Rob Gowen and Alan Smith Mullard Space Science Laboratory, UCL PI Penetrator consortium
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Transcript of Rob Gowen and Alan Smith Mullard Space Science Laboratory, UCL PI Penetrator consortium
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space for science, enterprise and environment
MoonLITE and LunarEX
Rob Gowen and Alan SmithMullard Space Science Laboratory, UCL
PI Penetrator consortium
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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
Launch22-9-06
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• 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
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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
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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
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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’!
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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
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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.
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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.
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MoonLITE/LunarEX – Mission Sequence
• Launch & cruise phase• Deployment & descent• Landed phase
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MoonLITE – Science
The Origin and Evolution of Planetary Bodies
NASA Lunar Prospector
Water and its profound implications for life andexploration
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Science – Polar VolatilesA 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
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Science - SeismologyA 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
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Science - GeochemistryX-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
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Science – Heat Flow
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
NASA Lunar Prospector
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• 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)
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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
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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
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Current activitiesGeneric 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
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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
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MoonLITE / LunarEX – UK
• Scientifically focussed • Precursor to future
penetrator programmes• High public interest• Impetus to industry• Affordable
Rationale
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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