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Status of the French Mars exploration program

EGS, Nice April 24, 2002

« Programme de Retour d’Echantillons Martiens et Installation d’Expériences en Réseau »

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The two main components of the PREMIER program

The two main components of the PREMIER program

both being considered as equally important

participation to the Marssample return project (MSR) through a co-operation with NASA

participation to the Marssample return project (MSR) through a co-operation with NASA

deployment of a networkof Martian landersin co-operation withEuropean partners(NetLander project)

deployment of a networkof Martian landersin co-operation withEuropean partners(NetLander project)

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Elements of PREMIERElements of PREMIER• Main elements

–development and operation of the Martian orbiter of the Mars Sample Return (MSR) mission

–development and deployment of the NetLanders with a European consortium

• Additional elements–instrumental participation to ESA’s Mars Express –provision of scientific equipment on the orbiters,

landers & rovers on the future Mars exploration missions, e.g. NASA’s 2009 « smart lander »

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ComplementarityComplementarity

in situ science:- local investigations(landers & rovers)- network measurements(NetLander stations)

in situ science:- local investigations(landers & rovers)- network measurements(NetLander stations)

sample returnsample return

orbital scienceorbital science

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2007 CNES mission:basic requirements 2007 CNES mission:basic requirements

• the 2007 orbiter mission will prepare MSR through the validation of its major critical step

sample canister rendezvous & capture in-orbit demo

• it must have a high level scientific content NetLander + complementary scientific mission

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CNES 2007 mission (1/2)CNES 2007 mission (1/2)• main mission:

– Ariane 5 direct launch to Mars (Sept-Oct. 2007) of an orbiter + 4 NetLanders carried by the orbiter’s 1st stage

– NetLanders carried, ejected and deployed; mission duration goal: 1 Martian year (22 months)

– Mars orbit insertion– sample canister rendezvous & capture demo– telecom relay function for the NetLanders

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• options considered for the Complementary Mission

(1) orbital science

(2) orbital phase, then escape from Mars for Vesta fly-by

(3) Mars atmospheric sample return; the sample is collected during the aerocapture phase

(4) Phobos sample return

(5) Phobos lander & in situ science

CNES 2007 mission (2/2)CNES 2007 mission (2/2)

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(CM) must have a limited impact on the design (e.g. TM, elm, AOCS)

mass & volume strictly limited for the CM payload

CM must not impact the relay function of the orbiter:

- the required data rate (15 Mbit / day / station)- the latitude dispersion (+/- 30°)- the longitude dispersion

Drivers for the Complementary Mission (CM)

Drivers for the Complementary Mission (CM)

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Complementary mission (1/3)Complementary mission (1/3)

• Mid-2001: preliminary assessment of the impact

of the risk mitigation plan on the complementary

mission options

• 2 options assessed as feasible:

– orbital science

– Phobos lander + in situ science

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Complementary mission (2/3)Complementary mission (2/3)

• CNES’s Science Program Committee recommended the « orbital science » option

• Synergy between the scientific objectives of the proposed orbital experiments and of the NetLander objectives, e.g. study of the Martian atmosphere:

• density profiles of the main components• global circulation• escape phenomena

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Complementary mission (3/3)Complementary mission (3/3)

• payload selection schedule:

–international AO released: February 2002

–Letter of Intent : 20 received

–Proposal due: May 15, 2002

–Final selection: July 2002

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Recent evolutions (1/3)Recent evolutions (1/3)• CNES + French industry had selected

aerocapture for Mars orbit insertion– aerocapture combines a minimal cruise time to Mars

(as does chemical propulsion) with a reduced launched mass (as does electric propulsion or propulsive Mars orbit insertion + aerobraking phase)

• May - June 2001: joint NASA - CNES risk assessment group for the 2007 mission, especially those linked to aerocapture

elaboration of a risk mitigation plan

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Recent evolutions (2/3)Recent evolutions (2/3)• conclusion of the NASA-CNES risk assessment group:

the risk associated to aerocapture is acceptable and comparable to other Mars missions (propulsive Mars orbit insertion +

aerobraking) if a risk mitigation plan is implemented• conclusion endorsed by the MPSET, by CNES and

NASA

• however, the implementation of the mitigation plan necessitates the re-sizing of sub-systems, which causes an important increase of the orbiter cost

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Recent evolutions (3/3)Recent evolutions (3/3)• the risk mitigation plan induced constraints in the

inclination and the altitude of the orbit, with a dis-optimisation of the NetLander relay function; it also strongly constraints the complementary mission.

