ESA s (future) Science Mission Overview

Transcription

1 ESA s (future) Science Mission Overview P. Falkner,, Science Direcrate, European Space Agency Peter.Falkner@esa.int / phone: P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page Contents Overview on future Science Mission situation Cosmic Vision Present TRS highlights with a focus on potential robotic technology needs Focus on planetary missions P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page 2

2 Cosmic Vision Herschel Planck 2007 LISA PF, launch 2009 JWST, launch 200 GAIA, launch 20 BC, launch 203 Cosmic Vision Ideas from community summarized in BR247 Call for proposals tentative Feb 2007 (SPC 78 Nov. 2006) To select up 3 M class (300 M ) & 3 L class (650 M ) missions for assessment No selection by now = difficult speak about future needs in detail P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page 3 Cosmic Visions Themes & 2 2 How How does does Solar Solar System work work? What What are are conditions for for life life & planetary formation? SolarPolar Orbiter (Solar Sailor) Heliopause Probe (Solar Sailor) Earth Magnespheric Swarm Jovian Insitu Planetary Observer (JEP) Kuiper belt Explorer Near Earth Asteroid sample & return From sun From sun edge edge solar solar The The Giant Giant Planets Planets ir ir environment environment Asteroids Asteroids small small bodies bodies Far Infrared Interferometer Jupiter Magnespheric Explorer (JEP) Near Infrared Terrestrial Planet Interferometer Europa Orbiting Surveyor (JEP) Mars Insitu Programme (Rovers & subsurface) Mars sample return Aurora Aurora From From dust dust gas gas stars stars planets planets From From exoplanets exoplanets biomarkers biomarkers Life Life & & habitability habitability in in solar solar Longer term Terrestrial Planet Astrometric Surveyor TerrestrialPlanet Spectroscopic Observer Looking for life Looking for life beyond solar beyond solar P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page 4 2

3 What are Technology Reference Studies? Hypotic science driven missions being not part ESA Science Programme introduced for potential future science missions : Identify critical enabling technologies Provide strategic focus for technology developments Provide a roadmap for technology developments Provide technology in Provide a olbox building blocks for future proposals With aim : enable low resource exploration missions assist in a nonpartisan manner community ESA in future proposal submission assessment Prepare Cosmic Vision P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page 5 What are Technology Reference Studies? Designed low cost (affordability) Small launcher (typical SoyuzFregat, 45 M ) Use MiniSat Use Highly Integrated Payload Avionics Suites (resource reduction) Launch windows: understing launch opportunities & repetition scheme Technology Development: typically within 5 technically realistic assumptions P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page 6 3

4 TRS Studies Aerobot & Microprobes > ASTRA 04 Sampling Mechanism Ling Aunomy Robotic arm Sampling Mechanism Ling Aunomy Ler & Robotic Arm? DSR heritage Venus Entry Probe Deimos Sample Return NEASR Near Earth Asteroid SR SF2B launch SF2B launch SF2B EntryProbe with Aerobot (floating 55 km) surface material Sample return with direct Earth reentry direct Earth reentry Atmospheric MicroProbes (5) potential surface & remote sensing investigations Atmospheric Orbiter Page 7 P. Falkner Science ASTRA WS 28Nov 2006, ESTEC TRS Studies No major robotics identified CSM JME JSE Aunomy Entry Probe? Microprobes? Ling (ling o difficult for st phase!) Cross Scale TRS Jupiter MiniSat Explorer Swarm 82 S/C 24 S/C escale tetrahedron (200 km) 4 S/C ionscale tetrahedron ( km) 24 S/C large scale ( km) SF2B launch Europa Orbiter + Jovian S/C Passively controlled formation flying Radar for subsurface investigations Jovian System Explorer Magnespheric (magnepause, magnetail, aurorae) Atmosphere entryprobe(s) (40 & 00 bar) Spinning spacecraft (up rps) P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page 8 4

