MARCO POLO COSMIC VISION MISSION A NEAR-EARTH OBJECT SAMPLE RETURN

1. MARCO POLO COSMIC VISION MISSION A NEAR-EARTH OBJECT SAMPLE RETURN ILMA PROJECT CORE TEAM (Ion Laser Mass Analyser) Hervé Cottin, Noel Grand, LISA Cécile Engrand, CSNSM Christelle Briois, Laurent Thirkell, CBM A. Glasmachers, U. Wuppertal

2. NEO Sample Return « Marco Polo » The main scientific objective of the MARCO POLO mission is to return unaltered NEO materials. MARCO POLO will allow us to analyze the samples in terrestrial laboratories, thereby obtaining measurements that cannot yet be performed from a robotic spacecraft. (e.g. dating the major events in the history of a sample: laboratory techniques can determine the time interval between the end of nucleosynthesis and agglomeration, the duration of agglomeration, time of accumulation, crystallization age, the age of major heating and degassing events, the time of metamorphism, the time of aqueous alteration, and the duration of exposure to cosmic radiation).

3. Matter of our natal molecular could Destruction of pristine matter Conservation of pristine matter ? Incorporation to the Sun, planets, molecules pyrolysis, sublimation and recondensation of ices, new synthesis Incorporation into comets ? in gaseous or condensed phase… Extension of the convection / mixing by turbulence Icy planetesimals Rocky planetesimals Kuiper ………… Oort ? Formation of asteroids Formation of comets Gradient in composition Pristine or differentiated

4. Orbits of the 100 largest NEOs NEAR EARTH OBJECTS Observed (2007) : ~ 4500 Total Population Estimated : More than 1000 > 1.0 km Hundred thousands > 0.1 km

7. Dimensions : 540 × 270 × 210 meters Mass~4.8×1010 kg Density2.0±0.3 g/cm³ Surface gravity ~0.0001 m/s² Escape velocity ~0.0002 km/s Rotation period : 0.5055 d (12.5 h) Spectral class : S Absolute magnitude : 19.2 Albedo : 0.53 Mean surfacetemperature~206 K Astéroïde (25143) Itokawa

9. LES FAMILLES DE METEORITES Météorites metalliques (sidérites) Plus de 90 % d’alliage Fer-Nickel 4% des météorites collectées, 90% de la masse • Météorites métallo-pierreuses (mixtes) • de 35 à 90% d’alliage Fer-Nickel • 1% des météorites collectées • Mésosidérites • Pallasites • Pierreuses • Moins de 35% de métal • 95% des météorites collectées • Chondrites(86%) • Ordinaires (81%) • Carbonnées (5%) • Achondrites (9%)

10. Moins dense (silicates, etc.) Dense (métaux) L’intérieur fond : pression de gravitation, radioactivité, Différenciation Grand planétésimal Des corps > 2000 km se forment en moins d’1 million d’années Corps parent fragmenté par collision Corps parent des météorites

11. NEO Sample Return Mission « Marco Polo » This proposal, prepared by a joint European Japanese team, is supported by 436 confirmed scientists. • Mission name : MARCO POLO • For the first time in Europe returned news about the existence of Japan (Cipango). • Lander name : SIFNOS • one of the Greek Cycladic Islands, cradle of European civilization, settled by an Asian population in 3000 B.C. • Both names testify to the long standing relationship between far eastern Asian and western European cultures.

12. European-Japanese collaboration (Heritage Hayabusa)- M.A. Barucci (LESIA, Paris Observatory, F) - M. Yoshikawa (JSPEC/JAXA, J) • Core members : • Europe : • P. Michel (OCA, Nice F) • J. Brucato (INAF, Naples I) • I. Franchi (Open University, UK) • E. Dotto (INAF, Rome I) • M. Fulchignoni (Univ. Paris Diderot, F) • S. Ulamec (DLR, Koln D) • Japan : • J. Kawagushi (JSPEC/JAXA) • H. Yano (JSPEC/JAXA, Japan) • USA : • R.P. Binzel (MIT, Cambridge, USA) COSMIC VISION ESA is currently carrying out an Assessment study Phase for the Marco Polo mission as a candidate for the “M1” launch slot in the Cosmic Vision plan, with a possible launch at the end of 2017. All currently studied M mission concepts will undergo a competitive selection at the end of 2009, from which 2 missions (out of the 4 currently under study) will be selected for Definition studies extending to the end of 2011. Eventually, only one mission will be adopted for flight with the industrial Implementation phase starting in 2012.

