Status of the French Mars exploration program
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Transcript of Status of the French Mars exploration program
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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