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Rob Gowen and Alan Smith Mullard Space Science Laboratory, UCL PI Penetrator consortium

MoonLITE and LunarEX. Rob Gowen and Alan Smith Mullard Space Science Laboratory, UCL PI Penetrator consortium. A department of University College London Established in 1967 >200 sounding rockets and >35 satellite missions 150 Staff and research students

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Rob Gowen and Alan Smith Mullard Space Science Laboratory, UCL PI Penetrator consortium

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  1. MoonLITE and LunarEX Rob Gowen and Alan Smith Mullard Space Science Laboratory, UCL PI Penetrator consortium

  2. A department of University College London Established in 1967 >200 sounding rockets and >35 satellite missions 150 Staff and research students Provided hardware or calibration facilities for 16 instruments on 14 spacecraft currently operating including NASA Swift, Cassini, Soho In-house mechanical and electrical engineering design, manufacture and test Provided stereo cameras for Beagle-2 Leading PanCam development for EXOMARS Mullard Space Science Laboratory Hinode Launch 22-9-06

  3. Birkbeck College London Lunar Science (Ian Crawford) Open University Large academic planetary group (Cassini Huygens Probe) Science and instrumentation(Ion trap spectrometer, etc) Imperial College London Micro-Seismometers Surrey Space Science Centre and SSTL Platform technologies, delivery system technologies Payload technologies (drill) Consortium

  4. Southampton University Optical fibres University of Leicester XRS (beagle2/Mars96) Aberystwyth Science (Chandrayaan-1) QinetiQ Impact technologies Platform &delivery systems technologies Astrium (in discussion) Platform &delivery systems technologies Consortium

  5. What are Penetrators ? • Instrumented projectiles • Survive high speed impact ~ 300 m/s • Penetrate surface ~ few metres • An alternative to soft landing • Lower cost and low mass => multi-site deployment

  6. Penetrator Heritage • Lunar-A – tested but not yet flown • DS-2 – tested but failed at Mars • Mars-96 – lower speed impact, tested but failed to leave Earth Orbit • Innumerable ground trials of instrumented shells • Validated impact modelling tools When asked to describe the condition of a probe that had impacted 2m of concrete at 300m/s a UK expert described the device as ‘a bit scratched’! Courtesy QinetiQ

  7. Penetrator Design Concept • Payload • IMPACT ACCELEROMETER • SEISMOMETERS/TILTMETER • WATER/VOLATILES (ISRU DETECTION) • GEOCHEMISTRY • HEAT FLOW • DESCENT CAMERA • Platform • S/C SUPPORT • AOCS • STRUCTURE • POWER/THERMAL • COMMS • CONTROL & DATA • HANDLING DETACHABLE PROPULSION STAGE POINT OF SEPARATION PAYLOAD INSTRUMENTS PENETRATOR DESCENT MODULE • ESTIMATED PENETRATOR SIZE • LENGTH: ~50cm • DIAMETER: ~15cm • MASS: ~10-13Kg

  8. MoonLITE/LunarEX - Mission Description • Delivery and Communications Spacecraft(Orbiter).Deliver penetrators to ejection orbit, providepre-ejection health status, and relay communications. • Orbiter Payload: 4 Descent Probes (each containing 10-15 kg penetrator + 20-25 kg de-orbit and attitude control). • Landing sites: Globally spaced Far side, Polar region(s), One near an Apollo landing site for calibration. • Duration: >1 year for seismic network. Other science does not require so long (perhaps a few Lunar cycles for heat flow and volatiles much less). • Penetrator Design: Single Body for simplicity and risk avoidAnce. Battery powered with comprehensive power saving techniques.

  9. MoonLITE/LunarEX – Mission Sequence • Launch & cruise phase • Deployment • Deploy descent probes from lunar orbit, using a de-orbit motor to achieve near vertical impact. • Attitude control to achieve orientation of penetrator to be aligned with velocity vector. • Penetration ~3 metres • Camera to be used during descent to characterize landing site • Telemetry transmission during descent for health status • Impact accelerometer (to determine penetration depth & regolith mechanical properties) • Landed Phase • Telemeter final descent images and accelerometer data • Perform and telemeter science for ~1year.