13. MAINS OBJECTIVES • Determine the physical and chemical properties of the target body, which are representative of the building blocks of the terrestrial planets. • 2. Identify the major events (e.g. agglomeration, heating, aqueous alteration, solar wind interactions …) which influenced the history of the target. • 3. Determine the elemental and mineralogical properties of the target body and their variations with geological context on the surface. • 4. Search for pre-solar material yet unknown in meteoritic samples. • 5. Investigate the nature and origin of organic compounds on the target body. • 6. Search for organic compounds which may shed light on the origin of pre-biotic molecules. • 7. Understand the role of minor body impacts in the origin and evolution of life on Earth.

14. MEASUREMENTS • morphological surface properties; • environment conditions (e.g. dust, gravity field…); • mass, volume and bulk density; • mineralogical composition; • surface (and possibly subsurface) mineralogy and thermophysical properties (thermal inertia, conductivity, diffusivity, cohesion of the materials….); • surface elemental composition and distribution; • overall internal structure properties; • global topography; • volatile abundance.

15. Optionalmeasurements The science return will be significantly enhanced by the following in situ measurements (which will also offer some scientific redundancy to the key sample collection/return aspects of the mission): • microscopic morphology; • bulk composition (chemical characterization of close-by samples); • mineralogical and chemical composition (elements, isotopes, molecules) of in situ samples;

17. TARGETS A number of possible targets of high scientific interest has been selected and covers a wide spectrum of possible launch windows in the time span 2016-2019, namely : • the dormant comet 4015 Wilson-Harrington (1979 VA), which can give insides on the unknown link between asteroids and comets; • asteroids which belong to the primitive D-type, e.g. 2002 AT4, 2001 SG286; • the primitive C-type double asteroid 1996 FG3, which can provide insight into binary formation processes.

19. A joint ESA/JAXA Mission The baseline mission scenario to 4015 Wilson-Harrington includes a launch with a Soyuz-type launcher of a Mother Spacescraft (provided by JAXA) carrying a Lander, named Sifnos (ESA), sampling devices (ESA and JAXA), a re-entry capsule (ESA and JAXA) and scientific payloads (shared between JAXA and Europe).

20. Why a sample return? Asteroids families are rather well characterized, divided into different classes according to their optical properties. On the other hand, many meteorites have been analyzed in the laboratory. But only the inner part of meteorites survives the impact (~90 % lost during atmospheric entry – incl. their outer surface) It is important to link asteroid to meteorites (Formation of the Solar System, Origin of Life) -> study of an asteroid sample (NEO) with the same tools than for meteorites

21. POSSIBLE MISSION SCENARIOS WITH AN INDICATION OF INCREASING/DECREASING COSTS option 1 (baseline): MSC, 2 touch & go sampling devices, Lander, re-entry capsule; option 2: MSC, 2 touch & go sampling devices, Lander, subsurface driller on the Lander, re-entry capsule; option 3: Lander/Earth return vehicle, core driller, re-entry capsule; option 4: MSC, 2 touch & go sampling devices, (no Lander) re-entry capsule. Options 3 and 4 provide lower cost mission alternatives for meeting the major scientific goals, but these alternatives are below the full potential scientific return of MARCO POLO.

