1. Landing on 67P/Churyumov- GerasimenkoDr. Jens Biele Philae Lander Payload Manager and Lander System Science, DLR CologneVLT 2014

2. 2Philae (Egypt) 3. FolLander FM Thermal-Vacuum Test at IABG, October 2001 4. Image: CIVA from 50 km 5. CIVA selfie from 20 km orbitstart : 2014/10/08 00:14:36, stop : 2014/10/08 00:18:47 (EOBT : 4298:00:13:26- 4298:00:17:36) 6. 6Schematic view of the Philae spacecraftN.B.: some instruments are not visible in the drawing: specifically, the instruments in charge of analyzing the samples distributed by the SD2 (CIVA, COSAC, PTOLEMY), and the down-looking camera (ROLIS). 7. 7Side view schematics of the inner structure of the lander compartment 8. 8Instruments - scientific goals10 instruments, including the drill (SD2), have been implemented, with the goal of: determining the composition (elemental, isotopic, mineralogic and molecular) of the cometary surface material; measuring the physical properties (thermal, electrical, mechanical) of the cometary surface material; describing the large scale structure (panoramic image, particles and field, and internal heterogeneity); monitoring the cometary activity;according to the next chart 9. 9Instruments - scientific goals1. CompositionElemental: APXS surfaceIsotopic : PTOLEMY, COSAC samplesMolecular : COSAC, CIVA-M, PTOLEMY samplesMineralogical : IVA-M samples2. Physical propertiesThermal : MUPUS, SESAME surface, subsurfaceElectrical: SESAME, CONSERT surface, globalMechanical: SESAME, SD2, MUPUS, ROLIS surface, subsurface3. Imaging and large scale structureImagery: IVA, ROLIS landing/drilling sitesMagnetic: ROMAP local, globalGas, Plasma: ROMAP, SESAME local, globalInternal structure: CONSERT global4. Cometary activityAll properties ALL INSTRUMENTS 10. Operational Sequences of LanderPre-DeliverySeparation Descent Landing (SDL)Landing will occur at a Sun distance of 3.0 AU and Earth distance of 3.4 AUTaking images during descent, plasma measurements, calibrationFirst Scientific Sequence (FSS)Based on primary battery with about 1000 WhAll instruments operated at least once within ~2.5 daysLong Term Science (LTS)Use of solar generator to recharge batteryOperate instruments (mainly sequentially) for weeks or monthsEventually, the Lander will die due to overheating or dust coverage on solar cells.12 11. 13 12. 14Eject and landingThe Rosetta Lander will separate from the Orbiter with an adjustable velocity of 0,05 to 0,52 m/s (used: 0.19 m/s) and will descend to the comets surface stabilised by an internal flywheel and upon touchdown by a cold gas thruster 13. Real lifeseparation from the orbiter is on November 12th, 8:35 (UTC) and landing 15:34 (UTC), so the first signal after landing may be expected at 17:00 (CET) the earliest.The elevation of the Sun at the landing site is 56.115 14. Descent operationsCIVA farewell images of Orbiter (direct uplink)ROLIS downlooking images DIT+DIS (some directly uplinked, some stored in ringbuffer, uplinked after TD)Consert sounding: range between Orbiter and Lander, proof that Lander is aliveMagnetometer scienceVarious calibrations of instruments and dust impact sensors running16 15. 17Harpoon Anchoring Device2 harpoons, accelerated by acartridge driven pistoninto surface material and con-nected by tensioned tetherto the Landers landing gear.Includes MUPUS accelerometers and temperature sensorsmass of unit: 400grewind velocity: 0.5 m/sanchor velocity: 60 m/srewind force(TBC): 1...30 Nmax. tether tension: 200 Nmax. gas pressure: 250 bar 16. Harpooning the comet 17. At and after touchdownTD signal triggers harpoon shooting (2 at ~ same time), ADS firing (hold-down thrust, 15N), rewind of anchor tethersTransition to post-landing operationsUplinkCIVA panoramic imagesROLIS downlooking imagesMagnetometerSolar generator housekeepingThe first data are used to assess the status of Philae and calculate the exact position and attitude on the surface19 LORR, October 14th, 2014, ESOC 18. Surprise: Comet by OSIRIS (early July) 19. Keep Fingers crossed! 20. Backup slides: LSS22 LORR, October 14th, 2014, ESOC 21. 23 LORR, October 14th, 2014, ESOCRLGS Landing Site Selection ProcessRLGS LSSP was part of the ESA Mission Level LSSP:RLGS has provided ESA with candidate landing site(s) meeting:Technical requirements RD2000, RD1000.Scientific criteria - RD3313ESA has verified that the candidate landing site(s) is (are) operationally feasible.A scenario to reach the selected site (J) is agreed between all parties involved!Key dates :Beginning of the process with first shape model delivered by OSIRISL-79 (24/08/.2014) : RLGS delivered to ESA 5 pre-selected landing sitesL-58 (14/09/2014) : RLGS delivered to ESA nominal and backup landing sitesL-33 (10/10/2014) : RLGS confirmed nominal landing siteLanding 12/11/2014. 22. 24 LORR, October 14th, 2014, ESOCRLGS Landing Site Selection ProcessPre-pre-selection of 10 feasible Landing areasPre-selection of Sites I, C (priorized) and J, A and BSince no O1 solution could be found for site C, sites C and J were swapped in prioritySite A showed high dispersion (and rough terrain), and was disregarded 23. 25 LORR, October 14th, 2014, ESOCRLGS Landing Site Selection ProcessSelection of nominal (J) and backup (C) sites:Site J was selected due to good illumination, good reachability (7hrs descent with O1 scenario), its relatively flat terrain, and good conditions for CONSERTAs backup site C (O2) was selected against B, due to better illumination and much lower number of boulders.Site I (after more detailed analyses, and the availability of high res images) turned out to have a very Lander-unfriendly terrain. Descent time would have been about 10hrs. 24. 26 LORR, October 14th, 2014, ESOCRLGS Landing Site Selection ProcessFinal step of RLGS LSSP confirmed site J as desired landing siteNO Landing site is flat within the complete landing ellipseThere are boulders in all sitesLanding will be risky!Completely new strategies (like waiting till May 2015 and consider landing at sole) were thought of , but disregarded 25. Folie 27 > 26. 29 LORR, October 14th, 2014, ESOCRLGS Landing Site Selection ProcessBoulder statisticsProbability to land on boulder: 17.8%Percentage of landing ellipse free of boulders: 98,3% 27. Topography and slopes (site J)30OSIRIS DTMRMOC global DTM 28. Solar illumination: site J31 LORR, 14. Oct 2014 29. 32Slope- and Illumination Statistics (site J)20% of the area with slope > 30 5% wit > 4595% of the area with sun illumination > 6hr/rotation