  10. MoonLITE/LunarEX – Mission Sequence • Launch & cruise phase • Deployment & descent • Landed phase

  11. The Origin and Evolution of Planetary Bodies MoonLITE – Science Waterand its profound implications for life andexploration NASA Lunar Prospector

  12. Science – Polar Volatiles A suite of instruments will detect and characterise volatiles (including water) within shaded craters at both poles • Astrobiologically important • possibly remnant of the orginal seeding of planets by comets • May provide evidence of important cosmic-ray mediated organic synsthesis • Vital to the future manned exploration of the Moon Prototype, ruggedized ion trap mass-spectrometer Open University NASA Lunar Prospector

  13. A global network of seismometers will tell us: Size and physical state of the Lunar Core Structure of the Lunar Mantle Thickness of the far side crust The origin of the enigmatic shallow moon-quakes The seismic environment at potential manned landing sites Science - Seismology

  14. Science - Geochemistry Leicester University X-ray spectroscopy at multiple, diverse sites will address: • Lunar Geophysical diversity • Ground truth for remote sensing XRS on Beagle-2 K, Ca, Ti, Fe, Rb, Sr, Zr

  15. Heat flow measurements will be made at diverse sites, telling us: Information about thecomposition and thermal evolution of planetary interiors Whether the Th concentration in the PKT is a surface or mantle phenomina Science – Heat Flow NASA Lunar Prospector

  16. Payload • Core • Seismology • Water and volatile detection • Accelerometer • Desirable • Heat Flow • Geochemistry/XRF • Descent camera • Mineralogy • Radiation Monitor Ion trap spectrometer (200g, 10-100amu) (Open University)

  17. Batteries – Availability (Lunar-A) Communications – A trailing antenna would require development Structure material (Steel or Titanium, carbon composite under consideration) Sample acquisition Thermal control (RHUs probably needed for polar penetrators) AOCS (attitude control and de-orbit motor) Spacecraft attachment and ejection mechanism Key Technologies

  18. Phase 1: Modelling (until Jan 2008) Key trade studies (Power, Descent, Structure material, Data flow, Thermal) Interface & System definition Penetrator structure modelling Procurement strategy Phase 2: Trials (until Jan 2010) Payload element robustness proofing Penetrator structure trials Payload selection and definition Baseline accommodation Phase 3: EM (until Jan 2012) Design and Qualification Phase 4: FM (until Jan 2013) Flight build and non-destructive testing Penetrator Development Programme Generic Mission Specific

  19. Generic penetrator development Funded (>£600k) under MSSL rolling grant Started in earnest in April 07 Full-scale trials March 2008 National Programme MoonLITE Research Council commissioned a mission study by SSTL (delivered in Late 2006) Proposed as national mission under current ‘Comprehensive Spending Review’. Indications expected in October/December 2007 NASA/BNSC bi-lateral study ESA Cosmic Visions Programme LunarEX (backed by industrial studies) Jupiter-Europa Titan-Enceladus Current activities

  20. Penetrator website: http://www.mssl.ucl.ac.uk/planetary/missions/Micro_Penetrators.php Conclusions MoonLITE - A focused mission with clear objectives based on a strong technology background

  21. MoonLITE / LunarEX – UK Rationale • Scientifically focussed • Precursor to future penetrator programmes • High public interest • Impetus to industry • Affordable

  22. Examples of hi-gee electronic systems Designed and tested : • Communication systems • 36 GHz antenna, receiver and electronic fuze tested to 45 kgee • Dataloggers • 8 channel, 1 MHz sampling rate tested to 60 kgee • MEMS devices (accelerometers, gyros) • Tested to 50 kgee • MMIC devices • Tested to 20 kgee • TRL 6 MMIC chip tested to 20 kgee Communication system and electronic fuze tested to 45 kgee

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