22. A BASELINE MARCO POLO MISSION SCENARIO TO 4015 WILSON-HARRINGTON

23. Baseline Marco Polo to 4015 Wilson-Harrington Launcher : Soyuz Fregat (indirect injection) MSC total mass 1320 kg Payload + capsule : 200 kg Lander : 100 kg (9 kg science) Cost : 250 M€ ESA + 300 M€ JAXA (+40 M€ for SR)

24. POSSIBLE MISSION SCENARIOS FOR THE OTHER THREE TARGET CANDIDATES

25. JAXA ESA MARCO POLO MISSION Baseline scenario (Option 1) mapping cruise phase sampling system landingand sampling ERC spacecraft sciencephase Lander NEO propulsionmodule TTC relay remote sensingpackage in situanalyses Launch re-entryphase Earth Operations return phase

26. (The Second Descent: Touch & Go Sampling) (The First Descent: Lander Release) (2) ESA Lander • Arm Extended (2) Target Marker #2 • Target Marker #1 Asteroid Surface (3) Touch Down & Sampling with Shock Absorption with Joints Asteroid Surface Lander : Philae heritage

27. (Modified Spacecraft Configuration for Sub-surface Sampling by Lander) Earth Return Capsule Volume for Bio-Sealing ESA Lander Canister Catcher Target Markers Canister Catcher Lander Sample Canister Spacecraft Samplers Retracted Canister Ejection Mechanism ESA Lander Sub-surface Drill Asteroid Surface (“Catch-Ball” Operation) (Option 2)

28. PAYLOAD

29. ILMA – Ion Laser Mass Analyser ILMA is a SIMS (Secondary Ion Mass Spectrometry) instrument based on a quadrupole ion trap mass spectrometer. Ions are extracted from the sample through primary ions bombardment. Secondary ions are stored with hyperbolic electrical field and their masses are determined non-destructively by the measurement of their frequency in the trap. High mass resolution (about 10,000) can be achieved using this analytical setup. and/or Laser

30. ILMA – Ion Laser Mass Analyser • Quantitative analysis for major constituents (including C) and small molecules such as H2O • Qualitative analysis of larger molecules (organic, inorganic) and identification by exact mass measurement • Isotopic analysis (performances under study) • Mass resolution: 10,000 (at 40 amu) • Mass range 1-300 • Weight: 2-3 kg • Dimensions: 5*17*15 cm3 • Power consumption: 1.5 watts • Area analysed: 1 mm2 • Mass spectrometer: Quadripolar ion trap. • Measurement of ion mass by non-destructive charge influence • Analysis can be performed by moving the instrument to the sample surface, or by moving the sample to the mass spectrometer.

31. ILMA and the study of the formation of the Solar System ILMA analyses will allow comparing the asteroid's composition with that of meteorites recovered on Earth. This should constrain the genetic link between asteroid types and meteorite classes. Measuring the main element chemical composition, as well as selected isotopic compositions (H, C, N, O, Si,…) of the asteroid with ILMA would also place constraints on the early evolution of the protostellar disk. Recent analyses of cometary samples returned by the STARDUST mission, as well as astronomical observations of objects presenting a cometary activity in the outer asteroid belt (e.g. Phaeton) also suggest the possibility of a continuum between asteroidal and cometary material. Analyses performed on a carbonaceous asteroid would help understand the structure and repartition of interplanetary material nowadays, helping retracing the formation and evolution of the solar system, 4.5 billion years ago. ILMA isotopic analyses could identify material with possible presolar interstellar heritage in the asteroid. The abundance of such interstellar material presolar material in a carbonaceous asteroid, compared to that found in meteorites, can help better understand the composition and astrophysical setting of the molecular cloud that gave birth to our solar system.

32. ILMA and the study of the origin of life Origin of water on Earth : measurement of D/H ratio in water Nature of organic component : - Measurements of D/H and C/H ratios in surface material can relate the composition of the organic component to the different family of H-bearing material found in meteorites, and relate the analyzed NEO to meteoritic well characterized material. - If drilling device : access to more pristine material. Maybe access to molecular structure of material protected from space alteration

33. CONCLUSIONS A project in its early stage (mission and instrument ILMA) A lot can be expected, and a lot can still change since ILMA is still in its early development phase More details about the instrument tomorrow with L. Thirkell. Earth as seen from NEA TOUTATIS, 29/9/2004, 1.5 million km from Earth