absolute errors. 8.3 Pulse to Pulse Errors over Coherent Subaperture For i = 1, …. , N define: Average amplitude of pulse i (at time ti) T /2 1 A(ti ) = ⋅ ∫ Ci (t ) ⋅ dt T −T / 2 EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 64 of 76 Average phase of pulse i (at time ti) T /2 1 ϕ (ti ) = ⋅ ∫ φi ⋅ dt T −T / 2 Pulse repetition interval is PRI. ∆T = PRI t i = i ⋅ ∆T Suppose the functions follows: A(t i ) and A(ti ) = A0 + A1 ⋅ ti + A2 ⋅ ti2 + N PP ϕ (ti ) are resolved into linear, quadratic, ripple+noise components as (ti ) ϕ (ti ) = ϕ 0 + ϕ1 ⋅ ti + ϕ 2 ⋅ ti2 + n phase (ti ) PP Where the origin of time to is assumed to be taken halfway through the subaperture period of N PRIs. Normalise amplitude such that the average pulse amplitude at to is unity. Thus: B(ti ) = B0 + B1 ⋅ ti + B2 ⋅ ti2 + N PP (ti ) where: A Bn = n , A(t0 ) (ti ) = N (ti ) A(t0 ) PP N PP The various categories of errors can now be defined as for the within pulse errors case. Interpulse linear amplitude error, peak to peak: amp ,lin , pp ε interpulse = 20 ⋅ log10 (1 + B1 ⋅ N ⋅ ∆T ) Interpulse quadratic amplitude error, peak to peak: ε amp , quad , pp interpulse ⎛ B2 ⋅ ( N ⋅ ∆T )2 ⎞ ⎟ = 20 ⋅ log10 ⎜⎜1 + ⎟ 4 ⎝ ⎠ EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 65 of 76 Interpulse amplitude error due to noise and ripple , one sigma: amp , noise ,1σ ε interpulse = 20 ⋅ log10 (1 + SD (N PP (ti ))) Interpulse linear phase error, peak to peak and in units of degrees: ⎛ 180 ⎞ ⎟ ⋅ ϕ1 ⋅ N ⋅ ∆T ⎝ π ⎠ phase ,lin , pp =⎜ ε interpulse Interpulse quadratic phase error, peak to peak and in units of degrees: (N ⋅ ∆T ) ⎛ 180 ⎞ ⎟ ⋅ϕ2 ⋅ 4 ⎝ π ⎠ 2 phase , quad , pp =⎜ ε interpulse Interpulse phase error due to noise and ripples , peak to peak and in units of degrees: ( ) PP ⎛ 180 ⎞ ⎟ ⋅ SD n phase (ti ) ⎝ π ⎠ phase , noise + ripple ,1σ ε interpulse =⎜ 8.4 Stability over time intervals Stability of parameters is defined over given time spans (e.g. in several cases over 10 minutes). It is to be considered that the satellite imposes temperature changes at TBD rate on the SES. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 66 of 76 9. OTHER DEFINITIONS Term Explanation Acquisition Acquisition is used in different meanings: atomic item generated by mission planning (a piece of information about an acquisition) raw data acquired by the satellite for a single product order item Note that for single product order items the relation between order items and acquisitions is n:1 where usually n is 1. Acquisition (Datatake) The process of imaging by the Synthetic Aperture Radar. Acquisition Info Acquisition info contains in principle the acquisition IDs for a downlink and the decryption keys. Acquisition of Signal Begin of a ground-station pass when the satellite comes with active transmitter over the horizon as valid for the ground-station antenna or after the transmitter was turned on. Acquisition Planning feasibility The state of feasibility of an order taking into account the capabilities of the instrument and the temporal and geometrical constraints. (see Feasibility Failure) Acquisition Planning inquiry A user's order for a radar acquisition of which the feasibility is not yet validated. Acquisition Planning Request An order for a radar acquisition, identified by a unique denominator agreed between PGS and MOS including all planning relevant information. Acquisition Planning Request The acquisition planning order defines the requested acquisition as an input for Mission Planning. Auxiliary Data Provision Via the auxiliary data provision (MOS) the PGS can get auxiliary data needed for the TMSP SAR processing. The orbit information is provided in different time frames and corresponding precisions: preliminary, NRT, precise, high precise. Auxiliary Product Ingestion The auxiliary product ingestion processing system gets all orbits provided by the auxiliary product provision of the MOS and transfers them to the Product Library for cataloguing and archiving. The TMSP SAR processing searches and retrieves corresponding auxiliary products for level 1 processing. Auxiliary Products Auxiliary products are needed for the processing of primary instrument data. In the context of Sentinel-1 orbit files, attitude files, calibration data and instrument characteristics are needed for L0 and L1b processing. Each of these data classes may correspond to an auxiliary product type. Availability Profile (Slot File) Information of a downlink station's availability or foreseeable outages. Background Order A background order is a kind of order (item) that specifies acquisitions for archiving of L0 products, but without immediate delivery. Basic Product Basic Products are the processed Sentinel-1 SAR images to be delivered to the user. Central Checkout System User Interface to the spacecraft and subsystems