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The European S Pace Exploration Programme “Aurora” The European S pace Exploration Programme “Aurora” Accademia delle S cienze Torino, 23rd May 2008 B. Gardini - E S A E xploration Programme Manager To, 23May08 1 Aurora Programme ES A Programme (2001) for the human and robotic exploration of the S olar S ys tem time Automatic Mars Missions Cargo Elements First Human IS S of first Human Mission to Mission Mars Moon B asis Mars S ample ExoMar Return To, 23May08 s (MS R) 2 Columbus Laboratory - IS S Launched 7 Feb. 2008, with Hans Schlegel, after Node2 mission with Paolo Nespoli To, 23May08 3 Automated Transfer Vehicle (ATV) Europe’s Space Supply Vehicle ATV- Jules Verne •Docked to ISS: 3 April 2008 •First ISS Re-boost: 25 April 2008 To, 23May08 •De-orbit: ~ August 2008 4 Human Moon Mission Moon: Next destination of international human missions beyond ISS Test-bed for demonstration S urface of innovative technologies Mobility & capabilities for sustaining human life on planetary surfaces. S ustainable Energy Life Provision & S upport Management In-S itu Robotic Support Resourc e Utilisatio To, 23May08 n 5 ES A Planetary Missions Cassini / Huygens (1997-2005) sonda a Saturno y Titán Rosetta (2004-…) Encuentro con el cometa Smart 1 (2003-2006) 67P Churyumov-Cerasimenko Sonda a la luna Mars Express (2003-…) Estudio de Marte Soho (1995-…): interacción Sol-Tierra To, 23May08 6 Mars Express HRS C (3D, 2-10m res) http://www.esa.int/esa-mmg/mmg.pl? To, 23May08 7 Why Life on Mars Early in the his tory of Mars , liquid water was present on its s urface; S ome of the proces ses cons idered important for the origin of life on Earth may have als o been pres ent on early Mars; Es tablishing if there ever was life on Mars is fundamental for planning future miss ions. To, 23May08 8 Comparative Planetology Water can only be found as steam on Venus surface and atmosphere and ice on Mars To, 23May08 9 Vikings 1 & 2 (1976) The Viking GC/MS did not detect organics above part per billion (ppb) level. However, the detection limit for amino acids was in the tens of ppm range At ppm level, amino acids from ~107 cells per gram of Martian soil Vikingwould did notnot rule out the possibility of life on Mars, past or present. been detected To, 23May08 10 EE XX OO MM AA RR SS ESA’s mission to search for signs of life on Mars To, 23May08 11 ExoMars h c n or + u 2013 a ARIANE 5 Proton-M Spacecraft L PRIME BACK-UP Composite NASA O + C NAS A S /C m e l (MRO) e NAS A ES A T DSN DSN Descent s p Module O M released from D Mars Orbit Rover s (210kg) d GEP (55kg) a Pasteur P/ O Humboldt l y L P/L Instr. a P Instr. (8.5kg) (16.5kg) To, 23May08 12 Deployed Rover (Pasteur) on Lander To, 23May08 13 GEP (Humboldt) Geophysical Environmental Instrument Package (GEP) To, 23May08 14 Mobility + Access to the subsurface Nominal mission: 180 sols; Nominal science: 7 Experiment Cycles + 2 Vertical Surveys; Extended mission: 10 additional EC; EC length: 15–18 sols; Rover mass: 210 kg. 2-m depth2-m To, 23May08 15 depth How deep? Adapted from Kminek and Bada (2006). 0.5 Gyr 1.0 Gyr 3.0 Gyr S urviving fraction of amino acids versus depth after simulated exposures of 0.5, 1.0, and 3.0 Gyr to ionising radiation in the Martian subsurface. For an initial abundance corresponding to that in a typical cell, the present detection limit of 0.01 ppb per amino acid can tolerate a reduction of 10-2 to 10-6 (red dashed lines), beyond which amino acid signatures become undetectable. When searching for biomarkers of Martian life that became extinct more than 3 Gyr ago, it is necessary to access the subsurface in the range of 2 m (yellow area). To, 23May08 16 Entry, Descent and Landing … Entry Energy dissipation via aerodynamic drag; Velocity Range: start ~5.4 km/s end ~430 m/s. Parachute Descent Energy dissipation via aerodynamic drag; Velocity Range: start ~430 m/s end ~85 m/s. Retrorockets Energy dissipation via propulsive impulse; Velocity Range: start ~85 m/s end ~10-15 m/s. Landing Landing with airbags Courtesy of Velocity Range: start ~10– Vorticity/AeroSekur 15 m/s end 0 m/s. To, 23May08 17 … on the S urface … guided from the R over Control Centre (Torino). Alcatel Alenia S pace - Italy is the ExoMars Prime Contractor. To, 23May08 18 ExoMars Science CZ ROM S LUX IRL GR BRA AUS JPN HUN CDN ExoMars Participating Scientists N PL FIN Total: 535 A P B RUS DK NL CH E USA D UK I F 0 10 20 30 40 50 60 70 80 90 100 110 120 To, 23May08 19 Italian S cience Team Coordinators Pasteur Payload: Infrared Spectrometer (MIMA): G. Belluci (Roma); Drill borehole IR spectrometer (Ma-MISS): A. Coradini (Roma); X-Ray Diffractometer (Mars-XRD): L. Marinangeli (Pescara); Humboldt Payload: Dust Instrument Suite (MEDUSA): L. Colangeli (Napoli); To, 23May08 20 Other Instruments with Italian S cientists PanCam (Panoramic Camera System) V. Formisano (Roma); WISDOM (Shallow GPR) R. Orosei (Roma), F. Ferri, F Angrili (Padova); MicrOmega (VIS + IR microscope) A. Coradini (Roma); AEP (Meteorological S uite) L. Colangeli (Napoli), F. Ferri (Padova); EIS S (Ground-Penetrating Radar) R. Orosei (Roma), F. Ferri, F Angrili (Padova); IRAS (Radiation instrument) A. Di Lellis (Roma), M. S torini (Roma), F. Constanzo (Perugia); LaRa (Radioscience experiment) P. Tortora (Bologna); S EIS (S eismometer) A. Amato, M. Cocco (Roma), A. Zollo (Napoli); Italian UVIS scientists (UV S pectrometer) are the most numerous in the L. PasteurColangeli instrument (Napoli); teams, overall the Italian scientists are the 2nd most numerous. To, 23May08 21 Pasteur – Humboldt Instruments CONTEXT e t o PanCam m SUPPORTING e MIMA R SUB-SYSTEMS WISDOM t CLUPI c e a t t i Mössbauer n u o Allocated Pasteur S Raman & LIBS Drill System C (2-m depth & instrument mass: 16.5 kg MicrOmega Mars_XRD surface) . b incl. Borehole IR a L l a ORGANICS/LIFE c i t y l Urey a n Sample Preparation MOMA A (Life Marker Chip & Distribution ) System Allocated Humboldt ENVIRONMENT MEDUSA instrument mass: 8.5 kg IRAS Accommodated UVIS in Humboldt AEP Payload To, 23May08 22 The international context 2005 2007 2009 2011 2013 Mars Telecom Orbiter ExoMars MS L: powerful geology ExoMars : next- rover; large 2-D mobility. generation To, 23May08 instruments ;3-D 23 mobility. Mars S ample Return - MS R First robotic mission including all elements representative of a human mission to Mars : Earth / Mars Transfer S tage Mars Orbiter Descent Module Mars Ascent Vehicle Earth re- entry vehicle Main objectives in technology Main objectives in science: Large mass soft landing S earch for traces of past or present life Ascent from Mars on Mars on the basis of Martian S ample collecting device soil/rock samples from several Planetary protection locations and from deep under the surface To, 23May08 24 Reference MS R Architecture (1) Mars Ascent Mars Vehicle launch & DM sample container Carrier Entry (SC) separation Separation RendezvousOrbit & Capture of SC by Orbiter Landing on Sample Surface Acquisition (Mobile) Earth Mars Orbit Lander Launch Atlas V (2020) Current architecture based on ESA / NASA- JPL and iMARS Earth investigations To, 23May08 25 Reference MS R Architecture (2) Mars Sample Rendezvous & Capture Container (SaC) of SaC by Orbiter Mars Orbit Ejection of redundant Orbiter hardware insertion Mars-Earth Separation of Propulsion transfer Orbiter & Earth Module avoidance Separation Orbiter Launch High-speed Earth A5 ECA (2020-2022) Re-Entry of Capsule Earth Orbit Landing, sample recovery and transfer to Sample Receiving Facility Earth To, 23May08 26 ES A MS R Preparatory Programme Consolidate mission design & schedule in close cooperation with the International Mars Exploration Working Group (IMEWG/ IMARS ), NAS A - JPL and national agencies; Prepare Europe to assume a strong role in MS R by: Identifying potential areas of contribution, initiate detailed s tudy and design of individual European candidate mis sion elements Intens ification of technology development / demons tration effort for the identified European flight s egment elements and the s cientific capabilities aimed at in-situ analys is of s amples S tart the des ign of the S ample Receiving and Curation Facilities & promote the cons titution of an MS R Ins titute in To, 23May08 27 Europe A programme proposal is being prepared for approval at the ES A Council at Ministerial level in November 2008. S ystem Trade-offs • Analysis of system level options will be carried out by European Industry to ensure a robust architecture which satisfies challenging mission requirements: • Mobility range versus landing accuracy • S ample collection redundancy • MAV propulsions options • Number of return capsules • Bio-sealing location Liquid MAV Lower landing Higher landing Propulsion accuracy higher accuracy lower System rover range and time rover range requirements requirements Solid MAV Propulsion System To, 23May08 28 Mission Element S tudy & Design Detailed study and design, at Phase B1 level, of key mission elements: • Mars Orbiter vehicle – performing rendezvous and capture, and Earth return • S ample collection system – primary/backup drill on mobile rover and static platform • Instrumentation for in-situ sample analysis • Mars Ascent Vehicle – propulsion system, vehicle design • Bio-S ealing & Containment system • S urface Platform elements – container transfer system etc. • Earth Return Capsule • S ample Receiving Facility – bio-hazard assessment etc. To, 23May08 29 MS R Technologies Development • Key mission elements under study will be supported by specific technology development efforts • Major areas already identified include: • B iocontainment – sealing and monitoring technologies • Planetary Protection – bio-burden control • S urface S ampling S ystems – drill based acquisition etc.
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