Third European Space Weather Week, 13-17 November 2006 Page 1 Planetary Exploration Studies Section Science Payload & Advanced Concepts Office ESAs Technology.

Third European Space Weather Week, 13-17 November 2006 Page 1

Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office

ESA’s Technology Reference Studies

ESA’s Technology Reference Studies:From Earth to Jupiter and beyondFrom Earth to Jupiter and beyond

M.L. van den Berg, P. Falkner, A. C. Atzei, A. Lyngvi, D. Agnolon, A. Peacock

Planetary Exploration Studies Section Science Payload & Advanced Concepts Office ESA/ESTEC




What they are:

Technologically demanding and scientifically meaningful mission concepts, that are not part of the ESA science programme

Aim:

Strategic focus on critical technology development needs for potential future science missions (e.g. from Cosmic Vision)

How:

Design feasible and consistent mission profiles

Output:

Identify critical technologies to enable new science missions

Establish roadmap for mid-term technology developments

SCI-A Technology Reference Studies




Key objective for solar system exploration:

Establish affordable mission concepts

TRS design philosophy

Cost-efficiency is achieved by:

• Medium-sized launch vehicle – Soyuz-Fregat

• Use of low resource spacecraft – typically ~200 kg (dry mass)

• Highly miniaturized, highly integrated payload and avionics suites

• When available proven, off the shelf, technology is baselined

• Identify promising and innovative technology that reduce resources

Technology Development: typically within 5

years

technically realistic assumptions




Venus Entry Probe Aerobot technology Microprobes

Deimos Sample Return & Near Earth-Asteroid Sample collection/investigation from a low gravity

body Direct Earth re-entry

Cross-scale Multi-spacecraft constellation Low resource spinners

Europa Minisat Explorer & Jupiter System Explorer Extreme radiation environment Use of solar power at 5 AU from the sun

Interstellar Heliopause Probe Extremely high delta-V (200 AU) Long lifetime

Geosail Solar sail demonstrator

Solar system studies overview




Cross-Scale / ObjectivesEstablish a feasible mission profile for the investigation of fundamental space plasma processes that involve non-linear coupling across multiple length scales

All three processes: Are dynamical Involve complex 3-D structured interaction between

different length scales (electrons, ions, MHD fluid) Can be investigated in near-Earth space

(bowshock, current sheet, magnetosheath)

The key universal space plasma processes are:

Reconnection Shocks Turbulence




Cross-Scale / Mission concept• 8 – 10 spacecraft to be launched with a single

Soyuz-Fregat 1 – 2 on electron scale: 2 – 100 km 4 on ion scale: 100 – 2,000 km 3 – 4 on large scale: 3,000 – 15,000 km

• Baseline orbit: 1.5 – 4 Re × 25 Re (near equatorial) < 100 krad in 5 y

• Spacecraft constellations optimized near apogee

• Dedicated transfer vehicle/dispenser system brings constellation to operational orbit

• Simple identical 130 kg spinners with ~30 kg P/L Individual data downlink Autonomous payload operation

Baseline solution

Cross-scale Technology Reference Study is work in progress




Study of the Jovian System (1)

1st study phase: Europa Exploration• Europa Orbiter: 30 kg P/L, 200 km polar

orbit • 1.5 year tour of the Galilean moons• In orbit life time ~ 60 days

(limited by radiation and perturbations)• TID: 1 Mrad (10 mm shield), 5 Mrad (4 mm

shield)

• Relay sat: 15 kg P/L, 11 Rj × 28 Rj Jupiter

orbit

• Equatorial Jupiter orbit achieved after 1.5

years• Operational lifetime ~2 years• TID: 1.5 Mrad (4 mm shield)

1st study phase: Europa Exploration• Europa Orbiter: 30 kg P/L, 200 km polar

orbit • 1.5 year tour of the Galilean moons• In orbit life time ~ 60 days

(limited by radiation and perturbations)• TID: 1 Mrad (10 mm shield), 5 Mrad (4 mm

shield)

• Relay sat: 15 kg P/L, 11 Rj × 28 Rj Jupiter

orbit

• Equatorial Jupiter orbit achieved after 1.5

years• Operational lifetime ~2 years• TID: 1.5 Mrad (4 mm shield)

• Launch with Soyuz-Fregat 2-1B • All-chemical propulsion / solar powered S/C• Transfer duration ~7 years

• Launch with Soyuz-Fregat 2-1B • All-chemical propulsion / solar powered S/C• Transfer duration ~7 years

Launchconfiguration

Europa orbiter

ONERA developed radiation model which combines:

Salammbô (2004), Divine & Garrett (1983) and Galileo Interim Radiation

Electron (2003)

ONERA developed radiation model which combines:

Salammbô (2004), Divine & Garrett (1983) and Galileo Interim Radiation

Electron (2003)




Study of the Jovian system (2)

Magnetospheric

orbiters:

• P/L: 40 kg, 40 W

• Equatorial orbit:

15 Rj × 70 Rj and/or

15 Rj × 200 Rj

• Operational lifetime:

at least 2 years

• TID:

< 1 Mrad (4 mm)

(TBD)

Magnetospheric

orbiters:

• P/L: 40 kg, 40 W

• Equatorial orbit:

15 Rj × 70 Rj and/or

15 Rj × 200 Rj

• Operational lifetime:

at least 2 years

• TID:

< 1 Mrad (4 mm)

(TBD)

2nd study phase: extended Jovian System

Exploration• Magnetosphere: 1 – 2 dedicated spinning

orbiter(s)• Atmosphere: 1 atmospheric entry probe

2nd study phase: extended Jovian System

Exploration• Magnetosphere: 1 – 2 dedicated spinning

orbiter(s)• Atmosphere: 1 atmospheric entry probe

Krupp et al. (2004)




• In-situ exploration of the outer heliosphere

• Interaction between heliosphere and local interstellar medium

o Termination shock, heliopause, hydrogen wall

o Plasma acceleration and heating processes

• Characterization of the local interstellar medium

o Plasma and plasma dynamics

o Neutral atoms

o Galactic cosmic rays

o Dust

Interstellar Heliopause Probe /ObjectivesMission concept for the exploration of the interface between the Heliosphere and the interstellar medium

From: http://interstellar.jpl.nasa.gov/interstellar




Interstellar Heliopause Probe / Mission concept• Launch with Soyuz-Fregat 2-1b• Solar sail propulsion system (245 × 245 m2)

Two solar photonic assist (closest approach 0.25 AU)

Solar sail jettisoned at 5 AU Flight time to 200 AU: 26 years (1 mm/s2)

• Radioisotopic power source (7 W/kg)

Spacecraft designItem Mass (kg)

Instruments 21

S/C 182

Sail assembly 249

Launch mass 431

Demonstration of solar sailpropulsion required




Solar sail demonstration by GeoSail

Sail size~40 × 40

m2

Characteristic acceleration

0.1 mm2/s

Sail assembly mass

~85 kg

Spacecraft mass ~85 kg

• Launch with VEGA from Kourou• Demonstration of solar sail propulsion

Sail deployment Sail AOCS Sail jettison

• Plasma measurements at 23 RE throughout the year Rotate line of apses 1 / day

GeoSail TRS: 11 x 23 Re

Spacecraft design parameters

GeoSail Technology Reference Study has recently started

1 deg/day




Conclusion

Sample of spacecraft technologies:• Enhanced Radiation Model for Jupiter (ONERA) –

finished• Jupiter LILT solar cells (RWE) - running• Solar Sail Material Development (TRP) – under ITT • Hi-Rad. Solar Cell development (TRP) – approval• Effective Shielding Methods for Jovian Radiation (TRP) -

approval

Technology Reference Studies are a tool for the identification of critical technologies:

Cross-scale• Spinning S/C with plasma physics instrumentation

Jovian system study• High radiation exposure tolerant systems (e.g. electronics,

solar cells)

Interstellar Heliopause Probe• Solar sailing, radio-isotopic power generation, long lifetime

systems

Cluster II




Questions?




Backup-slides




Cross-Scale / Orbit• 8 – 10 spacecraft to be launched with a single Soyuz-

Fregat 1 – 2 on electron scale: 2 – 100 km 4 on ion scale: 100 – 2,000 km 3 – 4 on large scale: 3,000 – 15,000 km

• Baseline orbit: 1.5 – 4 Re × 25 Re

• Spacecraft constellations optimized near apogee

Cross scale TRS baseline orbit 4 x 25 Re

• Constellation passes through bowshock, magnetosheath and magnetotail Perigee 1.5 – 4 Re Apogee 25 Re

• Constellations optimized near apogee

• Range of constellation length scales is sampled at least once




Tailbox Definition

• Q is 10 Re from the Earth’s centre in anti-sunward direction along the equatorial plane

• P (tailbox centre) is at 30 Re from the Earth’s centre with line Q-P parallel to the ecliptic plane

• The tailbox is defined as a rectangular box parallel to the ecliptic plane: 25 Re along Q-P line, extending 5 Re

tailward of P 4 Re orthogonal to the ecliptic plane

(+/-2 Re from the tailbox centre P) 10 Re parallel to the dawn-dusk

terminater (+/-5 Re from the centre P)