• it has thus been decided to give up with aerocapture for PREMIER 2007 Mars orbit insertion

• the launcher performances in 2007 and 2011 are compatible with this decision:

– 2007: Ariane 5 EPS 3 t

Ariane 5 ESC-A 3.5 to 4 t– > 2011:Ariane 5 ESC-B or Delta 4 Heavy > 5 t

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Final orbiter concept (1/2)Final orbiter concept (1/2)• 2 stage vehicle• 2007 Orbiter:

– 1st stage: passive NetLander carrier– Mars orbit insertion and orbit maintenance by

the 2nd stage (main stage)

• 20XX-MSR orbiter:– 1st stage: propulsive stage for Mars orbit

insertion– orbit maintenance and escape from Mars by the

2nd stage (main stage)

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OrbiterOrbiter configurationconfigurationOrbiterOrbiter configurationconfiguration

2007: Cruise configuration

2007: Mars orbit

20XX MSR Orbiter

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Final orbiter concept (2/2)Final orbiter concept (2/2)

• working orbit:

– near circular @ 500 km, near polar, heliosynchronous

@ 12 a.m. local time

– optimal for NetLander relay (goal: 1 Martian year)

– in a later phase, orbit lowered for the benefit of the

complementary mission (goal: 1 Martian year)

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2009

Science operations

2008• 2010 2011

phase 1

launchcruise

phase 2a 2b extension

phase 1 : priority NetLanders relayminimum : 1/2 martian yeargoal: 1 martian year

phase 2 : priority orbital science2a : low circular orbit2b : low periastre

End of NetLanders operations

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Orbiter characteristicsOrbiter characteristics

• mass budget (incl. margins):– orbiter dry mass: 830 kg– NetLanders: 340 kg (4x76.5 kg + interfaces)– rendezvous demo payload: 80 kg– additional science payload: 50 kg + I/F– Fuel: 1,680 kg

• total mass : ~3,000 kg

(compatible with Ariane 5 + EPS)

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NetLanders NetLanders

• 4 small ground station network• geophysical complement of MSR• main partners: CNES, FMI (Finland), DLR

(Germany), Belgium• 11 countries, mostly European and USA,

contribute to the NetLander payload

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NetLanders NetLanders • scientific objectives:

– study of the internal structure of Mars• sismometric measurements• magnetic sounding• subsurface sounding (GPR)

– climate monitoring• measurements of P, T, V, H20

• study of the polar condensation / sublimation cycle

– geodesy

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Cruise

Atmospheric Entry

Landing

Descent

NetLander mission scenarioNetLander mission scenario

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Panoramic Camera (PANCAM)

Seismometer (SEISM)

Meteo boom (ATMIS)

Magnetometer (MAG)

Electric field (ARES)

Ground Penetrating Radar (GPR)

Radioscience (NEIGE)geodesy & ionosphere

Soil properties (SPICE)Microphone

Netlander payloadNetlander payloadNetlander payloadNetlander payload

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Technical statusTechnical status

• orbiter– short definition phase (updating of phases A/B1):

March - July 2002– September 02: selection of a prime contractor– phase B2/C/D starts: 4th quarter 2002

• NetLander– phase C/D starts: June 2002

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MSR preparatory activities (1/2)MSR preparatory activities (1/2)

• objectives: ground based program aiming at preparing the French laboratories to response with success to the future international AOs concerning the analysis of the returned samples

• plan for upgrading the analysis facilities under preparation

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MSR preparatory activities (2/2)MSR preparatory activities (2/2)

• Planetary Protection activities– Planetary Protection Committee set up at the

Ministry of Research level– Planetary Protection office at CNES level

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Cooperative statusCooperative status

• October 2000: signature of a NASA - CNES « Statement of Intent » on Mars exploration

• July 2001: NASA-CNES LoA• Spring 2002: draft NASA-CNES MoU under

preparation (signature expected mid-2002)

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European DSN (1/2)European DSN (1/2)

• NASA’s DSN overloaded:– several Mars missions simultaneously on operation– high data rates, e.g.. 2nd generation MOC– other deep space missions (Cassini, Odyssey,

MRO, …)

• need for complementary facilities– utility for Rosetta, Bepi Colombo, Planck and

Herschel

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European DSN (2/2)European DSN (2/2)

• existing or planned European facilities:– ESA antenna in Australia (Perth)– ASI antenna in Sardinia (2005 ?)

• a 3rd antenna ( = 34 m), in South Africa (tbc) funded by CNES will provide a nearly full coverage

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ConclusionConclusion• the elaboration of the PREMIER program

has had a tremendous federative effect on the French scientific community

the AO on the MSR preparatory activities has received more than 40 proposals, involving 100 teams and 300 individuals

• many newcomers from the Earth and life science areas