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TASI -Torino October 09, 2013
ExoMars Mission 2018
3rd Industry Day
Torino October 9th, 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
3rd ExoMars Industry Day for 2018 Mission
Mission and System
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 TASI -Torino October 09, 2013
2018 Mission within ESA-ROS international cooperation
Roscosmos RNS
ESA ESTRACK
DSN
Trace Gas Orbiter (TGO)
2018 Mission
Spacecraft Composite (Carrier Module +
Descent Module + Rover Module)
ROCC (incl SOC- Altec)
Proton M /
Breeze M MOCC @ ESOC, Darmstadt
Spacecraft Operations
Rover and Landing
Platform
Archiving (ESAC)
Archiving (ROS)
International cooperation
NASA DSN N/A
Available for
“extreme contingencies”
during Cruise
Lander Op. Center (ROS)
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 TASI -Torino October 09, 2013
EXOMARS 2018 Reference Missions
Nominal Mission 2018 Short Transfer
Launch date: 07 May 2018
Mars Arrival: 15 January 2019
Transfer duration: 233 – 253 days
Arrival LS: 324° With arrival velocity range [3.377 – 3.465 km/s]
PROGRADE entry: Relative velocity range [5.74 – 5.78 km/s]
Reference Back-Up Mission 2020 Short Transfer with late arrival
Launch date: 05 August 2020
Mars Arrival: 19 April 2021
Transfer duration: 237 – 257 days
Arrival LS: 34° With arrival velocity range [2.684 – 3.510 km/s]
PROGRADE entry: Relative velocity is [5.37 – 5.83 km/s]
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 TASI -Torino October 09, 2013
EXOMARS 2018 Reference Mission Main Requirements
Communication Requirements
Spacecraft Composite housekeeping data return of 200 Mb/day (To be
Confirmed) during all mission phases Spacecraft Composite
During all mission phases, the Spacecraft Composite shall support
reception of commands from Ground Control at a minimum data rate of
2000 bps.
Mission to be designed to allow visibility from Earth of the EDL event
Essential telemetry transmitted at 8 kbps by the DM during the Coast
and EDL phases to allow real time transmission to, and reception by,
the 2016 TGO.
The relay link shall be compatible with a Mars surface-to-Orbiter data
relay provided by the TGO (nominal mission) and any other available
Mars Orbiters (NASA Relay Orbiter(s) as contingency case
Average data relay return of 0.4 Gb/day for the two surface assets
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 TASI -Torino October 09, 2013
EXOMARS 2018 Reference Mission Main Requirements
Mass Requirements 2800 Kg at Launcher separation,
including all maturity and system margins (w/o Launcher Adapter)
Note: DMC Mass bounded to 2000 Kg NTE (including a 350 Kg
class Rover Module
Power Requirements ˜1200 W (400 W to DMC during Cruise)
implies foldable Solar Panels on CM
Single Failure Tolerance (not applicable to RDA and to RCT
Configuration for Torque/Force Free Control)
GNC Spinning Spacecraft during Cruise and DM ballistic EDL
Operational LifeTime SCC/CM: 1 year
DM-SP: 2 years
RM: 0.6 year
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 TASI -Torino October 09, 2013
System Design Status: SCC Avionics
Descent Module Composite (DMC)
CARRIER MODULE (CM) BACK SHELL (BSH)
LANDER PLATFORM (LP)
FRON SHIELD (FS)
ROVER MODULE
HG
A
LG
A1
LG
A3
X-
DS
T
X-
DS
T
RF
DN
TW
TA
TW
TA
STR-1
CSS-1
CSS-2
STR-2
8 x
30
N
ctrl T
HR
RC
S
se
nso
rs
Pro
pu
lsio
n
SA
LRTU
Legs
LPCDU
IMU-1
IMU-2
CRTU
BATT
TCS
heaters
TCS
RV
HDRM
UHF-1
UHF-2
SWITCH
KEY
BATT
AC 1Legs
release
SEP MECH
SE
P M
EC
H
SE
P
ME
CH
RM-OBC
PCDE
PWR Sys.
Data Handl. Sys.
Thermal Contr. Sys.
Telecom. Sys.
