third european space weather week, 13-17 november 2006 page 1 planetary exploration studies section...
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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
Third European Space Weather Week, 13-17 November 2006 Page 2
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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
Third European Space Weather Week, 13-17 November 2006 Page 3
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s 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
Third European Space Weather Week, 13-17 November 2006 Page 4
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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
Third European Space Weather Week, 13-17 November 2006 Page 5
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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
Third European Space Weather Week, 13-17 November 2006 Page 6
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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
Third European Space Weather Week, 13-17 November 2006 Page 7
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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)
Third European Space Weather Week, 13-17 November 2006 Page 8
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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)
Third European Space Weather Week, 13-17 November 2006 Page 9
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
• 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
Third European Space Weather Week, 13-17 November 2006 Page 10
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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
Third European Space Weather Week, 13-17 November 2006 Page 11
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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
Third European Space Weather Week, 13-17 November 2006 Page 12
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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
Third European Space Weather Week, 13-17 November 2006 Page 13
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
Questions?
Third European Space Weather Week, 13-17 November 2006 Page 14
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
Backup-slides
Third European Space Weather Week, 13-17 November 2006 Page 15
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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
Third European Space Weather Week, 13-17 November 2006 Page 16
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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)
Third European Space Weather Week, 13-17 November 2006 Page 17
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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.
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Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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
Third European Space Weather Week, 13-17 November 2006 Page 19
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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
Third European Space Weather Week, 13-17 November 2006 Page 20
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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
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Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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
Third European Space Weather Week, 13-17 November 2006 Page 22
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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
Third European Space Weather Week, 13-17 November 2006 Page 23
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
Cosmic vision themes 3 & 4 (fundamental physics and astrophysics)
Third European Space Weather Week, 13-17 November 2006 Page 24
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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
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Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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
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Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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
Third European Space Weather Week, 13-17 November 2006 Page 27
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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
Third European Space Weather Week, 13-17 November 2006 Page 28
Planetary Exploration Studies SectionScience Payload & Advanced Concepts Office
ESA’s Technology Reference Studies
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