ESA’s (future) Science Mission...
Transcript of ESA’s (future) Science Mission...
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Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
P. Falkner Science Missions @ ASTRA WS 28-Nov 2006 , ESTEC Page 1
ESA’s (future) Science Mission Overview
P. Falkner
Planetary Exploration Studies Section, Science Payload & Advanced Concepts Office, Science Directorate, European Space Agency
[email protected] / phone: +31 71 565 5363
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
P. Falkner Science Missions @ ASTRA WS 28-Nov 2006 , ESTEC Page 2
Contents
• Overview on future Science Mission situation• Cosmic Vision 2015 – 2025• Present TRS highlights with a focus on
potential robotic technology needs
• Focus on planetary missions
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Cosmic Vision
• Cosmic Vision 2015 – 2025• Ideas from community summarized in
BR-247• Call for proposals tentative Feb 2007
(SPC 7-8 Nov. 2006)• To select up to
3 M class (~300 M€) & 3 L class (~650 M€)
missions for assessment• No selection by now
= difficult to speak about future needs in detail
Herschel – Planck 2007LISA PF, launch 2009JWST, launch 2010GAIA, launch 2011BC, launch 2013
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Terrestrial PlanetAstrometric Surveyor
Near Infrared Terrestrial Planet Interferometer
From exo-planets tobiomarkersFrom exo-planets tobiomarkers
Looking for life beyond the solar
system
Looking for life beyond the solar
system
Life & habitability in the solar system
Life & habitability in the solar system
From dust and gasto
stars and planets
From dust and gasto
stars and planets
What are the conditions for life& planetary formation ?
What are the conditions for life& planetary formation ?
Solar-Polar Orbiter (Solar Sailor)
EarthMagnetospheric Swarm
Helio-pause Probe(Solar Sailor)
Near Earth Asteroidsample & return
Far InfraredInterferometer
Jupiter MagnetosphericExplorer (JEP)
Jovian In-situ Planetary Observer (JEP)
Mars In-situ Programme(Rovers & sub-surface)
Europa OrbitingSurveyor (JEP)
The Giant Planets and their
environment
The Giant Planets and their
environment
Asteroids and small bodies
Asteroids and small bodies
From the sun to the edge of the solar system
From the sun to the edge of the solar system
How does the Solar System work ?How does the Solar System work ?
Mars sample and return
Terrestrial-Planet Spectroscopic Observer
Kuiper belt Explorer
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Cosmic Visions Themes 1 & 2
TRS
TRS
TRS
TRS
TRS
TRS
TRS
Longer term
Aurora
TRS
TRS
Aurora
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What are Technology Reference Studies ?
• Hypothetic science driven missions being not part of the ESA Science Programme
• introduced for potential future science missions to:
Identify critical enabling technologies
Provide strategic focus for technology developments
Provide a roadmap for technology developments
Provide technology in time
Provide a toolbox and building blocks for future proposals
• With the aim to:
enable low resource exploration missions
assist in a non-partisan manner the community and ESA in future proposal submissionand assessment
Prepare Cosmic Vision 2015 – 2025
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What are Technology Reference Studies ?
Designed to low cost (affordability)
Small launcher(typical Soyuz-Fregat, ~ 45 M€)
Use of MiniSat
Use Highly Integrated Payload and Avionics Suites (resource reduction)
Launch windows: 2015 to 2025+understanding of launch opportunities & repetition scheme
Technology Development: typically within 5 years technically realistic assumptions
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TRS Studies
Venus Entry Probe
SF-2B launch
Entry-Probe with Aerobot (floating ~55 km)
Atmospheric MicroProbes (15)
Atmospheric Orbiter
Deimos Sample Return
SF-2B launch
1 kg surface material
direct Earth re-entry
DSR
Near Earth Asteroid - SR
SF-2B
Sample return with direct Earth re-entry
potential surface & remote sensing investigations
NEA-SRheritage
Aerobot & Microprobes> described @ ASTRA 04
Sampling MechanismLanding Autonomy- Robotic arm
Sampling MechanismLanding AutonomyLander & Robotic Arm ?
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TRS Studies
Cross Scale TRSSwarm of 8-12 S/C
2-4 S/C e-scale tetrahedron (2-100 km)
4 S/C ion-scale tetrahedron (100- 2000 km)
2-4 S/C large scale (2000-15000 km)
“Passively controlled” formation flying
Spinning spacecraft (up to 1 rps)
Jupiter MiniSat Explorer
SF-2B launch
Europa Orbiter + Jovian S/C
Radar for subsurface investigations
Jovian System Explorer
Magnetospheric (magnetopause, magnetotail, aurorae)
Atmosphere entry-probe(s) (40 & 100 bar)
JMECSM
JSE
No major robotics identified
AutonomyEntry Probe ?Microprobes ?Landing (landing too difficult for 1st phase!)