Jupiter radiation belt modelsDivine & Garrett (1983) from Jet Propulsion Laboratory (JPL) :

– empirical model based on Pioneer & Voyager in situ measurements, observations from Earth, theoretical formula

– with a good coverage in both space and energy – …but based on a restricted set of quite old data :

• empirical pitch-angle dependence and magnetic field model far from reality

GIRE -Galileo Interim Radiation Electron- (2003) from JPL :– update of D&G thanks to Galileo measurements– only concern electrons from 8 to 16Rj

Salammbô-3D (2004) from ONERA :– physical model derived from the Salammbô-3D code widely used

for Earth– global model with a coverage in space limited to 6-9Rj

A. Sicard and S. Bourdarie, Physical Electron Belt Model from Jupiter's surface to the orbit of Europa, JGR, V109, February 2004.




Jupiter radiation models / spatial coverage

6 12 169.5

Ele

ctro

nP

roto

n

Salammbô

8

GIRE

Salammbô

D&G 83

D&G in 83 D&G out 83

Spatial coverage

L




Jupiter radiation models / energy coverage

0.001 0.01 0.1 1 10 100 1000MeV

Ele

ctro

n

Salammbô

GIRE

D&G in and out 83

Energy coverage

Pro

ton

Salammbô

D&G 83




JME – Radiation Concerns4mm shielding 8mm shielding 10mm shielding 1MeV fluence

Jupiter tour 3170 kRad 805 kRad 350 kRad 1.35E+15 e-/cm²

per day around Europa 35 kRad 12 kRad 7 kRad 2.85E+13 e-/cm²

60 days around Europa 2100 kRad 720 kRad 420 kRad 1.71E+15 e-/cm²

Total 5270 kRad 1525 kRad 770 kRad 3.06E+15 e-/cm²

For Jupiter and Jovian MoonsRadiation environment requires:

• European Rad-Hard component program (electronics, solar cells also materials)

Ganymede = somewhat relaxed, but still very harsh !

Outer Planets Program Yes or No?Yes develop European RTG technology

no specific high radiation solar cell LILT development

No high radiation solar cell LILT development

JEO Radiation




Jupiter challenges

The Jupiter Explorer TRS addresses several challenges:

• Development of low resource minisats• Surviving deep space as well as Jupiter’s extreme radiation

environment:• Radiation hardened components (Radiation hardened components ( 1 Mrad) + radiation shielding 1 Mrad) + radiation shielding• Radiation optimised solar cells, totally new development requiredRadiation optimised solar cells, totally new development required

• Development of highly integrated systems (especially low resource radar)

• Maximise the use of solar power, even at ~5 AU from Sun• Low power deep space communication• Planetary protection compatible systems• LOW COST vs. investments in new developments




Terrestrial PlanetAstrometric Surveyor

Near Infrared Terrestrial Planet Interferometer

From exo-planets tobiomarkers

From 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)

Cross-scale

Helio-pause Probe(Solar Sailor)

Near Earth Asteroid sample & return

Far Infrared Interferometer

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

12

Cosmic Vision Themes 1 & 2 (solar system themes)

TRS

TRS

TRS

TRS

TRS

TRS

TRS




Cosmic vision themes 3 & 4 (fundamental physics and astrophysics)




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-SR

heritage




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 (60.000m2)

200 AU in 25 year

RTG based

GeoSail

SPO




Other Technology Reference Studies

Gamma-ray lensEvolving violent universe

500 m focal lengthGamma-ray focussing optics

Formation flying

Wide Field ImagerExpanding universe/Dark

energySoyuz-Fregat to L2

2m telescope with 1° FOVLight weight optical mirrors




Status / Overview

• Venus Entry Probe (VEP) finished

• Deimos Sample Return (DSR) finished

• Jovian Minisat Explorer (JME) finished

• Jupiter Entry Probe (JEP) finished

• Interstellar Heliopause Probe (IHP) finished

• Jupiter System Explorer (JSE) on-going

• Cross Scale (CS) on-going

• Near Earth Asteroid Sample Return on-going

• Solar Sail Demonstrator (GeoSail) on-going

• Solar Polar Orbiter sail GNC under study

2006 -

2003-0

5Sci-AP TRS status as of 10 November 2006




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 / Summary

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

Third European Space Weather Week, 13-17 November 2006 Page 1 Planetary Exploration Studies Section Science Payload & Advanced Concepts Office ESAs Technology.

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