Royal Astronomical Society, January 11, 2008 MoonLite a UK led penetrator mission to the Moon...
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Royal Astronomical Society, January 11, 2008
MoonLite MoonLite a UK led penetrator mission to the Moona UK led penetrator mission to the Moon
Professor Alan SmithProfessor Alan SmithOn behalf of the UK Penetrator On behalf of the UK Penetrator
ConsortiumConsortium
Kaguya
Royal Astronomical Society, January 11, 2008
What Characterizes What Characterizes Penetrators ?Penetrators ?
Low mass instrumented packages Low mass instrumented packages (c.f. Lunar A 13.5Kg; DS-2 3.6Kg) (c.f. Lunar A 13.5Kg; DS-2 3.6Kg)
High impact speed ~ 300 m.sHigh impact speed ~ 300 m.s-1-1
Very rugged ~10kgeeVery rugged ~10kgee Few metres surface penetrationFew metres surface penetration Highly autonomous scientific payloadsHighly autonomous scientific payloads
Royal Astronomical Society, January 11, 2008
SINGLE-PIECE PENETRATOR
ALUMINIUM NOSE SECTION
TUNGSTEN TIP
DETACHABLE De-orbit and attitude control STAGE
ALUMINIUM CASING
Payload•IMPACT ACCELEROMETER
•Tiltmeter
•SEISMOMETERS/TILTMETER
•THERMAL SENSING (TEMP, CONDUCTIVITY,HEAT FLOW)
•GEOCHEMISTRY(E.G. WATER/VOLATILES DETECTOR)
•GROUND CAMERA (MINALOGY/ASTROBIOLOGY)
•OTHER (permitivity, magnetometer, radiation monitor)
•DESCENT CAMERA
ESTIMATED PENETRATOR SIZE
•LENGTH:- 480mm to 600mm (8:1 to 10:1 RATIO)
•DIAMETER:- 60mm
•ESTIMATED MASS 13kg
POINT OF SEPARATION
Penetrator Descent Module Design ConceptPenetrator Descent Module Design ConceptPlatform•S/C SUPPORT
•AOCS
•STRUCTURE
•POWER/THERMAL
•COMMS
•CONTROL & DATA HANDLING
Royal Astronomical Society, January 11, 2008
PROS and CONS ?PROS and CONS ?PROS• Cost effective especially for multiple sites.• Able to target areas which are not accessible to soft landers.• Provide ground truth for interpreting remote sensing data.• Provide direct access below the planetary surface
CONS• Can achieve key science, but low payload mass and high-gee constraints will
limit capability c.f. soft landers.• Limited Communications due to finite battery life.• Surviving for long periods for e.g. seismic network will be a challenge with
limited mass. (Insulation and RHU’s with primary batteries)• Have an associated impact risk
…good for pre-cursor investigations, seismic networks, and cost effective targetting of specific terrain features.
…good also as a step to exploration.
Royal Astronomical Society, January 11, 2008
Mars96 (Russia) failed to leave Earth orbit
DS2 (Mars) NASA 1999 ?
Planetary Penetrators - Planetary Penetrators - History
Many paper studies and ground trials
No survivable high velocity impacting probe has been successfully operated on any extraterrestrial body
TRL 5Japanese Lunar-A cancelled (maybe now to fly on Russian Lunar Glob ?)
Royal Astronomical Society, January 11, 2008
Suitable Bodies for Investigation ?Suitable Bodies for Investigation ?
• Moon (MoonLITE- UK Intiative)- is closeby – ideal technical demonstrator + excellent
science (polar water, deep structure, differentiation, …)- Airless -> like Europa, Enceladus - Very cold (polar traps) -> like Europa, Enceladus,Titan
• Europa,Titan/Enceladus (Cosmic Vision)- Astrobiology, interior ocean(s).- Europa – very high radiation environment
- Titan has an atmosphere – different approach !!!• NEO/Asteroids
- Accelerometer particularly interesting for investigating internal structure
• Etc, etc, (Mars, Venus, Mercury, Pluto, Triton, …)
Royal Astronomical Society, January 11, 2008
UK Penetrator Consortium - UK Penetrator Consortium - History
Jan 2006Jan 2006 – First meeting of consortium, now expanded to 8 – First meeting of consortium, now expanded to 8 UK institutes and 3 industriesUK institutes and 3 industries
Dec 2006Dec 2006 - UK Research Council commissioned report of - UK Research Council commissioned report of low cost lunar missions, MoonLITE (penetrator) and low cost lunar missions, MoonLITE (penetrator) and MoonRaker (lander), MoonLITE given top priority.MoonRaker (lander), MoonLITE given top priority.
Apr 2007Apr 2007 – First funding in place for penetrator trials – First funding in place for penetrator trials June 2007June 2007 – ESA Cosmic Vision proposals – ESA Cosmic Vision proposals
– LunarEx (not selected)LunarEx (not selected)– Jupiter-Europa (penetrator option) (passed first gate)Jupiter-Europa (penetrator option) (passed first gate)– Saturn-Enceladus (penetrator element) (passed first gate)Saturn-Enceladus (penetrator element) (passed first gate)
July 2007July 2007 – MoonLITE considered as part of a NASA- – MoonLITE considered as part of a NASA-BNSC bilateral programmeBNSC bilateral programme
Jan 2008Jan 2008 – Phase A study of MoonLITE to be kicked-off – Phase A study of MoonLITE to be kicked-off
Royal Astronomical Society, January 11, 2008
TerminologyTerminology
Descent Module, consisting of:Descent Module, consisting of:– PenetratorPenetrator– De-orbit (delta v ~ 1.7 km.sDe-orbit (delta v ~ 1.7 km.s-1-1) and attitude ) and attitude
control systemcontrol system– Descent CameraDescent Camera
The Descent Module is a spacecraft in its The Descent Module is a spacecraft in its own right, albeit rather short lived.own right, albeit rather short lived.
Royal Astronomical Society, January 11, 2008
FeasibilityFeasibility Military have been successfully firing Military have been successfully firing
instrumented projectiles for many instrumented projectiles for many years to at least comparable levels years to at least comparable levels of gee forces expected.of gee forces expected.
Target materials have been mostly Target materials have been mostly concrete and steel but include sand concrete and steel but include sand and ice.and ice.– 40,000gee qualified electronics 40,000gee qualified electronics
exist (re-used !)exist (re-used !)– When asked to describe the When asked to describe the
condition of a probe that had condition of a probe that had impacted 2m of concrete at 300 impacted 2m of concrete at 300 m.sm.s-1-1 a UK expert described the a UK expert described the device as ‘a bit scratched’!device as ‘a bit scratched’!
Royal Astronomical Society, January 11, 2008
Examples of hi-gee Examples of hi-gee electronic systemselectronic systems
Designed and tested :Designed and tested :
– Communication systemsCommunication systems 36 GHz antenna, receiver and 36 GHz antenna, receiver and
electronic fuze electronic fuze tested to 45 kgeetested to 45 kgee
– DataloggersDataloggers 8 channel, 1 MHz sampling rate 8 channel, 1 MHz sampling rate
tested to 60 kgeetested to 60 kgee
– MEMS devices (accelerometers, MEMS devices (accelerometers, gyros)gyros) Tested to 50 kgeeTested to 50 kgee
– MMIC devicesMMIC devices Tested to 20 kgeeTested to 20 kgee
– TRL 6TRL 6
MMIC chip tested to 20 kgeeMMIC chip tested to 20 kgee
Communication system and Communication system and electronic fuze tested to 45 kgeeelectronic fuze tested to 45 kgee
Royal Astronomical Society, January 11, 2008
MoonLITE - Mission DescriptionMoonLITE - Mission Description Delivery and Communications SpacecraftDelivery and Communications Spacecraft
(Orbiter).(Orbiter).Deliver penetrators to ejection orbit, Deliver penetrators to ejection orbit, provideprovide pre-ejection health status, pre-ejection health status, and relay communications.and relay communications.
Orbiter PayloadOrbiter Payload: : 4 Descent Probes 4 Descent Probes (each containing ~13 kg penetrator (each containing ~13 kg penetrator + ~23 kg de-orbit and attitude + ~23 kg de-orbit and attitude control).control).
Landing sites: Landing sites: Globally spaced Globally spaced Far side, Polar region(s), One near Far side, Polar region(s), One near an Apollo landing site for calibrationan Apollo landing site for calibration..
DurationDuration: : >1 year for seismic network. >1 year for seismic network. Other science does not require so long Other science does not require so long (perhaps a few Lunar cycles for heat flow (perhaps a few Lunar cycles for heat flow and volatiles much less).and volatiles much less).
Penetrator Design:Penetrator Design: Single Body for Single Body for simplicity and risk avoidance. Battery powered with simplicity and risk avoidance. Battery powered with comprehensive power saving techniques.comprehensive power saving techniques.
Royal Astronomical Society, January 11, 2008
MoonLITE – ScienceMoonLITE – Science
The Origin and Evolution of Planetary The Origin and Evolution of Planetary BodiesBodies
NASA Lunar Prospector
WaterWater and its profound and its profound implications for life andimplications for life andexplorationexploration
Royal Astronomical Society, January 11, 2008
Science – Polar VolatilesScience – Polar Volatiles
A suite of instruments will detect and A suite of instruments will detect and characterise volatiles (including water) characterise volatiles (including water) within shaded craters at both poleswithin shaded craters at both poles Astrobiologically importantAstrobiologically important
– possibly remnant of the original seeding of possibly remnant of the original seeding of planets by cometsplanets by comets
– may provide evidence of important cosmic-ray may provide evidence of important cosmic-ray mediated organic synthesismediated organic synthesis
Vital to the future manned exploration of Vital to the future manned exploration of
the Moonthe Moon
Royal Astronomical Society, January 11, 2008
Science - SeismologyScience - SeismologyA global network of seismometers will tell A global network of seismometers will tell us: us:
– Size and physical state of the Lunar CoreSize and physical state of the Lunar Core– Structure of the Lunar MantleStructure of the Lunar Mantle– Thickness of the far side crustThickness of the far side crust– The origin of the enigmatic shallow moon-The origin of the enigmatic shallow moon-
quakesquakes– The seismic environment at potential The seismic environment at potential
manned landing sitesmanned landing sites
Royal Astronomical Society, January 11, 2008
Science - GeochemistryScience - Geochemistry
X-ray spectroscopy at multiple, diverse sites X-ray spectroscopy at multiple, diverse sites will address:will address:
– Lunar Geophysical diversityLunar Geophysical diversity– Ground truth for remote sensingGround truth for remote sensing
XRS on Beagle-2
Leicester University
K, Ca, Ti, Fe, Rb, Sr, Zr
Royal Astronomical Society, January 11, 2008
Science – Heat FlowScience – Heat Flow
Heat flow measurements will be made at Heat flow measurements will be made at diverse sites, telling us:diverse sites, telling us:
– Information about theInformation about thecomposition and thermal composition and thermal evolution of planetary evolution of planetary interiorsinteriors
– Whether the Th Whether the Th concentration in the PKT concentration in the PKT is a surface or mantle is a surface or mantle phenominaphenomina
NASA Lunar Prospector
Royal Astronomical Society, January 11, 2008
– SeismologySeismology– Water and volatile detectionWater and volatile detection– AccelerometerAccelerometer– Heat FlowHeat Flow– Geochemistry/XRFGeochemistry/XRF
– Descent cameraDescent camera
– MineralogyMineralogy– Radiation MonitorRadiation Monitor
PayloadPayload
Ion trap spectrometer
(200g, 10-100amu)
(Open University)
Royal Astronomical Society, January 11, 2008
A systems approachA systems approach
ModularModular Impact modelling Impact modelling
validated with trialsvalidated with trials Parallel development Parallel development
of payload elements of payload elements and penetrator and penetrator structurestructure
Close liaison with Close liaison with Descent Module Descent Module primeprime
Cf. Skylark
Royal Astronomical Society, January 11, 2008
Key TechnologiesKey Technologies Payload instruments Payload instruments - ruggedization- ruggedization Batteries Batteries – Availability (Lunar-A, multiple US options)– Availability (Lunar-A, multiple US options) Communications – Communications – Based on Beagle-2, a trailing antenna Based on Beagle-2, a trailing antenna
