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

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


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



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



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 ?



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)


• 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


• Europa Orbiter: 36 kg P/L, 200 km circ. polar Europa orbit • In orbit life time ~ 66 days (limited by radiation and perturbations)


• 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



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



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



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



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



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 !

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