EDL/GNC Slides - Emits

ExoMars Mission 2018
Torino October 9th, 2013
TASI -Torino October 09, 2013
83230913-DOC-TAS-EN-002
3rd Industry Day
3rd ExoMars Industry Day for 2018 Mission
DESCENT MODULE (DM)
TASI -Torino October 09, 2013
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
Descent Module
Introduction
DM is designed and built by Lavochkin Association (LAV), under ROSCOSMOS contract
Tasks and responsibilities of developing HW and SW have been agreed as part of the
cooperation among all parties, ESA-ROS-TASI and LAV.
TAS-I provide support and items according to the 2016 mission experience and heritage.
The items (subsystems, units, equipment, products..) part of the provisions under
ESA/TASI are limited to the following areas:
GNC, including sensors, algorithms (part shared with LAV), SW and the Radar
Altimeter that will be a fully recurrent product of the 2016 mission
Data Handling
UHF communication system (most of it recurrent of 2016 mission)
Parachute System
EGSE (part provided as well by LAV)
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
Descent Module configuration
Descent Module
Carrier
Rover
(stowed)
Landing Platform
(Stowed)
Landing Platform (Deployed)
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
Mass Constraints
CM Mass:
DM Mass:
NOT CRITICAL
< 2000 kg (EDL constraints)
Launch: Direct Injection
EXTREMELY CRITICAL
LV Performance: ~ 5 Tons
SCC mass NOT CRITICAL
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
EDL/GNC sequence
Parachute System (PAS)
under ESA
DM MODE
GNC MODE
Transition Event
SW
IMU
RDA
RCS
InitBiasCalib
PRE-SEPARATION
GNC-PRE-SEPARATION
Separation
COASTING
COASTING
EntryInterfacePoint
EDL
Entry
ENTRY
SuperSonicParaOpening
DESCENT1
SubSonicParaOpening
EDL
Descent
DESCENT2
FrontShieldRelease
DESCENT3
RadarInTheLoop
DESCENT4
B&PSeparation
LANDING1
EDL
Landing
ClosedLoop
LANDING2
RadarOutsideTheLoop
LANDING3
ReadyForTouchDown
LANDING4
TouchDown
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
Product Tree- DM ESA/TAS-I Products
7
DM ESA/TAS-I Products
GNC
TT&C (UHF Band)
Data Handling (DH)
Parachute Syst. (PAS)
EGSE
Shared with LAV
Radar Altimeter (RDA)
UHF Transceiver
Recurring of EXM-2016
Recurring of EXM-2016
Inertial Meas. Unit (IMU)
ITT already issued
AeroThermal DB
Shared with LAV
SP Antenna
On Board Comp. (OBC-1)
Software S/W
Rear Jacket Antenna
Application S/W
S/W Integ/Valid Facil.
CCO Equipment
DH SCOE
GNC SCOE
ROS/LAV product
RFDN
UHF SCOE
Purchase order
Power SCOE
ROS/LAV Product
07/10/2013
Ref.:S-PM#3 – ESTEC
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
Descent Module Intended ITT
DM
SubSubsystem
Item
module
AS
Data Handling System On Board Computer (incl Fumo)
DM
LPF
GNC
IMU
TAS-I
ITT
DM
LPF
Communications / RF
Landing platfrom UHF Antenna
TAS-I
ITT
DM
LPF
Software
DM ASW DD&Coding (including carrier ASW)
TAS-I
ITT
DM
AS/LPF EGSE
DH SCOE
TAS-I
ITT
DM
AS/LPF EGSE
GNC SCOE
TAS-I
ITT
DM
AS/LPF EGSE
UHF SCOE
TAS-I
ITT
DM
AS/LPF EGSE
CCS (for CM & DM)
TAS-I
ITT
DM
AS/LPF software
Software integration/validation facility
TAS-I
ITT
DM
PAS
Parachute System
TAS-I
ITT
Module
Parachute
Procuring Prc.
Notes
company Mean
TAS-I
ITT
ITT running
includes CM GNC needs
(TBC) Pending resuse of 2016 mission
SVF
includes parachutes, PDD and HADT
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
DM ITT items
Item: On Board Computer – 1 (OBC-1)
Procuring Company: TAS-I
ITT issue: Q2 2014
Need date: Q3 2015
K/O:Q3 2014
Short description:
The OBC is the main On board computer of the EXOMARS 2018 mission. It will be in charge of the execution of the OnBoard software during all the mission phases: Cruise, EDL and Mars Surface Operations.
It is based on a Cold redundant processor module, cold redundant I/O module, Reconfiguration module, cold redundant
TMTC module.
Interfaces: mil 1553B; CAN bus, UART, SD16 RS422, In HPC, out HPC, analog acquisition and telemetries.
Main requirements:
Necessity of meeting the nominal Launch opportunity of 2018; challenging in terms of Item development schedule.