would require developmentwould require development Structure material Structure material (Aluminium, carbon composite under (Aluminium, carbon composite under
consideration – needed for heatflow where trailing antenna is not consideration – needed for heatflow where trailing antenna is not available)available)
Sample acquisition Sample acquisition Thermal control Thermal control (RHUs probably needed for polar (RHUs probably needed for polar
penetrators)penetrators) AOCSAOCS (attitude control and de-orbit motor) (attitude control and de-orbit motor)
Spacecraft attachment and ejection mechanismSpacecraft attachment and ejection mechanism
Royal Astronomical Society, January 11, 2008
Technology IssuesTechnology Issues
Power / thermalPower / thermal Comms and data handlingComms and data handling Instrument ruggedizationInstrument ruggedization Heat Flow measurement and structure Heat Flow measurement and structure
materialmaterial
Royal Astronomical Society, January 11, 2008
Penetrator Development ProgrammePenetrator Development Programme
Phase 1: Modelling Phase 1: Modelling (until Jan 2008)(until Jan 2008)– Key trade studies (Power, Descent, Key trade studies (Power, Descent,
Structure material, Data flow, Thermal)Structure material, Data flow, Thermal)– Interface & System definitionInterface & System definition– Penetrator structure modellingPenetrator structure modelling– Procurement strategyProcurement strategy
Phase 2: Trials Phase 2: Trials ((until Jan 2010)until Jan 2010) – Payload element robustness proofingPayload element robustness proofing– Penetrator structure trials (March 2008)Penetrator structure trials (March 2008)– Payload selection and definitionPayload selection and definition– Baseline accommodationBaseline accommodation
Phase 3: EM Phase 3: EM (until Jan 2012)(until Jan 2012)– Design and QualificationDesign and Qualification
Phase 4: FM Phase 4: FM (until Dec 2012)(until Dec 2012)– Flight build and non-destructive testingFlight build and non-destructive testing
Generic
Mission
Specific
A BNSC – NASA Phase-A study will begin in January 2008 and last 6-9 months
Royal Astronomical Society, January 11, 2008
For more information visit: For more information visit:
http://www.mssl.ucl.ac.uk/planetary/missions/Micro_Penetrators.phphttp://www.mssl.ucl.ac.uk/planetary/missions/Micro_Penetrators.php or or
http://www.mssl.ucl.ac.ukhttp://www.mssl.ucl.ac.uk and follow the links and follow the links
Or contact Alan Smith on:
Royal Astronomical Society, January 11, 2008
Penetrator Descent Modules
Penetrator delivery system
Descent camera
De-orbit Motor
S/C attachment & ejection
Penetrator
Attitude Control System
Penetrator attachment &
ejection
Ground Support
Equipment
MoonLITE
Orbiter
Oribiter sub-systems
Royal Astronomical Society, January 11, 2008
StructureScience Instrumentation
Communication link
Data Management &
Control
Seismometer
Heat flow instrument
Power system
Geochemistry package
Water/volatile package
Regulation
Battery Unit
Packaging & Internal Support
Penetrator body
Transmitter
Receiver
Penetrator
Thermal
Accelerometers & Tilt
Sample Acquisition
Insulation
Sensors
RHU’s (?)
Data Handling
Commanding
Software
Antenna
Other
Royal Astronomical Society, January 11, 2008
MoonLITEMoonLITE
Mass (at impact) 13kg
Impact deceleration Up to 10,000 g.
Impact angle (between impact velocity vector and tangent to surface)
~90 (not critical)
Attack angle (between penetrator long axis and impact velocity vector)
~<8 (critical)
Penetration depth into regolith 2 to 5m.
Ambient penetrator operating temperature: -20°C to -50°C.(50K to 100K in shaded polar craters)
Mean penetrator power (subsystems & payload)
60mW.
Mission duration 1.2 years (1 year on surface)
Royal Astronomical Society, January 11, 2008
MoonLITE nominal PayloadMoonLITE nominal Payload
Payload instrument Sub-instrument
Mass (g) Integrated power usage over 1 year mission (W.hr)
Telemetry Allocation (over 1 year) (Mbits
Accelerometer and Tilt-meter 66 0.002 0.1
Geochemistry package 260 12.0 0.1
Water/Volatile Experiment 750 4.1 2.0
Seismometer 300 501.0 6.0
Heat Flow 300 1.0 0.6
Total Penetrator 1676 516.1 8.8
Descent Camera 160 0.05 2.0