via the manufacturer-supplied EGSE (CCS) during the AIT-phase. The CCS provides the two-way interface (Telemetry and telecommand) to the spacecraft and is provided and operated by GSOC. Coverage Order A coverage order is a kind of order (item) that specifies a region of interest to be covered by acquisitions. Coverage Pre-check The coverage pre-check checks the theoretical feasibility of a possible order with respect to the specified satellite/instrument parameters, the specified region of interest and the specified acquisition time window. Data Quality Check Product The collection of parameters and quicklooks that are required to monitor the health of the SAR sensor and the quality of the acquired data. Data Transfer System Automatic or semi-automatic controlled processes at GSOC for transfer (copying or moving) data-files from one location to one or several other destinations either regularly (configurable schedule) or on request Delivery Package A delivery package corresponds to a user order. It contains products for order items. Delivery Product A delivery product is the result of a post-processing step in order to meet the users needs (e.g. specified format). It may temporarily be stored in the Product Library for delivery by Online/Offline Product Generation&Delivery Direct Access Customer A special Customer, e.g. in the reconnaissance field. The received data are solely used to produce geo-information products for its own and private applications Direct Access Partner A partner acts as regional affiliate of Infoterra. In his Region of Interest (ROI) he has all commercial rights for acquisition of data and marketing of the corresponding products. Compatible Geo-information products are produced and sold to the market EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 Term S1-LI-ASU-PL-0011 Issue 1 Page 67 of 76 Explanation Downlink A downlink (dump) is the data received by a receiving station at a single pass of the satellite, contains acquisitions (or fragments of acquisitions in some cases). Downlink (Datadump) The process of transmitting SAR data to the ground station. Downlink Info Downlink info in principle contains the start and stop time for reception. It is identified by orbit (or time) and receiving station. It is used for reception planning. Dual Polarization Mode Transmit and receive polarization switch using interleaved pulse strategy resulting in two image layers. Dump Synonym for the process of reading out stored data from onboard memory and transmitting it to the ground-station at a high data-rate Execution Planning The process of establishing a timeline of spacecraft and ground activities closest to the time of execution taking into consideration the latest acceptable acquisition planning request. The goal is to establish automated rule based execution planning in accordance with the guidelines given by the strategic planning. Footprint A footprint is an area on the earth surface which is described by a polygon. an area on the earth surface covered by an earth observation product => product footprint an area on the earth surface illuminated by a radar antenna => antenna footprint Footprint Beam Database A Data Base holding information about the accessibility of geographical locations by the available radar beams assuming an orbit which is steered at high precision. Future Product A future product is an order item that specifies a product which needs an acquisition and subsequent processing. Instrument Command A facility which translates the settings of the SAR instrument, which are produced by the Generator Radar Parameter Generator, into instrument specific commands for up-link. Key Encryption key used to establish a secure, non-interferable downlink of SAR data. Launch and Early Orbit Phase Sum and sequence of all activities from the moment the launcher-countdown is initiated until the spacecraft is in a stable and secure configuration in orbit. This phase is typically characterised by around the clock shift-work, special safety requirements and additional ground-network resources needed to perform all necessary activities within the time-frame available. Loss of Signal End of a ground-station pass as the satellite disappears with active transmitter behind the horizon-mask as valid for the ground-station antenna or after the transmitter was turned off. Mission Planning System Part of the MOS which consists of all tools and processes necessary to establish a feasible and optimised timeline for spacecraft and ground activities. Mission programmable Means programmable but fixed for a particular mission i.e. not modifiable via telecommand. Online/Offline Product Generation Operating Tool Online/Offline Product Generation produces a delivery package based on (delivery) products. The operating tool provides unified, interactive monitoring and control of DIMS services and processing systems. Orbit info contains two line elements with orbit parameters used by receiving stations. An appropriate format (TLE TBC) to communicate the spacecraft's orbit Order Accounting is implemented by a commercially available software (SAP). The user order is handed over from Ordering Control for commercial treatment. Order Accounting is responsible for managing quotes, invoices, delivery papers, reports and the customer and prices data base. Order Management handles the business process “ordering” throughout DIMS. It is split into two components, Ordering Control and Order Accounting. Ordering Control handles incoming orders from the User Information Services. It verifies the user order with help of the Product Library information, user and crisis area information. If requested, it initiates an acquisition. If necessary, it initiates the processing of the ordered product. Finally, it requests a post-processing (e.g. formatting) and the delivery product generation to satisfy the user order. Software tool which is used to analyse the interdependence of SAR system parameters on each other and on the image quality. A processing system is the operational unit responsible for the processing of products of one Orbit Info Orbit Info (TLE) Order Accounting Order Management Ordering Control Performance Estimator Processing System EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 Term Processor Producible Product Product Product Type Production Control Radar Parameter Generator Receiving Station SAR Signal Data File Sequence of Events SpotLight Strategic Planning StripMap Swath Preview Time Tag User User Information Services S1-LI-ASU-PL-0011 Issue 1 Page 68 of 76 Explanation or more product types. The actual processing is done by one or more processors. Administrative tasks like cache management and scheduling are performed by the processing system management (PSM). A standard processor is a complex processing algorithm able to convert lower level products to higher level products. Auxiliary processors are used for example to handle metadata or manage files. A producible product is an order item that specifies a product that can be generated from products existing in the Product Library. A product is a defined earth observation data set which is composed of metadata and data files. It is build up by one or more components like primary data or quicklook which are assigned to a specific processing level. A product is either a reference product which is subject for long-term archiving or a delivery product which is temporarily available for customer delivery. A product can be managed as an item in the Product Library. A product type is a collection of products with the same characteristics, e.g. with the same mission, sensor and processing level. Production control is instructed by Ordering Control for the acquisition/production of a product which is not available in the Product Library. Therefore, it organizes processing chain to produce the ordered product. Production Control identifies the relevant processing systems and reports status back to production control. A facility which determines the optimal settings of the SAR instrument on the basis of relevant SAR system parameters and order parameters. The receiving station is a system, which is able to receive TX-data at X-band and S-band frequencies with the desired quality and in the desired elevation range and which enables all steps up to the generation of SAR acquisition files and its decryption. RS-decoded and decrypted instrument source packets extracted from transfer frames. Chronological listing of all major activities (on system and subsystem level) during the Launch and Early Orbit Phase (see above) or other phases to achieve the mission goal for this specific phase. The SoE lists and calls relevant procedures, where all detailed activities are defined. High resolution SAR imaging mode with one beam, azimuth antenna steering and therefore limited azimuth extent of acquisition. The purpose of strategic planning is to express the intention of the project management in agreement with all user groups how to make use of the Sentinel-1 space and ground egment. This may comprises the establishment of protected time-slots, apportionment of available acquisition and reception time, assignment of priorities and acquisition timewindows and definition of decision rules for more detailed planning stages. The strategic planning is supported by the Mission Planning System by indicating predictable conflicts, by determining gradually evolving shortages and by proposing alternative options. Standard SAR imaging mode with one beam and unlimited acquisition length. The swath preview shows the maximum possible field of view of