Models: STM, EM/EQM, PFM/FM, 2 FuMo
Main Reviews: PDR, CDR, TRR, TRB, DRB, QR/AR
Notes:
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
DM ITT items
Item: Landing Platform UHF Antenna
Procuring Company: TAS-I
ITT issue:Q2 2014
Need date: Q3 2015
K/O:Q3 2014
Short description:
•
•
•
Low Gain Antenna
UHF band
Hemispherical coverage
Main requirements:
Necessity of meeting the nominal Launch opportunity of 2018.
Models: STM, EM/EQM, PFM/FM
Main Reviews: PDR, CDR, TRR, TRB, DRB, QR/AR
Notes:
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
DM ITT items
Item: DM ASW DD & Coding (including
CM ASW)
Procuring Company: TAS-I
ITT issue:
March-2014
Need date: Q3 2015 (+12 months support)
K/O: Sep/Oct 2014
Short description:
CM ASW: It is in charge to support Attitude and Guidance navigation and control functions, thermal control, power management,
TTC management. (It is under TAS-I / OHB responsibility to define the RB requirements, under which the OBSW will be
designed and implemented.)
DM ASW: It is in charge to support Guidance navigation and control functions, thermal control, power management, TTC
management. (It is under TAS-I / LAV responsibility to define the RB requirements, under which the OBSW will be designed
and implemented.)
Both ASWs will run on the DM computer and will rely on the Hardware Dependent Software (HDSW) including Bootstrap and
the I/O driver services (provided by DM CTU supplier) and system management layers including necessary services for TC/TM
packets management.
Main requirements:
Co-operate with TAS-I since the Preliminary Design Definition phase.
Perform coding (C language) and unit testing.
Participate at the integration & testing activities on the test benches (SVF,STB) at TAS-I premises.
Models: N/A
Main Reviews: DM / CM SW DDR, SW TRR
Notes: participation to overall DM OBSW SW PDR and SW CDR as necessary
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
DM ITT items
Item: EGSE – DH SCOE
Procuring Company: TAS-I
ITT issue:Q1 2014
Need date: Q4 2015
K/O: Q3 2014
Short description:
This SCOE(s) implements Data Handling Subsystem (On Board Computer in Particular, but not limited to) interfaces, missing
unit simulation and emulation either from the electrical and/or from the functional point of view.
It guarantees the EXOMARS buses monitoring (1553bus, Can Bus, Serial lines, Spacewire, etc).
It implements the possibility of failure injection on the applicable busses and protocols for testing purposes.
The architecture includes Telemetry and Telecommand management and archiving through the by-pass link.
The architecture includes the Quick SW loading functionality on On board Memories.
The SCOE will implement Serial and Discrete I/O, Missing units functional models, Thermal simulation/acquisition,
Communication S/S model, Busses monitoring and archiving, Time distribution and Synchronization with other EGSE
equipments, Failure injection on the busses, Telemetry and Telecommand blocks management through by-pass link and trough
busses using also high level System Telemetry and Telecommands.
Main requirements :
To meet the launch opportunity in 2018, the equipment shall be able to cope with a challenging development schedule
The SCOE shall include Remote Interface with one or more CCS through defined protocols.
Models: 2 (TBC)
Main Reviews: PDR, CDR, AR
Notes:
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
DM ITT items
Item: EGSE – GNC SCOE
Procuring Company: TAS-I
ITT issue: Q1 2014
Need date: Q4 2015
K/O: Q3 2014
Short description:
The GNC SCOE shall be in charge to test, verify and validate the entire GNC subsystem in real time, either in a fully automated
mode (by means of test's procedures) or in manual one. It shall be used for both Open and Closed Loop tests. The GNC
sensors and actuators can be either simulated or stimulated by the GNC SCOE.
The SCOE will include Real Time Simulation SW, (including S/C dynamics and kinematics ), Front End Equipment and/or
boards for Simulation/Stimulation and Acquisition of on board signals/data, Interface(s) with the busses, Interface with the
Power SCOE (separation straps), Time Synchronization with other EGSE equipments.
The SCOE shall include also Remote Interface with one or more CCS through defined protocols.
Main requirements:
To meet the launch opportunity in 2018, the equipment shall be able to cope with a challenging development schedule
Models: 2 (TBC)
Main Reviews: PDR, CDR, AR
Notes:
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
DM ITT items
Item: EGSE – UHF SCOE
Procuring Company: TAS-I
ITT issue: Q1 2014
Need date: Q4 2015
K/O: Q3 2014
Short description:
The UHF SCOE is in charge to test and verify the UHF Transceiver in real time by using a fully automated environment.
The SCOE will also provide the capability to acquire, monitor and record the Proximity-1 traffic on the RF link.
The SCOE will include:
• Interface to CCS for remote control
• Interface with the antenna anechoic cap
• Interfaces with the S/C (RF transponder)
• Instrumentation for RF link characterisation
• Proximity-1 protocol handling
• Connection with the TM/TC FEE contained in the DH SCOE
• Synchronization with other EGSE equipment.
Main requirements:
To meet the launch opportunity in 2018, the equipment shall be able to cope with a challenging development schedule
Models: 2 (TBC)
Main Reviews: PDR, CDR, AR
Notes: The ITT has to be confirmed, pending utilization of a Rover recurrent item
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
DM ITT items
Item: EGSE – Central Check-out System
(CCS), for CM and DM
Procuring Company: TAS-I
ITT issue: Q1 2014
Need date: Q4 2015
K/O: Q3 2014
Short description:
Set of computers running the software packages to prepare and control the test execution. It allows the test preparation and
configuration, the execution of automatic test sequences, the data monitoring, archiving and the test report preparation.
The CCS is also in charge of the processing of data exchanged with the Spacecraft over the Telemetry and Telecommand links
and of the control and co-ordination of the Special Check-Out, Front-End (SCOEs, FEEs) and the Instrument Stations belonging
to the overall EGSE.
The CCS will be designed so that Off-line activities (e.g. Test SW preparation) can be performed simultaneously to On-line realtime tasks without performance degradation or in general without disturbing the ongoing S/C testing.
Main requirements:
To meet the launch opportunity in 2018, the equipment shall be able to cope with a challenging development schedule
Models: 1 (TBC)
Main Reviews: PDR, CDR, AR
Notes:
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
DM ITT items
Item: Software Integration/Validation
Facility
Procuring Company:TAS-I
ITT issue: Jan-2014
Need date: 18 months (+12 months support)
K/O: June-2014
Short description:
The Software Verification Facility is a pure SW test facility. The SVF allows the execution of the OBSW on the
CTU processor emulator interfaced with the simulation of the I/O devices used on the HW target platform.
External units connected on busses and serial lines are also simulated.
The test session can be prepared, logged and controlled though a proper MMI and dedicated SW tools.
Main requirements:
Shall be based on commercial items.
HW setup including needed performances and operative system has to be agreed with TAS-I.
Models: N/A
Main Reviews: All standard SW reviews as per ECSS E-40 standard
Notes: This item is TBC, pending reuse of the SVF developed for the EXM 2016 mission which is available
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
DM ITT items
Item: Parachute System (PAS)
Procuring Company:TAS-I
ITT issue: Q2 2014
Need date: Q3 2016
K/O: Q4 2014
Short description:
The parachute system shall be able to decelerate a 2000 kg descent module to a terminal velocity not higher than 60
m/s. It shall be safely deployed in a mach range of 1.8 2.1. The parachute system can be composed ba a single stage
rather than a double stage with a supersonic stage and a main stage to be used in subsonic range to break the probe to
the needed velocity and altitude (~1.5 km AGL) when the powered descent phase is initialized. A drogue/stabilizer
parachute will be deployed in supersonic flow
The maximum dynamic pressure at deployment will be < 1 kPa
The Parachute bridles will be attached to the canister to minimize interface with DM
Parachute deployment will be activated by a mortar system.
Main requirements:
The necessity of meeting the nominal Launch opportunity of 2018 gets the PAS development very challenging in terms
of development schedule.
The Company responding to the PAS ITT, shall propose a consortium of subcontractors/ suppliers
developing/manufacturing the products needed as well as the flight test (HADT)
Models: QM, FM (other models TBD depending on proposed development)
Main Reviews: PDR, CDR, QR
Notes:
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
3rd ExoMars Industry Day for 2018 Mission
EDL/GNC
TASI -Torino October 09, 2013
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
Introduction
This short presentation is
aimed to provide you with a
quick insight of the EXM
2018 EDL main aspects
EDL
means
Entry
Descent
Landing
EDL the three steps from Space to Mars Landing
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
OVERALL EDL STRATEGY – Cruise and Coasting
Spinning
SCC
Spinning
DM
 CRUISE 
Entry Interface
Point
CM/DM
 COASTING 
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to any third party without the prior written permission of Thales Alenia Space - 2012, Thales
Alenia Space
(125
Km AGL)
Separation
(~30 min)
 ENTRY 
OVERALL EDL STRATEGY – Entry
Entry trajectory simulated by the
EXM2018 E2E Mission Simulator
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to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space
OVERALL EDL STRATEGY – Descent
The Lander is
separated by the
Backshell
Parachute
Deployment
device is
initiated to
release the
Supersonic
Parachute
Deployment of
the Subsonic
Parachute
Jettison of the
Front Shield
~1 sec
Radar Doppler
is Switched On
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OVERALL EDL STRATEGY – Landing
3
1
42
53
64
Final Approach
to Landing Site
Avoidance
ClosedLoop
Trigger
In flight
Overtaking
Play
This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed
to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space