DOC-TAS-EN-002 ALTEC Auditorium - Torino - Italy December 9-10, 2014 Bruno MUSETTI ESWT#7 – ESWT#7

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 ALTEC Auditorium - Torino - Italy December 9-10, 2014 EXOMARS 2018 Mission: Introduction The ExoMars Program is pursued as part of a joint cooperation between ESA and Roscosmos, with an important contribution from NASA, to explore Mars and prepare for the Mars Sample Return and for future planetary exploration mission. In particular, it features two missions, one to be launched in January 2016 and one in May The 2018 mission is devoted to develop a Spacecraft Composite (SCC), consisting of a Carrier Module (CM) and a 2 ton Descent Module (DM), capable to land on Mars and allow for the deployment and egress of the European Rover Module (RM) and the operations of an instrumented Russian Surface Platform (SP). The 2018 mission will be launched with a Proton M/Breeze-M rocket and is expected to arrive on Mars on January 2019.

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 EXOMARS 2018: System Elements Tree ALTEC Auditorium - Torino - Italy December 9-10, 2014

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 ALTEC Auditorium - Torino - Italy December 9-10, 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 ESOC, Darmstadt Spacecraft Operations Rover and Landing Platform Archiving (ESAC) Archiving (ROS) EXOMARS 2018 International Cooperation NASA DSN 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 Mission Objectives (1/2) The ExoMars Programme will demonstrate key flight and in situ enabling technologies in support of the European ambitions for future exploration missions, as outlined in the Aurora Declaration pursuing fundamental scientific investigations. In particular: To search for signs of past and present life on Mars To investigate the water/geochemical environment as a function of depth in the shallow subsurface To investigate Martian atmospheric trace gases and their sources To characterize the surface environment ALTEC Auditorium - Torino - Italy December 9-10, 2014

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 Mission Objectives (2/2) In support of the objectives of the Aurora Program, the development, in flight and in situ demonstration of the following technologies shall be achieved: Entry, Descent and Landing (EDL) of a payload on the surface of Mars Surface mobility with a Rover Access to the sub-surface to acquire samples Sample preparation and distribution for analyses by scientific instruments Qualification of Russian ground-based means for deep-space communication in cooperation with ESA’s ESTRACK Adaptation of Russian on-board computer for deep space missions and ExoMars landed operations Development and qualification of throttleable braking engines for prospective planetary landing missions Another important objective of the ExoMars Programme is to provide data relay services for landed assets on the surface of Mars until the end of 2022 Note: this objective will be achieved as part of the ExoMars 2016 Mission. ALTEC Auditorium - Torino - Italy December 9-10, 2014

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 ALTEC Auditorium - Torino - Italy December 9-10, 2014 EXOMARS 2018 Reference Mission Main Requirements Spacecraft Composite housekeeping data return of 20 Mb/day during Cruise Spacecraft Composite Telecommand data rates ranging from 8 bps to 4 kbps, according to the ECSS standard 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 the 2016 TGO (or other compatible and available Data Relays Average Data return of Gb/sol for each asset on Mars (RM and SP) Mass  2900 Kg at Launcher separation, including all maturity and system margins (w/o Launcher Adapter) Note: DMC Mass shall be bounded to 2000 Kg NTE (including 345 Kg Rover Module) Power  350 W to DM during Cruise (up to 1600 W supplied to the whole System by the Carrier Module  15 m 2 Solar Arrays during CRUISE to Mars) Single Failure Tolerance (where applicable)

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 EXOMARS 2018 Reference Mission Main Elements The ExoMars 2018 Mission System consists of: The Space Segment, as a single Spacecraft Composite (SCC), which is composed by: The Carrier Module (CM) which carries the whole system close to Mars atmospheric borders. The Descent Module (DM) which separates from the CM, heading the Descent Module into its entry, descent and landing trajectory. It performs the entry, descent and landing on the Martian surface of a Landing Platform (LP) and its payloads for static science research. The DM consists of Landing Platform, Front shield and Rear Jacket (or Backshell) and a Parachute system. Note 1: The Landing Platform (LP) ensures the landing on Mars Surface and consists of Propulsion system, Landing devices, systems ensuring operation on Martian surface and scientific instruments. The CM-DM separation is implemented through a CM-DM Separation Assembly, which is composed by the Separation mechanism and the mechanical Adapter. The Rover Module (RM) which, egressing from inside the DM, allows a Rover Vehicle (RV) and its boarded experiments to perform science exploration onto the Mars Planet ALTEC Auditorium - Torino - Italy December 9-10, 2014