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Jupiter Minisat Explorer
1st study phase: concentration on Europa Exploration JME
• Relay sat: 16 kg P/L, 11.2 Rj x 28 Rj Jupiter orbit
• Equatorial Jupiter orbit achieved after 1.2 years
• Operational lifetime ~2 years
• TID: 1 Mrad (4 mm shield)
• Europa Orbiter: 36 kg P/L, 200 km circ. polar Europa orbit • In orbit life time ~ 66 days (limited by radiation and perturbations)
• TID: 1 Mrad (10 mm shield)
• 1.5 year tour of the Galilean moons
1st study phase: concentration on Europa Exploration JME
• Relay sat: 16 kg P/L, 11.2 Rj x 28 Rj Jupiter orbit
• Equatorial Jupiter orbit achieved after 1.2 years
• Operational lifetime ~2 years
• TID: 1 Mrad (4 mm shield)
• Europa Orbiter: 36 kg P/L, 200 km circ. polar Europa orbit • In orbit life time ~ 66 days (limited by radiation and perturbations)
• TID: 1 Mrad (10 mm shield)
• 1.5 year tour of the Galilean moons
Study of the Jovian system
2nd study phase: extended Jovian System Exploration JSE• Magnetosphere: dedicated orbiter(s)
• Atmosphere: entry probe(s)
2nd study phase: extended Jovian System Exploration JSE• Magnetosphere: dedicated orbiter(s)
• Atmosphere: entry probe(s)
• Launch with Soyuz-Fregat 2-1B • All-chemical propulsion option baselined, SEP back-up.• Transfer duration: 6-7 years • Launch mass into GTO 3000 kg
• Launch with Soyuz-Fregat 2-1B • All-chemical propulsion option baselined, SEP back-up.• Transfer duration: 6-7 years • Launch mass into GTO 3000 kg
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Jupiter System Explorer / magnetospheric scenarios
View perpendicular to equatorial planeView in equatorial plane
View perpendicular to equatorial plane View in equatorial plane
View perpendicular to equatorial planeView in equatorial plane
Single S/C, equatorial plane: Magnetotail
Dual S/C, equatorial plane: Magnetopause + Magnetotail
Dual S/C, equatorial and polar plane: Magnetopause + Magnetotail + Poles
15x200 Rj
15x200 Rj
15x200 Rj
70x15 Rj
70x15 Rj
1 to 2 entry probes possible
no entry probe possible (TBC)
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Jupiter Entry Probe CDF (Nov 2005)
All dimensions in mm
100 bar probe- Mass ~ 320 kg- P/L resource ~ 12 kg, ~30 W (peak), ~350 bps - Entry latitude +3 deg- One probe + one orbiter- Descent time = 1 hour- Variable power comms system to cope with very
strong atmospheric attenuation (~23 dB)
100 bar probe- Mass ~ 320 kg- P/L resource ~ 12 kg, ~30 W (peak), ~350 bps - Entry latitude +3 deg- One probe + one orbiter- Descent time = 1 hour- Variable power comms system to cope with very
strong atmospheric attenuation (~23 dB)
40 bar probe- Mass ~ 270 kg- P/L resource ~ 12 kg, ~30 W (peak), ~350 bps- Entry latitude between -7 and +3 deg- Two probes + one orbiter- Descent time = 1 hour- Comms scenario complicated but should be feasible
40 bar probe- Mass ~ 270 kg- P/L resource ~ 12 kg, ~30 W (peak), ~350 bps- Entry latitude between -7 and +3 deg- Two probes + one orbiter- Descent time = 1 hour- Comms scenario complicated but should be feasible
Antenna’sPilot chuteMain chute
available volume
Upper Shell
Lower Shell
Back cover3 layers: ablator, structure, IFI
Front shield3 layers: ablator, structure, IFI
Platform
Robotic Probe:
• Main Challenge: Heat shield (TPS) & testing = driving cost !
