1a esa asi aurora

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Information about 1a esa asi aurora

Published on January 25, 2008

Author: Massimo

Source: authorstream.com

Preparatory European Space Exploration Programme “Aurora” Mars Robotic Missions:  Preparatory European Space Exploration Programme “Aurora” Mars Robotic Missions ASI – ESA Workshop on International Cooperation For Sustainable Space Exploration Abbazia di Spineto 5th May 2005 Introduction:  Introduction The foundations of the Aurora Programme were set in early 2001 via a “Call for ideas” addressed to the scientific community at large. An overwhelming response from several hundred scientists all around the world indicated Mars exploration as the first priority, with the “search for life” as the underlying theme. The 1st “Aurora Exploration Workshop” in April 2001 identified a Mars Exobiology Mission (ExoMars) and a Mars Sample Return (MSR) mission as the first steps in Aurora. Basic requirements were identified for the two missions defined above: ExoMars: surface mobility & drill (1.5-2.0 m) MSR: investigate a “minimum” mission design Science Workshop Recommendations:  Science Workshop Recommendations The science content of the Aurora Programme has been reviewed at the 2nd Aurora Science Workshop on the 6-7th April in Birmingham, attended by more than one hundred scientists from Europe, UK and US. Several Mars missions concepts have been presented and thoroughly debated. The recommendations from the Scientific community were: Launch date 2011, to allow build up of expertise and financial margins for a substantial European contributions to the 2016 NASA MSR mission Privilege a mission with a large Rover, which potentially represent the major European contribution to the international MSR mission Extend the ExoMars mission scientific objectives to include a package of seismic / meteorology instruments and secure the Beagle2 science, in particular the isotopic composition analysis Mars Exobiology Mission (ExoMars):  Mars Exobiology Mission (ExoMars) ExoMars / Pasteur Main technology objectives: Safe landing of a large size payload Surface mobility (Rover) and access to the subsurface (drill) Rover power generation using solar arrays Forward Planetary Protection Main scientific objectives: To search for traces of past and present life on Mars To identify surface hazards to future human missions To characterise the shallow subsurface water/geochemical composition and vertical distribution profile Slide5:  Estimated Pasteur mass: 40 kg The composition of the Payload is under review (2nd Aurora Science Workshop) ExoMars: Pasteur Payload Composition The Pasteur Payload includes a drill (1.5 to 2.0 m drilling depth) and a sample-handling device, for collecting and analysing samples from within surface rocks, and from underground Slide6:  ExoMars Mission Baseline (Orbiter) Launcher: Ariane 5 ECA Robust design for all launch dates, mass margin at launch:> 20% Spacecraft stack composed of: Orbiter to deliver the Descent Module and operate as data relay once in its final orbit Descent Module with rigid front shield technology to carry the Rover and its Pasteur Instruments payload EDLS design (MER type) with non-vented airbags and retrorockets. Release of Descent Module from Mars orbit, after dust storm season. International cooperation: NASA: Pasteur Instruments from US / EDLS and Rover design validation Russia: RHUs / Rover chassis design validation Slide7:  ExoMars Mission Baseline Orbiter scientific instruments: 30kg allocation AO instruments nationally funded for (e.g.) next generation Mars Express instruments and global atmospheric research via remote sensing. secure valuable science years after the successful completion of the Rover operations (primary mission). Pasteur instruments: 40 kg Rover exploration range: 10+ km/180sols Launch dates: Launch Nov. 2011 / arrival Sept 2012 / landing April 2013 at the end of the dust storm season Launch June 2013 / landing April 2015 Slide8:  ExoMars – Lite (Carrier-Option) Launcher: Soyuz 2b (from Kourou) Mass margin at launch: 20% Spacecraft composed of: Carrier to deliver the Descent Module from hyperbolic trajectory Descent Module with rigid front shield technology to carry the Rover and its Pasteur payload EDLS design (MER type) with non-vented airbags and retrorockets. An advanced EDLS based on vented airbags, if qualified on time, would allow landing of a larger Rover / Payload International cooperation: NASA: Pasteur Instruments from US / Mars Telecom Orbiter (mandatory) / EDLS and Rover design validation Russia: RHUs / Rover chassis design validation ExoMars – Lite Mission:  ExoMars – Lite Mission Long cruise required for achieving: Acceptable mass performance arrival after dust storm season Release of Descent Module from hyperbolic trajectory for acceptable mass performance Carrier scientific instruments: None. Mission success will depend on the Rover science (primary mission). Pasteur instruments: 36 kg Rover exploration range: 10+ km / 180 sols Launch dates: Launch June 2011 / landing June 2013 Launch May 2013 / landing March 2015 Birmingham Science Workshop follow up:  Birmingham Science Workshop follow up Reassess the Soyuz / Ariane 5 launch capability and mission design to accommodate additional instruments (seismic package / Beagle2 science). Start immediately the preparation of a dedicated Announcement of Opportunity (AO) for the seismic and Beagle2 science instruments aiming at a finalized Payload complement definition by October-November 2005 Continue discussions with NASA for the financing of the US Pasteur instruments and the provision of telecom infrastructure for data relay (e.g. via the NASA Mars Telecom Orbiter – 2009). Further discuss with NASA the definition and possible European participation to the MSR Continue the preparatory work for the Council at Ministerial level. A strategy paper will be presented for discussion at next Aurora Board of Participants and the PB – HSR Backup charts:  Backup charts Rover design:  Rover design With RHUs Without RHUs Slide13:  Pasteur Concept lay-out (option 1) Pasteur include the instruments and a Pasteur Service Module Drill + Corer, on a separate, articulated arm hosting also the contact instruments Pancam, Navcam and IR spectrometer on telescopic arm. SPDS has a robotic arm and a 20 position carrousel Slide14:  Site Characterisation Determine the geological context Slide15:  To ascertain the past presence of water and establish geochemistry Close-up imager Brush Mössbauer spectrometer APXS Raman spectrometer fibre If results are interesting, obtain a core sample: Underground: with the 2-m drill Surface rock: using a small corer Contact instruments Examine surface rocks Slide16:  Analytical laboratory Flow diagram Slide17:  Ionizing & UV radiation Spectrum, absorbed dose, quality factor, dose equivalent Dust measurements Morphology, size distribution, deposition rate, properties, relation to climatology Dust devils: pressure, direction, speed, spatial and temporal scales, effects Climate & meteorology Temperature Pressure Humidity Ice condensation Water and CO2 cycle Also addressed by other Pasteur instruments Hazards and environment

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