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 EXOMARS 2018 Reference Mission The transfer for the ExoMars 2018 mission is a short transfer, where the trajectory roughly resembles a half-ellipse. The obtained transfer for the 2018 opportunity departs Earth in May 2018 and arrives at Mars on 2019/1/15, fulfilling the constraint on the arrival Ls that states that it arrival shall not be in the global dust storm season. All trajectory design is subject to the following assumptions, which also implicitly apply to all applicable Launch opportunities:  Consistency with a Proton M / Breeze M launch  Application of a launch period that spans 21 consecutive days (with Launcher Programmes currently limited to 6)  Absence of Deep Space Manoeuvres (DSM) Note: Currently, a ΔV allocation of 25m/s for the Launcher Injection Correction (LIC) and 25 m/s for the transfer navigation has been assumed as a reliable figure  No constraints on the Mars hyperbolic arrival velocity The ExoMars 2018 mission comprises :  a Launch and Cruise phase carried out by the ExoMars Composite Spacecraft  an atmospheric Entry Descent and Landing (EDL) phase carried out by the Descent Module  two well-separated Mars Surface Science Missions, one implemented by the DM Static Landing Platform and one be the Rover Module that will egress the Surface Platform (SP) after completion of its Check-out after landing. ALTEC Auditorium - Torino - Italy December 9-10, 2014

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 EXOMARS 2018 Reference Mission EventDate Launch window7-27 May 2018 CM-DM separation15 January 2019 DM landing15 January 2019 (Ls = 324°) Rover Egress< 25 January 2019 Nominal end of mission 31 August 2019 (RM) 15 January 2021 (SP) Nominal sequence of events ALTEC Auditorium - Torino - Italy December 9-10, 2014

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 EXOMARS 2018 Reference Mission: CRUISE ALTEC Auditorium - Torino - Italy December 9-10, 2014 The escape sequences is 4.5 hours, counted from lift-off to separation of the payload from the Breeze M stage, when the Mission Operations control is handed-over to ESOC  TCM1 ((Launch +7 days) First Trajectory Correction  TCM2 (Launch +30 days) is to clean up the TCM1 error  TCM3 (EIP -30 days)  TCM4 (EIP -8 days)  TCM5 (EIP -2 days) The Spacecraft Composite (SCC) will perform the whole Cruise spinning at 2.5 rpm, controlled by the Carrier Module (CM) GNC. For the first 50 days, the SCC will keep a sun pointing attitude, guaranteeing the communication with the CM Low Gain antenna’s. After that and up to the preparation for CM-DM separation, the SCC will be Earth Pointing, except for Safe mode, to allow communication with Ground by means of the CM Medium Gain Antenna. Shortly before atmospheric entry the DM is separated from the CM by means of a linear Separation mechanism part of the DM. After being separated, the CM is not foreseen to operate and break/burn up during its uncontrolled entry in Mars atmosphere while the DM starts its EDL mission for landing onto the Mars surface.

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 EXOMARS 2018 Reference Mission: EDL ALTEC Auditorium - Torino - Italy December 9-10, 2014 The DM is separated from the CM 0.5 hours before crossing the Entry Interface Point (EIP). Prior to separation, the Spacecraft Composite is reoriented to the attitude that the DM requires at atmospheric entry, assumed parallel to the relative velocity at the EIP. In the current reference mission, the EIP is taken to be at 120 km altitude above a spherical planet radius of km; the reference entry flight path angle is °. The separation mechanism imparts relative linear velocity of at least 35 cm/s between DM and CM while the DM spinning rate, ranging between 2.25 and 2.75 rpm, is guaranteed by the SCC dynamics condition at release. For the DM, neither orbit nor attitude trim manoeuvres are possible after separation. After separation, the DM coasts autonomously to the Entry Interface Point followed by hyperbolic entry, descent and landing at its landing site (still to be selected at any latitude in the range 5 degrees South to 25 degrees North of the Martian surface). The DM will hit the top of the Martian atmosphere at approximately 20,000 km/h. A thermal shield at the bottom of the capsule will be used to decelerate to roughly twice the speed of sound. Thereafter, the parachute system will take over. However, even after the main parachute has reached its terminal velocity, the DM will be still traveling at more than 300 km/h. The last stage will involve the use of throttled liquid engines. A multi-beam radar will measure the distance to ground and the horizontal speed over the terrain. The DM’s computer will receive this information and combine it with its knowledge of the DM’s attitude to decide how to exercise the engines and achieve a controlled landing. Legs will be used for the final touchdown. Landing of the EDM occurs about 6.5 min after EIP.

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 EXOMARS 2018 Reference Mission: EDL ALTEC Auditorium - Torino - Italy December 9-10, 2014

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 Spacecraft Composite Configuration (1/2) ALTEC Auditorium - Torino - Italy December 9-10, 2014 SCC with deployed Solar Arrays SCC with stowed Solar Arrays

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 ALTEC Auditorium - Torino - Italy December 9-10, 2014 Spacecraft Composite Configuration (2/2)

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 ALTEC Auditorium - Torino - Italy December 9-10, 2014 Descent Module Configuration CM-DM Separation Adapter

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 ALTEC Auditorium - Torino - Italy December 9-10, 2014 SCC Avionics Block Diagram CAN bus