From MARS To MOON. V. Giorgio Director of Italian Programs. Sorrento, October, All rights reserved, 2007, Thales Alenia Space

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1 From MARS To MOON Sorrento, October, 2007 V. Giorgio Director of Italian Programs

2 Page 2 Objectives of this presentation is to provide the Lunar Exploration Community with some information and status of the ongoing technology developments presently udergoing within the Mars Exploration Projects, namely EXOMARS and Mars Sample Return. The optimization of the sinergies to the level of basic tecnologies and system level capabilities is felt compulsory due to the financial envelopes required for such missions. Mars robotic mission, Moon mission and Earth Orbit Technologies development will allow the entire community to reach the important milestone: MEN WORKING ON MARS

3 From Mars to Moon Page 3 Main differences when approaching Mars and Moon missions: Martian gravity level is greater ( nearly twice) than the lunar one which has implication on landing and mobility technologies Mars has an atmosphere which implies differences in Entry, descent and landing operations ( tipically based on heatshields, parachutes and airbags) Soil temperature variations are different due to presence of atmosphere and distance to the Sun Approach to planetary protection is significantly different. For Mars esploration is a key requirement Communication latency requires extensive autonomy capabilities

EXOMARS Mission Objectives Page 4 First mission of the Aurora Exploration Programme Main Technology Demonstration Objectives: Entry, Descent and Landing (EDL) of a large payload on the surface of

4 EXOMARS Mission Objectives Page 4 First mission of the Aurora Exploration Programme Main Technology Demonstration Objectives: Entry, Descent and Landing (EDL) of a large payload on the surface of Mars; Surface mobility via a Rover having several kilometres of mobility range; Access to sub-surface via a Drill to acquire samples down to 2 metres; Automatic sample preparation and distribution for analyses of scientific instruments. Main Scientific Objectives (in order of priority): To search for signs of past and present life on Mars; To characterise the water/geochemical environment as a function of depth in the shallow subsurface; To study the surface environment and identify hazards to future human missions; To investigate the planet s subsurface and deep interior to better understand the evolution and habitability of Mars

Enhanced Baseline System Launch: Dec 2013 Arrival:

parking orbit, when conditions are optimal 100 100

3-sigma, major major axis axis dispersion dispersion

are optimal Landing: Spacecraft Composite Science

Pasteur Payload Data Relay NASA DSN Prime Back-up

5 Enhanced Baseline System Launch: Dec 2013 Arrival: Sep 2014 Arrival: Sep 2014 DM Release: Page 5 From a parking orbit, when conditions are optimal km km (target (target km) km) 3-sigma, 3-sigma, major major axis axis dispersion dispersion DM Release: From a parking orbit, when conditions are optimal Landing: Spacecraft Composite Science Elements Carrier & Descent Module or ExoMars Rover + Pasteur Payload Data Relay NASA DSN Prime Back-up Phobos-Grunt (TBC) ESA DSN Lander + Geophysics and Environmental Payload

6 Mission Overview Launch a Descent Module to Mars with supporting spacecraft infrastructure for Cruise Phase Release Descent Module into Mars atmosphere for automatic entry, and landing on surface Egress of a Rover from the landed module Minimum 6 months (180 Sol) Rover operation on mars surface with maximum range between sample locations of 1km (terrain dependent) Command and Data links through Mars Orbiter (NASA baselined, ESA options) Soyuz-Fregat launch from Kourou HEO Apogee Raising Launch in 2013 NASA Orbiter for Rover relay Page 6 Cruise to Mars

7 Deployed Rover On Lander Page 7

8 Technology Highlights Page 8 Rover mass optimization (material, compacted avionic, miniaturization) Sample collection, preparation and preservation (Drill & SPDS technology) Rover mobility, navigation and autonomy Rover control concept including the Operations Center Release from orbit of the landing vehicle

9 MSR MISSION PROFILE Page 9

10 PLANNING Page 10-3 Launch Windows identified: 2018 / 2020 / 2022 (AR-5) - Precursor Missions Launch : 2016 (Soyuz) - Precursor Mission Approval : 2008 Phase A2: September 2006 September 2007

11 MSR Peculiarities Page 11 Entry, Descent and Landing on Mars Very high landing mass w.r.t. other missions Requirements on landing site accuracy very severe (in the order of 10-km semimajor axis), which means GUIDED Entry instead of Ballistic Soft Landing and Soil Recognition capability RendezVous and Capture Capture: never done before Docking: much more complex than capture, but still under trade-off; never done before in authonomous way Ascent from Mars Surface Never done before Earth Re-entry Never done before at the required speed

12 Precursor Mission Scenarios Page 12 M-1 M-2 M-3 M-4 RV&C Full - RV&C, scaled Only GNC Landing - Full, scaled Full, scaled Full, scaled Environment Mars; Aerobraking Moon Moon Moon Guided entry Ascent - Partial Only Ops - Sample handling Full - Partial - Earth re-entry

M1 Demo objectives summary Aerobraking Launch Mass Page 13 3- Target Orbit Aquisition 2- Orbiter + ERC Capture into Mars orbit RV & Capture 8- Rendez-vous and Capture SHS; Backwards PP

13 M1 Demo objectives summary Aerobraking Launch Mass Page Target Orbit Aquisition 2- Orbiter + ERC Capture into Mars orbit RV & Capture 8- Rendez-vous and Capture SHS; Backwards PP Rules 9- Return and Earth entry 4- Assy#2 Transfer to Mars 1- Assy#1 Transfer to Mars 7- Ascent with the sample 6- Sample Collection 5- Descent Module + MAV release and entry, descent and landing

14 Study Logic Mission Requirements - Launcher (SOYUZ) - Launch Date ( ) - Global Dust Storm avoidance Science Implementation - Small Lander(s) - Orbiter P/L Trade-off on: -Launch strategy Demo Objectives implementation - RV&Capture - Aerobraking -Trajectory (Δ-V) - Sample Handling System -Objectives sharing Mission design Page 14 System design

15 MSR Representativity: Page 15 Soft Landing Hazard Avoidance Rover for Lunar Surface Mobility

16 Mission Requirements - Launcher (SOYUZ) - Launch Date ( ) Demo Objectives implementation - Soft Landing - Hazard avoidance Page 16 Science Implementation - Small ROVER - Surface P/L Package Trade-off on: -Launch strategy -Trajectory (Δ-V) -Objectives Mission design System design

NEXT Exploration Science and Technology Mission. Relevance for Lunar Exploration

NEXT Exploration Science and Technology Mission Relevance for Lunar Exploration Alain Pradier & the NEXT mission team ILEWG Meeting, 23 rd September 2007, Sorrento AURORA PROGRAMME Ministerial Council