5 Jupiter Minisat Explorer Study Jovian st st study study phase: phase: concentration concentration on on Europa Europa Exploration Exploration JME JME Relay Relay sat: sat: 6 6 P/L, P/L,.2.2 R j x j x R j Jupiter j Jupiter orbit orbit Equarial Equarial Jupiter Jupiter orbit orbit achieved achieved after after.2.2 Operational Operational life life 2 2 TID: TID: Mrad Mrad (4 (4 mm mm shield) shield) Europa Europa Orbiter: Orbiter: P/L, P/L, km km circ. circ. polar polar Europa Europa orbit orbit In In orbit orbit life life days days (limited (limited by by radiation radiation perturbations) perturbations) TID: TID: Mrad Mrad (0 (0 mm mm shield) shield).5.5 year year ur ur Galilean Galilean moons moons 2 2 nd nd study study phase: phase: extended extended Jovian Jovian System System Exploration Exploration JSE JSE Magnesphere: Magnesphere: dedicated dedicated orbiter(s) orbiter(s) Atmosphere: Atmosphere: entry entry probe(s) probe(s) Launch Launch with with SoyuzFregat SoyuzFregat 2B 2B Allchemical Allchemical propulsion propulsion option option baselined, baselined, SEP SEP backup. backup. Transfer Transfer duration: duration: Launch Launch mass mass in in GTO GTO P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page 9 Jupiter System Explorer / magnespheric scenarios Single S/C, equarial plane: Magnetail 2 entry probes possible View perpendicular equarial plane View in equarial plane 5x200 Rj 70x5 Rj Dual S/C, equarial plane: Magnepause + Magnetail View perpendicular equarial plane View in equarial plane 5x200 Rj no entry probe possible (TBC) Dual S/C, equarial polar plane: Magnepause + Magnetail + Poles 70x5 Rj View perpendicular equarial plane View in equarial plane 5x200 Rj P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page 0 5

6 Jupiter Entry Probe CDF (Nov 2005) bar bar probe probe Mass Mass P/L P/L resource resource 2 2,, W (peak), (peak), bps bps Entry Entry latitude latitude deg deg One One probe probe + + one one orbiter orbiter Descent Descent = = hour hour Variable Variable power power comms comms cope cope with with very very strong strong atmospheric atmospheric attenuation attenuation (23 (23 db) db) bar bar probe probe Mass Mass P/L P/L resource resource 2 2,, W (peak), (peak), bps bps Entry Entry latitude latitude between between deg deg Two Two probes probes + + one one orbiter orbiter Descent Descent = = hour hour Comms Comms scenario scenario complicated complicated but but should should be be feasible feasible Back cover 3 layers: ablar, structure, IFI Pilot chute Main chute available volume Front shield 3 layers: ablar, structure, IFI Antenna s Upper Shell Platform Lower Shell All dimensions in mm Robotic Probe: Main Challenge: Heat shield (TPS) & testing = driving cost! Pressure P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page Jupiter Summary Decent Probe Jupiter Summary: Europa Orbiter Stacked Magnespheric Orbiter Deployed JMO Main driver: distance from sun LILT solar arrays, power limitation harsh radiation environment cost cap most likely only orbiting spacecraft (remote sensing) ling o difficult, requires detailed exploration first Entry probe = challenging & expensive limited requirements on robotic technology P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page 2 6

7 Near Earth Asteroid Sample Return Objectives Composition Composition Primitive Primitive Bodies Bodies Early Early Solar Solar System System Condensation Condensation Mineralogy, Mineralogy, Remote Remote Sensing Sensing Ground Ground Truth Truth Composition Composition Regolith Regolith Scattering Scattering Properties Properties Organic Organic Compounds Compounds (?) (?) Gardening Gardening on on Small Small Bodies Bodies Status running KO: KO: 26Jul06/PM: 26Jul06/PM: 6Sep06/PDR: 6Sep06/PDR: 6Dec06 6Dec06 Initial Initial Mission Mission Analysis Analysis done done Investigation Investigation potential potential targets targets Design Design cost cost Trade: Trade: Sample Sample Return Return / / insitu insitu observation observation P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page 3 NEASR / Target identification Asteroid target selection: Priority Ctype related (B, F, G) All or types remain potential cidates D/P asteroids excluded from Sample Return scenario (Planetary Protection*) Mini. Size 200 m for a Ctype (magnitude H < 22) 3000 NEA 5 C, BFG & 07 Stype NEA identified A number accessible targets preliminary selected (999 JU3 (C), 4660 Nereus (C), 996 FG3 (C), 405 Wilson Harringn (C, F?), 2002 AT4 (D), etc.) Many more targets accessible but class is unknown! Problem for ling sample Return Limited knowledge surface properties & lowg environment design needs cope with wide range properties P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page 4 7

8 NEASR / Robotics Sample return: Cost problem but many challenges for Robotics: aunomous navigation & collision avoidance ling anchoring (aunomous), uchgo or hovering (TBS) subsurface access (drill) sample retrieval sample packaging sample transfer ERC/ERV docking (in case separated ler) InSitu mission: Reduced cost problem also many robotic challenges aunomous navigation & collision avoidance ling anchoring (aunomous) low genvironment subsurface access (drill) sample analysis mobility (most probably robotic arm) low genvironment difficult for rover P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page 5 TRS Studies Solar Sailing Solar Sailing Demonstration Technically challenging post CV 525 no major robotics SPO IHP GeoSail GeoSail Solar Sail demonstrar 40 x 40 m 2 Sail Size Rotate line apsides º / day Small S/C Technology P/L Solar Polar Orbiter Solar Sail 0.48 AU (3: resonance) Max inclination 83 5 year cruise 40 P/L mass Interstellar Heliopause Probe SF2B launch solar sail based ( m 2 ) 200 AU in 25 year RTG based P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page 6 8

9 Solar Sail Missions / GeoSail GeoSail GeoSail Solar Sail demonstrar 40 x 40 m 2 Sail Size Rotate line apsides º / day Small S/C Technology P/L R E x 23 R E S/C mass 250 GeoSail Solar Polar Orbiter Interstellar Heliopause Probe Increasing Technical Complexity P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page 7 TRS Technologies Microprobes Localization Communication (QinetiQ) running High Speed Impact (Vorticity) finished (2006) 2 System studies (ESYS TTI) finished (2004) Entry: Jupiter Entry numerical simulation (ESIL) running Venus Entry MicroProbes (ESIL) finished (2004) Jupiter Entry Probe (ESACDF, Oct 2005) finished (2005) Spacecraft Technology: Jupiter LILT solar cells (RWE) running HiRad. Solar Cell development (TRP) approval Solar Sail GNC (ESA internal study) running Solar Sailing Trajecries (Univ. Glasgow, McInnes) finished 04 Solar Sail Material Development (TRP) under ITT Enhanced Radiation Model for Jupiter (ONERA) finished Effective Shielding Methods for Jovian Radiation (TRP) approval TouchGo sample mechanism (GSTP06) under preparation (?) Instrumentation Technology: Jupiter Ground Penetrating Radar (ESACDF, Jun 2005) finished Advanced Radar Processing (GSP2006) running Miniaturization Radars (SEA) finished (2005) Planetary Radar running Payload Definition for (IHP, DSR, VEP, JME) finished Highly Integrated P/L suites Engineering Plan finished (2005) Highly Integrated P/L suites Detailed Design under negotiation 3 axis Fluxgate Magnemeter ASIC running Ground Penetrating Radar YAGI Antenna (TRP) under approval Insitu P/L: NanoRover + Geochemistry P/L (VHS) Mole + HP3 (Galileo, DLR) LMS ATR Melting Probes OSL surface dating P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page 8 9

10 Conclusion Difficult define needs on robotics at this stage within Science Program due pending CV525 call for proposals Provided overview on Technology Reference Studies (TRS) Main robotics could be expected for insitu missions (ling) = difficult aim due cost cap (300, 650 M ), better with international collaboration More defined after CV 525 mission selection for assessment! Thank you! P. Falkner Science ASTRA WS 28Nov 2006, ESTEC Page 9 0