GNC. Sensors
Actuators
Propulsion Sys
Separ. Interfaces
Discrete lines
MIL-1553 bus
RS-422/485
PWR/Pyro lines
CAN bus
PDD
CPCDU
SA
RD
A
RM
E-2
BR
SA
RD
A A
nte
nn
as
ESA-OBC
Pyro
va
lve
s
AC 1Legs
sensors
Ramps
AC 1Ramps
releaseAC 1Ramps
sensorsAC 1Ramps
actuators
TH
Rs
RC
S
se
nso
rs
RC
S
Pyro
va
lve
s
Sensors
AC 1Thermistors
TCS
heatersAC 1Thermistors
AC 1Entry Sensors
AC 1Entry Sensors
SEP CONNECTOR
SE
P
CO
NN
EC
TO
R
ROS-OBC
PA
YL
OA
Ds
ADE
SE
P
CO
NN
EC
TO
R
SE
P C
ON
NE
CT
OR
LG
A2
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 TASI -Torino October 09, 2013
System Design Status: SCC Configuration
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 TASI -Torino October 09, 2013
System Design Status: CM Configuration
Thruster 2x4
Battery
Tank
Deployable Solar panel
Tank
EPC
LGA
CRTU
Transceiver
TWT
Radiator
PCDU
Star Tracker
Thruster 2x4
Solar Generator
Star Tracker
Central Tube1640.7mm I/F to
separation mechanism of
DM
MGA
1666mmLauncher I/F
Battery
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 TASI -Torino October 09, 2013
System Design Status: DMC Configuration
Preliminary CAD model of the Descent Module delivered 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 TASI -Torino October 09, 2013
System Design Status: DMC Configuration
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 TASI -Torino October 09, 2013
System Design Status: DMC Configuration
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 TASI -Torino October 09, 2013
Rover Module Configuration
Deployable solar panels
SVM Radiator
Actuator Drive Electronic
PanCam
Pan and Tilt Mechanism
Deployable Mast Assembly
Drill Box
Clupi
DBE/MaMiss Elec
Core Sample transportation
mechanism port
ALD Radiators
UHF Antenna
Bogey Electromechanical assembly
ISEM Optical Head
Loc cameras
Navigation cameras
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
TASI CM Upcoming procured items
TASI -Torino October 09, 2013
EXOMARS Mission 2018
Spacecraft Composite
EXOMARS Mission 2018
Carrier Module
EXOMARS Mission 2018
Descent Module
EXOMARS Mission 2018
Rover Module
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
Star Tracker
TASI -Torino October 09, 2013
Item: Autonomous Star Tracker Procuring Company: TAS-I
ITT issue: Q2-2014 K/O: Q4-2014 Date of Need (PFM): Q1-2016
Short description:
Autonomous Star Tracker unit to provide attitude quaternion for spin stabilized
spacecraft. The unit shall include dedicated baffle to be protected from any stray-light
solar, lunar, Earth, Mars, planetary or other sources in the FoV
Main requirements:
Accuracy: 0.05 deg 3-sigma;
Compatible with spin rate range between 2.5 to 3 ÷ 5 rpm, with bore-sight radially
mounted wrt spin axis
Average power consumption 13W, data I/F preferred MIL-STD-1553 bus
Star Catalog set-up to cover all interplanetary mission
Models: STM, E(Q)M, 2xFM, FM Spare (tbc)
Main Reviews: PDR, CDR, QR, DRB.
Notes: In case of an OTS unit the reviews shall be limited according to unit qualification
status
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
Cruise GNC algorithms
TASI -Torino October 09, 2013
Item: Cruise GNC algorithm design &
verification support
Procuring Company: TAS-I
ITT issue: Q2-2014 K/O: Q4-2014 Date of Need: Q2-2016
Short description:
Task I: analytical verification of Guidance Navigation and Control algorithms for Cruise
phase in support to detailed design phase
Task II: evaluation of results and algorithm optimization during GNC verification activities
on ATB
Main requirements:
GNC for attitude orientation control of Spin spacecraft (2.5rpm) with pointing accuracy
1deg half-cone during cruise, 0.2deg half cone at pre-separation
GNC for trajectory control with autonomous delta-V determination 1% and
implementation
GNC architecture: IMU, STR, Sun Sensor. Delta-DOR (TBC)
Models: Technical notes, Verification report, contribution to system documentation
Main Reviews: input to system CDR
Notes: