83

23

09

13

-DO

C-T

AS

-EN

-00

2

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: