Mars Advanced Studies: The Next Generation Orbiters

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Mars Advanced Studies The Next Generation
Orbiters

• Marie-Jose Deutsch
• JPL/CalTech
• August 10, 2002
• 11th UN/ESA Workshop, Cordoba, Argentina

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(No Transcript)
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Advanced Studies Process
MEPAG
Study Office
Program
Surface Mobility
Next Generation Orbiters
Program Plan
Measurement Platform Analysis (191)
Measurements (191)
Subsurface Access
Investigations (40)
Reference Missions
Objectives (9)
Goals (4)
MSR
Pre-Projects

• Pre-Projects
• MSR
• Scouts

Scouts

• Life
• Climate
• Geology
• HEDS

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Program-Driven Missions
Increasing Scientific Knowledge Base
Knowledge
Requirements
Legacies
Mission 2
Mission 3
Mission 4
Mission 1
Services
New Technologies
Demonstrations
Program Progress, Time
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Mars Exploration Approach Seek, In Situ, Sample
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Reference Mission Summary (Post 2005)
Advanced Studies
Pre-Projects

• In-Situ Concepts
• Subsurface Drill
• Volcanology Rover
• Polar Layer Rover
• Orbiter Concepts
• SAR
• Atm/Imaging
• Multi-Scout

• Smart Lander 2009
• CNES Orbiter 2007
• ASI Telecom Orbiter 2007

Industry Studies

• Mars Sample Return
• Boeing
• Ball
• LMA
• TRW

Scout Studies

• PI led Concept Studies for 2007 launch

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Mars Future Mission Studies
CNES Mars 07 Orbiter Mission

• Function of Mission
• Deploy NetLanders CNES lead
• Aerocapture Demo CNES lead (this may be
  dropped from baseline)
• Rendezvous Sample Capture Demo for MSR NASA
  lead
• Orbital Science CNES lead
• RdV Payload Mass
• Allowed RdV mass is 105 kg
• Exploration Metrics
• Demo capture subphase
• Demo proximity RdV subphase
• Demo search /detection subphase

• Technology Heritage
• New Tech LAMP, RDF, OS, RdV GNC system
• Prior Mission redundancy Mission is demo for
  MSR Tech demos prior to CNES07 mission
  planned
• MSFC ground test
• XSS-1/ST6 test of RdV in proximity subphase

Earliest Possible Technology Ready
Launch September 2007
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G.Marconi OrbiterTarget Mars
JPL Advanced MISSION STUDIES

• Function of Mission
• Communications relay
• link for
• Data from landed and orbiting assets
• Critical event coverage
• Navigation support for
• S/C approaching Mars
• Navigation support for
• S/C approaching Mars
• OSS Detection

Technology Heritage New technology Electra
UHF X Gimbaled Orbiter Sample
Camera Prior Missions Dependency MRO
Demo Electra UHF OS Camera CNES 07
Orbiter Electra OSC Spares Sharing
Service Metrics Circular sun-synch orbit at
4450 km 4-hr/sol contact with landed assets
at all latitudes Data Return Up to 2
Gb/sol Data rate from surface 1 Kbps to
2Mbps Lifetime 6 years 4 years of
consumables
Earliest Possible Technology Ready Launch
July, 2007
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Mars Advanced Orbiter Imaging/Atmospheric Mission
MARS FUTURE MISSION STUDIES

• Exploration metrics
• Elliptical sun synchronous 330 orbit
• 150 km x 400 km
• 2 Mars years
• Imaging
• - 15 cm hi-resolution imaging (vis)
• - 20 m IR imaging
• - Hyper-spectral imaging (.4 to 5 micron) 10 m
  (Vis) to 30 m (IR)
• atmospheric water vapor concentration resol lt 100
  m
• Orbiter 2062 kg LV delta IV

• Function of Mission
• Very high resolution imaging of selected
• Sites and stereo imaging of of key sites
• Improve understanding of climate and
• atmosphere dynamics and constituents
• detailed landing site selection and hazard
• recognition

• Science payload
• Fourier Transform Spectrometer
• Hi-Res Stereo camera 2 context imagers 1 WA
• Hyper-spectral Imaging spectrometer
• IR and microwave radiometers
• Thermal imager

• Technology heritage
• Firewire I/F
• Ka-band 12.6 Mbps
• High power (250 W)
• TWTAs and DSN assets
• Autonav for terrain recognition
• High Compression 80X

• Earliest Possible Technology Ready Launch
  September, 2009
• Study Baselined for an October 2011 Launch

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Mars Advanced Orbiter Surface Science Mission
MARS FUTURE MISSION STUDIES

• Exploration metrics
• Elliptical sun synchronous 330 orbit
• 150 km x 400 km
• Imaging
• - 15 cm hi-resolution imaging (vis)
• - Hyper-spectral imaging (.4 to 5 micron) 10 m
  (Vis) to 30 m (IR)
• Orbiter 1442 kg LV delta IV

• Function of Mission
• Very high resolution imaging of selected
• Sites and stereo imaging of of key sites
• detailed landing site selection and hazard
• recognition

• Science payload
• Fourier Transform Spectrometer
• Hi-Res Stereo camera 2 context imagers 1 WA
• Hyper-spectral Imaging spectrometer

• Technology heritage
• Firewire I/F
• Ka-band High power (250 W)
• TWTAs and DSN assets (12 Mbps)
• Autonav for terrain recognition

• Earliest Possible Technology ready Launch
  September 2009
• Study Baselined on an October 2011 Launch
  Opportunity

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Mars Advanced Orbiter Atmospheric Mission
MARS FUTURE MISSION STUDIES

• Exploration metrics
• Circular 385 km 1 PM orbit
• Imaging
• - 20 m IR imaging
• - Hyper-spectral imaging (.4 to 5 micron) 10 m
  (Vis) to 30 m (IR)
• atmospheric water vapor concentration resol lt 100
  m
• Orbiter 1333 kg LV delta IV

• Function of Mission
• Improve understanding of climate and
• atmosphere dynamics and constituents

• Science payload
• Hyper-spectral Imaging spectrometer
• IR and microwave radiometers
• Thermal imager

• Technology heritage
• Firewire I/F
• Ka-band High power (250 W)
• TWTAs and DSN assets(12 Mbps)

• Earliest Possible Technology Ready
  LaunchSeptember, 2009
• Study Baselined on an October 2011 Launch
  Opportunity

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Mars Advanced Orbiter SAR Mission
MARS FUTURE MISSION STUDIES

• Exploration metrics
• 50 m and 5 m-targeted resolution topography
• 300 km circular, terminator orbit
• 7-Sol mapping repeat cycle
• covers 100 of planet over 1 Mars year
• Ka-band 5 Mbps downlink
• 1797 Kg flight system LV Delta IV

• Function of Mission
• Ku-band 20-m baseline interferometer
• to map Mars surface topography.
• P-band repeat-pass interferometer to
• map subsurface topography morphology
• Support for landing site selection

• Science payload
• The radar is part of
• the spacecraft

• Technology
• Ka-band DSN assets
• High power (100 W) TWTA
• Partially deployable 6 m antenna skirt
• (Ku-band 3 m antenna, P-band 6 m antenna)

• Earliest Possible Technology Ready Launch
  October, 2009

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MARS FUTURE MISSION STUDIES
Mars Advanced Orbiter Magnetometer/Gravity Mission

• Function of Mission
• High resolution magnetic field map of Mars
• Gravity field map
• Resolution of ages of locations on Mars
• Atmospheric sounding

• Exploration metrics
• Sub-satellite, SAR assumed to be carrier
• Elliptical sun synchronous noon orbit
• - 500 x 90 km? for magnetometer mission
• - 120 km periapse for gravity mission
• In orbit for one year 3 times global coverage
  with track spacing 100 to 150 km
• High accuracy accelerometers for gravity
  mission
• 210 kg orbiter requires host mission for trip
  to Mars

• Science payload
• Mass 5 kg
• Data rate 1.2 kbps
• 2 triaxial sets of fluxgate magnetometers
• Electra payload for UHF X- band Doppler
• to Earth and assets at Mars
• Mass spectrometer

• Technology heritage
• High heritage

Earliest Possible Technology Ready Launch
September, 2007 (Baselined for 2009 launch
piggybacked on Mars NG SAR mission)
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Payload Delivery / Telesat Orbiter
MARS FUTURE MISSION STUDIES

• Function of Mission
• Multi-scout carrier

• Exploration metrics
• 24 hr elliptical near polar orbit
• 263 km periapsis
• Mission duration a Martian year in orbit
• Carrier up to 1662 kg
• Scout Mass up to 750 kg
• LV Delta III (1920 kg) - Delta IV (3042 kg)

