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

space for science, enterprise and environment

MoonLITE and LunarEX

Rob Gowen and Alan SmithMullard Space Science Laboratory, UCL

PI Penetrator consortium


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


• 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


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


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


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’!


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


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.


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.


MoonLITE/LunarEX – Mission Sequence

• Launch & cruise phase• Deployment & descent• Landed phase


MoonLITE – Science

The Origin and Evolution of Planetary Bodies

NASA Lunar Prospector

Water and its profound implications for life andexploration


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


Prototype,

ruggedized ion trap

mass-spectrometer

Open University


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


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


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



• 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)


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


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


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


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


MoonLITE / LunarEX – UK

• Scientifically focussed • Precursor to future

penetrator programmes• High public interest• Impetus to industry• Affordable

Rationale


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

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

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