Royal Astronomical Society, January 11, 2008 MoonLite a UK led penetrator mission to the Moon Professor Alan Smith On behalf of the UK Penetrator Consortium.

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


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


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


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.


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 ?)


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, …)


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


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.


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’!


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


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.


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


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


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


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


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


– 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)


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


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


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


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


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:

[email protected]


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


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


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)


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

Royal Astronomical Society, January 11, 2008 MoonLite a UK led penetrator mission to the Moon Professor Alan Smith On behalf of the UK Penetrator Consortium.

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