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

1. ESA’s Technology Reference Studies: From 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

2. SCI-A 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

3. TRS design philosophy • Key objective for solar system exploration: • Establish affordable mission concepts • 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

4. Jovian Minisat Explorer TRS Solar system studies overview 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

5. Reconnection Shocks Turbulence Cross-Scale / Objectives • Establish a feasible mission profile for the investigation of • fundamental space plasma processes that involve • non-linear coupling across multiple length scales • The key universal space plasma processes are: • 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)

6. 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 Cross-Scale / Mission concept Baseline solution • 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 • Cross-scale Technology Reference Study is work in progress

7. Study of the Jovian System (1) • Launch with Soyuz-Fregat 2-1B • All-chemical propulsion / solar powered S/C • Transfer duration ~7 years • 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) Launchconfiguration Europa orbiter • ONERA developed radiation model which combines: • Salammbô (2004), Divine & Garrett (1983) and Galileo Interim Radiation Electron (2003)

8. Study of the Jovian system (2) • 2nd study phase: extended Jovian System Exploration • Magnetosphere: 1 – 2 dedicated spinning orbiter(s) • Atmosphere: 1 atmospheric entry probe • Magnetospheric orbiters: • P/L: 40 kg, 40 W • Equatorial orbit:15 Rj × 70 Rjand/or15 Rj × 200 Rj • Operational lifetime:at least 2 years • TID: < 1 Mrad (4 mm) (TBD) Krupp et al. (2004)

9. Interstellar Heliopause Probe /Objectives • Mission concept for the exploration of the interface • between the Heliosphere and the interstellar medium • In-situ exploration of the outer heliosphere • Interaction between heliosphere and local interstellar medium • Termination shock, heliopause, hydrogen wall • Plasma acceleration and heating processes • Characterization of the local interstellar medium • Plasma and plasma dynamics • Neutral atoms • Galactic cosmic rays • Dust From: http://interstellar.jpl.nasa.gov/interstellar

10. 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 design • Demonstration of solar sail • propulsion required

11. Solar sail demonstration by GeoSail • 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 1 deg/day GeoSail TRS: 11 x 23 Re Spacecraft design parameters • GeoSail Technology Reference Study has recently started

12. Conclusion • 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 • 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

13. Questions?

14. Backup-slides

15. 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 / Orbit • 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 Cross scale TRS baseline orbit 4 x 25 Re

16. 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)

17. Divine & 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 belt models

18. Jupiter radiation models / spatial coverage Spatial coverage D&G out 83 D&G in 83 GIRE Electron Salammbô L 6 8 9.5 12 16 Salammbô Proton D&G 83

19. Jupiter radiation models / energy coverage Energy coverage D&G in and out 83 GIRE Electron Salammbô MeV Proton Salammbô D&G83

20. JME – Radiation Concerns JEO Radiation • For Jupiter and Jovian Moons • Radiation 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

21. Development of low resource minisats Surviving deep space as well as Jupiter’s extreme radiation environment: Radiation hardened components ( 1 Mrad) + radiation shielding Radiation 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 Jupiter challenges The Jupiter Explorer TRS addresses several challenges:

22. Cosmic Vision Themes 1 & 2 (solar system themes) How does the Solar System work ? What are the conditions for life & planetary formation ? 2 1 TRS Solar-Polar Orbiter (Solar Sailor) From the sun to the edge of the solar system From dust and gas to stars and planets Far Infrared Interferometer Helio-pause Probe (Solar Sailor) TRS TRS Cross-scale Jupiter Magnetospheric Explorer (JEP) TRS The Giant Planets and their environment From exo-planets to biomarkers TRS Jovian In-situ Planetary Observer (JEP) Near Infrared Terrestrial Planet Interferometer TRS Europa Orbiting Surveyor (JEP) Asteroids and small bodies Life & habitability in the solar system Kuiper belt Explorer Mars In-situ Programme (Rovers & sub-surface) TRS Near Earth Asteroid sample & return Mars sample and return Terrestrial Planet Astrometric Surveyor Looking for life beyond the solar system Terrestrial-Planet Spectroscopic Observer

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

24. TRS Studies VEP DSR heritage NEA-SR  Deimos Sample Return SF-2B launch 1 kg surface material direct Earth re-entry  Near Earth Asteroid - SR SF-2B Sample return with direct Earth re-entry potential surface & remote sensing investigations Venus Entry Probe SF-2B launch Entry-Probe with Aerobot (floating ~55 km) Atmospheric MicroProbes (15) Atmospheric Orbiter

25. IHP TRS Studies – Solar Sailing SPO GeoSail Interstellar Heliopause Probe SF-2B launch solar sail based (60.000m2) 200 AU in 25 year RTG based • GeoSail • Solar Sail demonstrator • 40 x 40 m2 Sail Size • Rotate line of apsides 1º / day • Small S/C and Technology P/L • Solar Polar Orbiter • Solar Sail based • @ 0.48 AU (3:1 resonance) • Max inclination 83° • 5 year cruise time • ~40 kg P/L mass

26. Other Technology Reference Studies • Gamma-ray lens • Evolving violent universe • 500 m focal length • Gamma-ray focussing optics • Formation flying • Wide Field Imager • Expanding universe/Dark energy • Soyuz-Fregat to L2 • 2m telescope with 1° FOV • Light weight optical mirrors

27. Status / Overview Sci-AP TRS status as of 10 November 2006 • 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 2003-05 2006 -

28. TRS Technologies / Summary • 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 • 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