1. space for science, enterprise and environment MoonLITE and LunarEX Rob Gowen and Alan Smith Mullard Space Science Laboratory, UCL PI Penetrator consortium

2. space for science, enterprise and environment Mullard Space Science Laboratory 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 Hinode Launch 22-9-06

3. space for science, enterprise and environment 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. space for science, enterprise and environment Consortium 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

5. space for science, enterprise and environment 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. space for science, enterprise and environment 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 Courtesy QinetiQ 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’!

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

8. space for science, enterprise and environment MoonLITE/LunarEX - Mission Description Delivery and Communications Spacecraft (Orbiter). Deliver penetrators to ejection orbit, provide pre-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. space for science, enterprise and environment 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. space for science, enterprise and environment MoonLITE/LunarEX – Mission Sequence Launch & cruise phase Deployment & descent Landed phase

11. space for science, enterprise and environment MoonLITE – Science The Origin and Evolution of Planetary Bodies NASA Lunar Prospector Water and its profound implications for life and exploration

12. space for science, enterprise and environment 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 NASA Lunar Prospector Prototype, ruggedized ion trap mass-spectrometer Open University

13. space for science, enterprise and environment Science - Seismology 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

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

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

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

17. space for science, enterprise and environment Key Technologies 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

18. space for science, enterprise and environment Penetrator Development Programme 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 Generic Mission Specific

19. space for science, enterprise and environment Current activities 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

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

21. space for science, enterprise and environment MoonLITE / LunarEX – UK Scientifically focussed Precursor to future penetrator programmes High public interest Impetus to industry Affordable Rationale

22. space for science, enterprise and environment 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