• Pressure
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Jupiter - Summary
Jupiter Summary:
Main driver: - distance from sun LILT solar arrays, power limitation- harsh radiation environment- cost cap
most likely only orbiting spacecraft (remote sensing) landing too difficult, requires detailed exploration first
Entry probe = challenging & expensive
limited requirements on robotic technology
Decent Probe Europa OrbiterStacked Magnetospheric Orbiter
Deployed JMO
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Near Earth Asteroid Sample Return
Objectives• Composition of Primitive Bodies• Early Solar System Condensation• Mineralogy, Remote Sensing and Ground Truth• Composition of the Regolith and Scattering
Properties• Organic Compounds (?)• Gardening on Small Bodies
Objectives• Composition of Primitive Bodies• Early Solar System Condensation• Mineralogy, Remote Sensing and Ground Truth• Composition of the Regolith and Scattering
Properties• Organic Compounds (?)• Gardening on Small Bodies
Status - running• KO: 26-Jul-06/PM1: 6-Sep-06/PDR: 6-Dec-06
• Initial Mission Analysis done
• Investigation of potential targets
• Design to cost
• Trade: Sample Return / in-situ observation
Status - running• KO: 26-Jul-06/PM1: 6-Sep-06/PDR: 6-Dec-06
• Initial Mission Analysis done
• Investigation of potential targets
•• Design to costDesign to cost
•• Trade: Sample Return / inTrade: Sample Return / in--situ situ observationobservation
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NEA-SR / Target identification
Asteroid target selection:
• Priority to C-type and related (B, F, G) All other types remain potential candidates
• D/P asteroids excluded from Sample Return scenario (Planetary Protection*)
• Mini. Size ~ 200 m for a C-type (magnitude H < 22) 3000 NEA
15 C, 11 BFG & 107 S-type NEA identified
A number of “accessible” targets preliminary selected (1999 JU3 (C), 4660 Nereus (C), 1996 FG3 (C), 4015 Wilson Harrington (C, F?),
2002 AT4 (D), etc.)
• Many more targets accessible but class is unknown !
Problem for landing and sample Return
• Limited knowledge of surface properties & low-g environmentsystem design needs to cope with wide range of properties
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NEA-SR / Robotics
Sample return:
Cost problem
but many challenges for Robotics:- autonomous navigation & collision avoidance- landing and anchoring (autonomous), touch-and-go or hovering (TBS)- subsurface access (drill) and sample retrieval - sample packaging- sample transfer to ERC/ERV - docking (in case of separated lander)
In-Situ mission:
Reduced cost problem
also many robotic challenges- autonomous navigation & collision avoidance- landing and anchoring (autonomous) - low g-environment- subsurface access (drill) and sample analysis- mobility (most probably robotic arm) - low g-environment difficult for rover
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TRS Studies – Solar Sailing
Solar Polar OrbiterSolar Sail based
@ 0.48 AU (3:1 resonance)Max inclination 83°5 year cruise time~40 kg P/L mass
GeoSailSolar Sail demonstrator
40 x 40 m2 Sail SizeRotate line of apsides 1º / daySmall S/C and Technology P/L
IHP
Interstellar Heliopause Probe
SF-2B launch
solar sail based (60.000 m2)
200 AU in 25 year
RTG based
GeoSail
SPO
Solar Sailing DemonstrationTechnically challenging – post CV 1525no major robotics
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Solar Sail Missions / GeoSail
GeoSailSolar Sail demonstrator
~40 x 40 m2 Sail SizeRotate line of apsides 1º / daySmall S/C and Technology P/L
11 RE x 23 RE
S/C mass ~ 250 kg
GeoSail
GeoSailSolarPolar
Orbiter
InterstellarHeliopause
Probe
Increasing Technical Complexity
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Microprobes
• Localization and Communication (QinetiQ) - running
• High Speed Impact (Vorticity) – finished (2006)
• 2 System studies (ESYS and TTI) – finished (2004)
Entry:
• Jupiter Entry numerical simulation (ESIL) - running
• Venus Entry and MicroProbes (ESIL) – finished (2004)
• Jupiter Entry Probe (ESA-CDF, Oct 2005) – finished (2005)
Instrumentation Technology:
• Jupiter Ground Penetrating Radar (ESA-CDF, Jun 2005) – finished
• Advanced Radar Processing (GSP2006) – running
• Miniaturization of 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 Magnetometer ASIC – running
• Ground Penetrating Radar YAGI Antenna (TRP) – under approval
TRS Technologies
Spacecraft Technology:
• Jupiter LILT solar cells (RWE) - running
• Hi-Rad. Solar Cell development (TRP) – approval
• Solar Sail GNC (ESA internal study) – running
• Solar Sailing Trajectories (Univ. of 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
• Touch-and-Go sample mechanism (GSTP06) – under preparation (?)
In-situ P/L:
• Nano-Rover + Geochemistry P/L (VHS)
• Mole + HP3 (Galileo, DLR)
• LMS
• ATR
• Melting Probes
• OSL – surface dating
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Conclusion
• Difficult to define needs on robotics at this stage within Science Program due to pending CV1525 call for proposals
Provided overview on Technology Reference Studies (TRS)
• Main robotics could be expected for in-situ missions (landing) = difficult aim due to cost cap (300, 650 M€), better with international collaboration
• More defined after CV 1525 mission selection for assessment !
Thank you !