the instrument on the earth surface within a given time window. A time-stamp (relative or absolute) assigned to a telecommand which is planned for automatic execution on-board at the defined time. A user is a person that uses EOWEB to browse and order acquisitions or products. The user information services offer interactive user services, namely information retrieval, product guide and directory, product inventory and browse, ordering, order follow-up and delivery (via pickup-point). User programmable Means settable via telecommand via the C&C bus. User Order A user order is a binding request to acquire or deliver certain products, issued by a user through EOWEB. It defines the user requested order items (products), user information itself and order, processing and delivery options. The procedure for ascertaining that an intended use or application (of a product or service) is successful. The procedure for ascertaining that a requirement/specification is met. Validation Verification EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 69 of 76 10. ECSS TERMS 10.1 ECSS-E-10-02A Acceptance stage A verification stage with the objective of demonstrating that the product is free of workmanship defects and integration errors and ready for its intended use. Analysis A verification method which entails performing a theoretical or empirical evaluation by accepted analytical techniques. The selected techniques may typically include systematics, statistics, qualitative design analysis, modelling and computer simulation (see also ECSS-P-001A Rev.1 3.5). Assembly The process of mechanical mating hardware to obtain a low level configuration after the manufacturing process (see also ECSS-P-001A Rev.1 3.9). In-orbit stage The verification stage valid for projects whose characteristics (e.g. mission, in-orbit operations) require inorbit verification. Inspection A verification method that determines conformance to requirements for constructional features, document and drawing conformance, workmanship and physical conditions without the use of special laboratory equipment, procedures or services (see also ECSS-P-001A Rev.1 3.73). Integration The process of physically and functionally combining lower level products (hardware and/or software) to obtain a particular functional configuration. Model philosophy The definition of the optimum number and characteristics of physical models required to achieve a high confidence in the product verification with the shortest planning and a suitable weighing of costs and risks. Post-landing stage The verification stage valid for projects whose characteristics require post-landing verification (e.g. multimission projects). Pre-launch stage The verification stage with the objective to verify that the flight article is properly configured for launch and, to the extent practical, it is capable to function as planned for launch. Qualification stage The verification stage with the objective to demonstrate that the design meets the applicable requirements including proper margins. Review-of-design A verification method using validation of previous records or evidence of validated design documents, when approved design reports, technical descriptions and engineering drawings unambiguously show that the requirement is met. Test A verification method wherein requirements are verified by measurement of product performance and functions under various simulated environments (see also ECSS-P-001A Rev.1 3.147). Verification Level The product architectural level at which the relevant verification is performed. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 70 of 76 10.2 ECSS-E-10-03A Airborne Support Equipment (ASE) Equipment installed in a recoverable launch vehicle to provide support functions and interfaces for the spacecraft during launch and orbital operations of the recoverable launch vehicle • NOTE ASE includes the hardware and software that provides the structural, electrical, electronic and mechanical interfaces with the launch vehicle. ASE is recovered with the launch vehicle. Burst Pressure Maximum test pressure that pressurized equipment withstands without rupture to demonstrate the adequacy of the design in a qualification test • • NOTE 1 Burst pressure is equal to the product of the maximum expected operating pressure, a burst pressure design factor, and a factor corresponding to the differences in material properties between test and design temperatures. NOTE 2 An item subjected to a burst pressure test is not used for other purposes. Design Environments Composite of the various environmental loads, to which the hardware is designed • NOTE Each of the design environments is based upon: • • • the maximum and minimum predicted environments during the operational life of the item; the qualification margin that increases the environmental range to provide an acceptable level of confidence that a failure does not occur during the service life of the item; uncertainties and tolerances related to the analytical prediction. Environmental Design Margin Increase of the environmental extremes for the purpose of design and qualification above the levels expected during the life cycle • NOTE Environmental design margin includes levels such as mechanical, thermal, radiation as well as the time of exposure of them. Environmental Test Simulation of the various constraints (together or separately) to which an item is subjected during its operational life cycle • NOTE Environmental tests cover natural and induced environments. Fundamental Resonance (for Structural Modes) first major significant resonances as observed during one-axis vibration test for each of the three test axes fundamental resonance (for structural modes) first major significant resonances as observed during one-axis vibration test for each of the three test axes • • NOTE 1 The term fundamental resonance is used in conjunction with notching of sinusoidal vibration input spectrum for item qualification. NOTE 2 Significant resonances are modes that have an effective mass greater than 10 % of the total mass of the item. Integrated System Test Test that has the scope to verify that the performance of the element meets the specification requirements, in terms of correct operation in all operational modes, including back-up modes and all foreseen transients. • NOTE Integrated system test is also known as system functional test. Integrated System Check Sub-set of the integrated system test, able to involve all major functions, at the maximum extent automatically performed and with the scope to provide the criteria for judging successful survival of the element in a given test environment, with a high degree of confidence, in a relatively short time. • NOTE Integrated system check is also known as abbreviated functional test. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 71 of 76 Limit Load Maximum anticipated load, or combination of loads, which a structure is expected to experience during the performance of specified missions in specified environments. • NOTE Since the actual loads that are experienced in service are in part random in nature, statistical methods for predicting limit loads are generally employed. Low Level Sinusoidal Vibration Exposing an item to a frequency sweep of low level sinusoidal vibrations to show possible deficiencies in workmanship, as a consequence of another environment. • NOTE Low level sinusoidal vibration test is also known as signature test. Maximum Predicted Acceleration Acceleration value determined from the combined effects of the quasi steady acceleration and the transient response of the vehicle to engine ignition, engine burn-out and stage separation. • NOTE Where the natural frequency of the equipment mount or mounting structure can couple with engine initiated transients, the maximum predicted acceleration level accounts for the possible dynamic amplification. Maximum Predicted Acoustic Environment Maximum value of the time average r.m.s. SPL (sound pressure level) in each frequency band occurring below payload fairing or within STS orbiter cargo bay, which occurs during lift-off, powered flight or re-entry. • NOTE The maximum predicted acoustic environment test spectrum is specified in octave or 1/3 octave bands over a frequency range of 31,5 Hz to 10 000 Hz. The duration of the maximum environment is the total period when the overall amplitude is within 6 dB of the maximum overall amplitude. Maximum Predicted Operating Pressure Working pressure applied to equipment by the pressurizing system with the pressure regulators and relief valves at their upper operating limit, including the effects of temperature, transient peaks and vehicle acceleration. Maximum Predicted Pyro Shock Environment Maximum absolute shock response spectrum determined by the response of a number of single degree of freedom systems using an acceleration amplification factor at the resonant frequency of lightly damped system (Q = 10). • • NOTE 1 The shock response spectrum is determined at frequency intervals of one-sixth octave or less over a frequency range of 100 Hz to 4 000 Hz or more. NOTE 2 The pyro shock environment imposed on the spacecraft equipment is due to structural response when the space or launch vehicle electro-explosive devices are activated. Resultant structural response accelerations have the form of superimposed complex decaying sinusoids that decay to a few percent of their maximum acceleration in 5ms to 15ms. Maximum Predicted Random Vibration Environment Random vibration environment imposed on the spacecraft, subsystems and equipment due to the lift-off acoustic field, aerodynamic excitations, and transmitted structure-borne vibration. • • NOTE 1 A different spectrum can exist for different equipment zones or for different axis. The equipment vibration levels are based on vibration response measurements made at the equipment attachment points during ground acoustic tests or during flight. The duration of the maximum environment is the total period during flight when the overall level is within 6 dB of the maximum overall level. NOTE 2 The Power spectral density is based on a frequency resolution of 1/6 octave (or narrower) bandwidth analysis, over a frequency range of 20 Hz to 2 000 Hz EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 72 of 76 Maximum Predicted Sinusoidal Vibration Environment Predicted environment imposed on the spacecraft, subsystems and equipment due to sinusoidal and narrow band random forcing functions within the launch vehicle or spacecraft during flight or from ground transportation and handling. • • NOTE 1 In flight, sinusoidal excitations are caused by unstable combustion, by coupling of structural resonant frequencies (POGO), or by imbalances in rotating equipment in the launch vehicle or spacecraft. Sinusoidal excitations occur also during ground transportation and handling due to resonant responses of tires and suspension systems of the transporter. NOTE 2 The maximum predicted sinusoidal vibration environment is specified over a frequency range of 5 Hz to 100 Hz for flight excitation. Maximum And Minimum Predicted Equipment Temperatures Highest and lowest temperatures that are expected to occur in flight on each equipment of the spacecraft during all operational and non-operational modes which include uncertainties. Moving Mechanical Assemblies Mechanical or electromechanical devices that control the movement of one mechanical part of a spacecraft relative to another part. • NOTE Moving mechanical assemblies include: deployment mechanisms, pointing mechanisms, drive mechanisms, design mechanisms and the actuators, motors, linkages, latches, clutches, springs, cams, dampers, booms, gimbals, gears, bearings and instrumentation that are an integral part of these mechanical assemblies (e.g. recorders). Multipacting Resonant back and forth flow of secondary electrons in a vacuum between two surfaces separated by a distance such that the electron transit time is an odd integral multiple of one half the period of the alternating voltage impressed on the surface. • • • • NOTE 1 Multipacting does not occur unless an electron impacts one surface to initiate the action, and a secondary emission of one or more electrons at each surface to sustain the action takes place. NOTE 2 Multipacting is an unstable self-extinguishing action which occurs at pressures less than 6,65 × 10-2 hPa, however, it becomes stable at a pressure less than 1,33 × 10-3 hPa. NOTE 3 The pitting action resulting from the secondary emission of electrons degrades the impacted surfaces. The secondary electron emission can also increase the pressure in the vicinity of the surfaces causing ionisation (corona) breakdown to occur. NOTE 4 These effects can cause degradation of performance or permanent failure of the radio frequency cavities, waveguides or other devices involved. Notching of Sinusoidal Vibration Input Spectrum Notching of the shaker input spectrum to limit structural responses at resonant frequencies according to qualification or acceptance loads. • NOTE Notching of sinusoidal vibration input spectrum is a general accepted practise in vibration testing. Operational Modes Combination of operational configurations or conditions that can occur during the service life for equipment or spacecraft. • EXAMPLE Power-on or power-off, command modes, readout modes, attitude control modes, antenna stowed or deployed, and spinning or de-spun. Proof Pressure Test pressure for pressurized equipment to sustain without detrimental deformation. • • NOTE 1 The proof pressure is used to give evidence of satisfactory workmanship and material quality, or to establish maximum possible flaw size. NOTE 2 The proof pressure is equal to the product of maximum expected operating pressure (see 3.1.15), proof pressure design factor, and a factor accounting for the difference in material properties between test and design temperature. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 73 of 76 Service Life Total life expectancy of an item, equipment or space vehicle. • NOTE The service life starts at the completion of assembly of the item and continues through all acceptance testing, handling, storage, transportation, launch operations, orbital operations, refurbishment, retesting, reentry or recovery from orbit, and reuse if applicable. Space Element Product or set of products intended to be operated in outer space. • • NOTE 1 In order to avoid repetition in the level of decomposition of the space product, the term element is used to define .systems within the system.. The term element is used to identify any system within the space system. NOTE 2 Elements that operate entirely in space or on the ground are referred to as Space segment and Ground Segment, respectively. Space Vehicle integrated set of subsystems and equipment capable of supporting an operational role in space. • NOTE A space vehicle can be an orbiting vehicle, a major portion of an orbiting vehicle, or a payload that performs its mission while attached to a launch or upper-stage vehicle. The ground support equipment is considered to be a part of the space vehicle. Stabilized Test Temperature Specified temperature for equipment and subsystem tests that has been achieved and has not changed by more than 1ºC during the previous one-hour period. • NOTE During system level tests, performance verification testing may be started when the rate of change is below 1ºC within a time period equal or near the time constant of the spacecraft. Temperature Reference, Reference Point Physical point located on the equipment providing a simplified representation of the equipment thermal status. • • NOTE 1 Depending upon the equipment dimensions, more than one temperature reference may be defined. NOTE 2 The temperature of the reference point is measured by temperature sensors during test. The temperature distribution within the equipment and hot spots on the external casing due to point heat sources are not used as reference points. Ultimate Load Maximum static load to which a structure is designed. • NOTE It is obtained by multiplying the limit load by the ultimate factor of safety. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 74 of 76 10.3 ECSS-E-20A Centroid Error Function (CEF) Difference between the position of the barycentre of the Point Spread Function (PSF), calculated by means of a suitable algorithm, and the theoretical position of the PSF centre, given by the intersection of the corresponding chief ray with the image plane. The centroid algorithm evaluates the position of the PSF energy barycentre and it is based on the energy measurement on a predetermined number of pixels in the image plane. Encircled Energy Function (EEF) The fraction of the PSF energy which lies within a circle, evaluated as a function of the circle radius. Field Of View (FOV) Angular extent of the object space which can be detected by an optical system or instrument. (The FOV is not be always symmetrical about the optical axis). Instantaneous Field Of View (IFOV) Angular extent of the object space which can be detected by an optical system or instrument, during a negligible time interval. (The IFOV is not be always symmetrical about the optical axis). Line Spread Function (LSF) One-dimensional transverse energy distribution in the image of a narrow slit object. Modulation Transfer Function (MTF) The modulation transfer function is the modulus of the optical transfer function. Considering a sine wave pattern object, the MTF is found to be the ratio of the modulation in the image to that in the object as a function of the spatial frequency of the sine wave pattern. Noise Equivalent Power (NEP) The Noise Equivalent Power is the value of the detector input power which produces a detector output equal to the r.m.s. noise output within a stated bandwidth at a stated frequency. Optical Transfer Function (OTF) It is the normalized Fourier transform of the point spread function Point Spread Function (PSF) Two dimensional energy distribution in the image of an object point. Wavefront error (WFE) Distribution of the distance between the wavefront exiting from an optical system and a reference wavefront or surface, measured on the normal to the reference wavefront and expressed in wavelength units. EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE Sentinel-1 S1-LI-ASU-PL-0011 Issue 1 Page 75 of 76 11. COMMERCIAL The definitions below are from the point of view of the SES level :The Agency – Mission Prime The European Space Agency (ESA) Industrial End Customer – Spacecraft Prime Thales Alenia Space Italia S.p.A (TAS-I) Industrial Customer – Payload Prime Astrium GmbH, Friedrichshafen (ASD) Customer – SES Prime Astrium Ltd, Portsmouth (ASU) Contractor A company providing goods or services into the SES programme EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE COMMERCIAL IN CONFIDENCE S1-LI-ASU-PL-0011 Issue 1 Page 76 of 76 Sentinel-1 DOCUMENT CHANGE DETAILS Issue Issue Date Change Authority Class Relevant Information/Instructions 1 First Issue 2 Up Issue DISTRIBUTION LIST EXTERNAL INTERNAL Configuration Management (FileNet) EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. COMMERCIAL IN CONFIDENCE