• Science payload
• Scouts to be released on approach and/or to be
  released from orbit
• Scout classes
• Global network (seismic, meteo) 10kg
• Small near-surface and surface probes 100 kg
• Lander/rover, small science orbiter 400 kg
• Moderate size Lander/rover, medium orbiters
  700 kg

• Technology heritage
• High heritage for carrier

• Earliest Possible Technology Ready Launch
  August 2007

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Mars Network and Telecom Mission (Rough Lander)
Function of Mission Deliver multiple landers
to Mars Provide telecom relay capability
for landers and succeeding Mars assets
Mission Characteristics Initial
orbit tailored to Lander needs which might
include in- orbit deliver Transition to
working telecom relay orbit Science mission
duration goal of 1 Martian year Total Mass
of Landers 700 kg Telecom S/C Mass 2100
kg Injected Mass 2800 kg LV Delta IV _at_
3300 kg
Science Payload 4 - 6 Network Landers
delivered on approach to Mars and/or from
in-orbit Each lander carries 10 20 kg of
science instruments
Technology Heritage High heritage for telecom
spacecraft Lander needs - Rough lander
structure - 2000 g packaging - Long life
technologies
Telecom Relay Comparable capability to
GMO - Electra Proximity Link - X/Ka Band to
DSN - Up to 2 Gb/sol - 6 years in-orbit (goal
10)
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MARS FUTURE MISSION STUDIES
Orbital Subsat Carrier/Telesat

• Exploration metrics
• 3 Sub-satellites released from multipurpose
  carrier
• Elliptical sun synchronous noon orbit
• - 500 x 90 km? for magnetometer mission
• - 120 km periapse for gravity mission
• In orbit for one year 3 times global coverage
  with track spacing 100 to 150 km
• High accuracy accelerometers for gravity mission
• 210 kg orbiter requires host mission for trip
  to Mars

• Function of Mission
• Orbital network carrier release 3 sub-sats
• study of Mars interior (magnetic and gravity
  maps) and upper atmosphere
• Telecom satellite

• Science payload/sub-sat
• 2 triaxial sets of fluxgate magnetometers
• Electra payload for UHF X-band Doppler
• to Earth and assets at Mars
• Mass spectrometer

• Technology heritage
• High heritage

• Earliest Possible Technology Ready Launch
  September, 2007

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Multiple Surface Landers Delivery System
MARS FUTURE MISSION STUDIES

• Function of Mission
• Delivery system for multiple landers (9
  landers)
• Detect presence depth (200 m)of subsurface
  water for three distinct locations
• Locate position of landers accurately

• Exploration metrics
• Payload released from orbit landed error ellipse
  50 x 4 Km2
• Landed mission duration 1 months
• Carriers 799 (x 3) kg
• LV Delta IV 4450-14 (2992 kg)

• Science payload (98 kg)
• 3 sites explored
• Each site
• 3 seismometers w 8 drop charges
• 3 EM sounders with 3 lop antennae

• Technology
• High heritage for carrier
• Parafoil deployment at Mars

• 3 beacons
• 3 reflectors or die for visual location from
  orbit
• 1 context imager

• Earliest Possible Technology Ready Launch
  August 2007

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Solar System Exploration Priorities for 2003-2013
(NRC Planetary Decadal Report, New Frontiers in
the Solar System An Integrated Exploration
Strategy, Released July 11, 2002)
http//www.aas.org/dps/decadal/
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A Possible Sequence for Future Mars Missions with
Early Sample Return
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Mars Long-Lived Landed Network
MARS FUTURE MISSION STUDIES

• Function of Mission
• Global Science Network ( gt 8 probes) over full
  Martian year
• internal structure and activity of the
  planet
• composition and activity of its atmosphere.

• Exploration metrics
• Deliver probes between /- 40 lat.
• less than full year coverage at higher
  latitudes no data in winter side of planet on
  arrival (no RTGs)
• Deliver on approach (do not carry any probes
  into orbit for later deployment)

• Science payload (10 kg)
• Passive, long period passive short period
  seismometers
• Met stations (P, T, rel. humidity, atmos
  opacity, wind velocity)

• Mass spectrometer (high precision chemical and
  isotopic analysis of the chemical dynamics of C,
  H, and O)
• PanCam multispectral
• Entry science (accelerometers)
• No Heat-flow probes because require drilling of
  holes

• Technology heritage
• high inheritance

• Earliest Possible Technology Ready Launch
  August 2007