Spin-off Rosetta Lander for Marco Polo
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1 Spin-off Rosetta Lander for Marco Polo S. Ulamec, J. Biele DLR, Cologne, Germany
2 The Rosetta Lander Philae is the first ever built device to land on a comet Rosetta was launched 2004; landing is planned for 2014 Many aspects for landing on Rosetta s target comet also apply for the Marco Polo Mission! Folie 2 > Vortrag > Autor
3 Conditions when landing on Small Bodies Low gravity Impact velocity can be chosen small Rebounce needs to be minimized Anchoring to be considered Uncertainty regarding surface properties Wide range of surface strength to be considered Local slopes may be steep Dust ice gas-jets Usually not spherical wobbling potatoes Rotation may be chaotic Day night cycle at landing site not trivial to be estimated Complex descent analysis necessary Folie 3 > Vortrag > Autor
4 Areas for possible Spinoff Landing strategy Eject Mechanism (from mother S/C) Anchoring Payload Communications system (S-Band) Operations concept Power / Thermal concept (tbc) Folie 4 > Vortrag > Autor
5 Daktyl (NASA/Galileo) Ida (NASA/Galileo) Mathilde (NASA/NEAR) Wild 2 (NASA/Stardust) Phobos (ESA/MEX) Gaspra (NASA/Galileo) Eros (NASA/NEAR) Land h ere Wilson Harrington Tempel 1 (NASA/Deep Impact) Churyumov-Gerasimenko Wirtanen 1989 UQ Itokawa (JAXA/Hayabusa)) Folie 5 > Vortrag > Autor
6 Target: Comet 67P/Churyumov-Gerasimenko Discovered by Klim Churyumov in photographs of 32P/Comas Solá taken by Svetlana Gerasimenko on 22 October Characteristica: Diameter ~4000 m Density gcm -3 Aphelion 5.75 AU Perihelion 1.3 AU Orb.period 6.57 years Albedo Rotation h latest Perihelion: August 2003 Folie 6 > Vortrag > Autor
7 Scientific Objectives of the Lander In-situ-analysis of original material of the Solar System Elemental and isotope composition Organic molecules Minerals and ices Structure and physical properties of the nucleus Surface topology Physical properties Stratigraphy, global internal structure Observation of variations with time Day-night cycle Approach to the Sun Folie 7 > Vortrag > Autor
8 Lander Characteristica Landing system Damping of landing Rotation and hight adjustment Anchoring with harpune Hold-down Thruster Energy- und Thermal-Concept Solar generator 11 W (at 3AU) Primary and secondary batteries warm and cold areas Drill /Sampling Device Drill depth 20 cm multiple sampling low temperature modifications Data Central computer Data relay via Orbiter (16 kb/s) Folie 8 > Vortrag > Autor
9 Lander FM Thermal-Vacuum Test at IABG, October 2001 Folie 9 > Vortrag > Autor
10 Landing Scenario Separation from the Orbiter Orbiter Descent (gravity) Activation of cold gas system (optional) ROSETTA Orbiter Attitude control with flywheel Soft landing Fixation to ground v or,sep ²v 1 v 0,lan v rot,com et Ejection maneuver Folie 10 > Vortrag > Autor
11 Scientific Instruments Material Analysis COSAC (MPS) MODULUS (OU) APX (MPCh/Uni Mainz) Cameras ÇIVA (IAS) ROLIS (DLR) Structure SESAME (DLR) CONSERT (LPG) MUPUS (U. Münster/DLR) Plasma/Magnetic Environment ROMAP (TU Braunschweig) Sampling & Drilling Device SD 2 (Politecnico Milano) Folie 11 > Vortrag > Autor
12 Harpoon Anchoring Device Folie 12 > Vortrag > Autor
13 Eject Mechanism Separation Δv, adjustable between 5 and 52 cm/s Accuracy 1% (1s) Emergency release (spring) Developed by MPAe/MPS Folie 13 > Vortrag > Autor
14 Separation Test Separation Test with Lander FM Performed at ESTEC, March 2002 Movie by MPAe/MPS Folie 14 > Vortrag > Autor
15 Lander Operations For the Rosetta Lander there is a dedicated Lander control Center (LCC) at DLR (MUSC) Operations are performed via ESOC (Darmstadt and together with the SONC (Science Ops and Navigation Center) at CNES in Toulouse. The LCC is successfully operating the Lander since launch during all commissioning, test and checkout phases A similar approach is recommended for future Small bodies Lander missions Folie 15 > Vortrag > Autor
16 Mars Swingby 2007: Some results Closest Approach: km CIVA deliveres spectacular images ROMAP detects Bow Shock CIVA/Philae/ESA Folie 16 > Vortrag > Autor
17 Various alternative Lander strategies Impactor / Penetrator Classical Lander with landing legs or platform (e.g. Philae, Phobos) Hopper (e.g. Phobos Hopper) Opening shell (derivative from Mars Netlander) Orbiter Landing (e.g. Hayabusa) Folie 17 > Vortrag > Autor
18 Earth Return Capsule Volume for Bio-Sealing ESA Lander Canister Catcher Target Markers Marco Polo with Sifnos (possible Concept..) Canister Ejection Mechanism Canister Catcher Lander Sample Canister ESA Lander Spacecraft Samplers Retracted Sub-surface Drill Asteroid Surface Folie 18 > Vortrag > Autor
19 Options to be considered e.g for Marco Polo Sifnos Minerva-Type Lander ~ 35 kg Lander with about 5-7 kg of payload (short lived) ~ 45 kg Lander with about 7-9 kg of payload (semi-long lived [weeks]) ~ 100 kg Lander with about 25 kg payload (long lived, Philae-like) Payload needs to emphasize on: In situ characterization of the local environment at the sampling area Characterize samples in-situ to quantify modifications during return Allow large scale measurements (e.g. global sounding) Folie 19 > Vortrag > Autor
20 Conclusions Landers on Asteroids (or Comets) allow essential measurements, even in case of a Sample Return Mission There is significant heritage in Europa for the development of a Small Bodies Lander; namely Philae Particular areas for Spin-off are: Landing scenario Anchoring Eject Mechanism Payload elements (incl. drill) Thermal and Power design Operations concept Folie 20 > Vortrag > Autor
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