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Benjamin NeumannExploration Systems Mission Directorate
Lunar Reconnaissance Orbiter &Lunar CRater Observation and Sensing Satellite Project
Commercial Development SummitMay 13, 2008
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Lunar Robotic MissionsLunar Robotic Missions
Lunar Outpost BuildupLunar Outpost Buildup
Commercial Crew/Cargo for ISSCommercial Crew/Cargo for ISS
Ares I and Orion DevelopmentAres I and Orion Development
Altair Lunar Lander DevelopmentAltair Lunar Lander Development
Surface Systems DevelopmentSurface Systems Development
Ares V & Earth Departure StageAres V & Earth Departure Stage
Science Robotics MissionsScience Robotics Missions
0605 07 08 09 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25
SSP TransitionSSP Transition
Operations Capability Development(EVA, Ground Operations, Mission Operations)Operations Capability Development(EVA, Ground Operations, Mission Operations)
Orion and Ares I Production and OperationOrion and Ares I Production and Operation
Initial Orion (CEV) CapabilityInitial Orion (CEV) Capability
Research and Technology Development on ISSResearch and Technology Development on ISS
Space Shuttle OperationsSpace Shuttle Operations
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Lunar Reconnaissance Orbiter
• Provide early information for human missions to the Moon– Focus on unknowns associated with the North and South Poles –
likely destinations for a lunar outpost
• Increase capability and sustainability through strategic priorities:– Good quality topographical global map– Surface temperature and illumination characteristics– Resource distribution to overlay map– Radiation environment– Search for presence of water in permanently shadowed craters at
lunar poles
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• Launch in late 2008 on a Atlas V into a direct insertion trajectory to the moon. Co-manifested with LCROSS lunar impacter mission.
• On-board propulsion system used to capture at the moon, insert into and maintain 50 km mean altitude circular polar reconnaissance orbit.
• 1 year mission with extended mission options.
• Orbiter is a 3-axis stabilized, nadir pointed spacecraft designed to operate continuously during the primary mission.
• Investigation data products delivered to Planetary Data Systems (PDS) within 6 months of primary mission completion.
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• The deposits at the north appear to be in the form of many small pockets which average about 100 ppm above the equatorial hydrogen content.
o The spatial resolution of the spectrometer was on the order of 50 to 150 km, insufficient to resolve surface features associated with the hydrogen signature.
• The deposits in the permanently-shaded craters near the south are consistent with a thick soil containing an enhancement of 1670±890 ppm hydrogen.
equivalent to 1.5 ± 0.8 wt.% H2O
Nor
th P
ole
(>70
o )So
uth
Pole
(<-7
0o )Interpretation: Polar Hydrogen Deposits on the Moon
Observations from Lunar Prospector Neutron Spectrometer
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Lunar Reconnaissance OrbiterGoddard Space Flight Center (GSFC)
LROCLunar Reconnaissance Orbiter Camera
Arizona State Univ
LENDLunar Exploration Neutron Detector
Russian Inst for Space Research
DLREDiviner Lunar Radiometer Experiment
UCLA/JPL
CRaTERCosmic Ray Telescope for the Effects of Radiation
Boston U/MIT
MINI-RFSynthetic Aperture Radar
Naval Air Warfare Center
LOLALunar Orbiter Laser Altimeter
GSFC
LAMPLyman Alpha Mapping Project
Southwest Research Inst
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Lunar Exploration Neutron Detector (LEND)
Solar Array (Deployed)
Mini-RF Technology Demonstration
Instrument Module(LOLA, LROC, LAMP)
High Gain Antenna System
Cosmic Ray Telescope for the Effects of Radiation (CRaTER)
Diviner Lunar Radiometer Experiment (DLRE)
Spacecraft Bus
60, 30 arc-secPointing Accuracy, Knowledge
Dry: 924 kg, Fuel: 898 kg (1263 m/sec)
461 Gb/day, 100Mb/secData Volume, Max Downlink rate681 WOrbit Average Bus Power1845 kgMass (CBE)
LRO Orbiter Characteristics
LEND Neutron InstrumentACS Thruster Module (1 of 4)
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Instrument Suite has Detailed Traceability to Exploration Requirements
• S-band and X-band SAR demonstration
Mini-RFTechnology Demonstration
• Polar Illumination Movies• Mineralogy
• Rock hazards• Small craters
LROCLunar Reconnaissance Orbiter Camera
• Simulation of Lighting Conditions• Crater Topography• Surface Ice Reflectivity
• Slopes• Topography/Rock
Abundance• Geodesy
LOLALunar Orbiter Laser Altimeter
• Neutron Radiation Environment
• Subsurface Hydrogen Enhancement• Localization of Hydrogen
Enhancement
LENDLunar Exploration Neutron Detector
• Surface Ice• Image Dark Craters
LAMPLyman Alpha Mapping Project
• Temperature• Mineralogy
• Rock abundanceDLREDiviner Lunar Radiometer Experiment
• High Energy Radiation• Radiation effects on
human tissue
CRaTERCosmic Ray Telescope for the Effectsof Radiation
New TechnologyLife in Space EnvironmentLocate ResourcesNavigation/
Landing Site SafetyInstrument
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Visible Camera• Impact Context• Curtain Morphology
Lunar Crater Observation & Sensing SatelliteAmes Research Center (ARC) &
Near Infrared Camera• Water Ice / Curtain
Morphology• NIR Context
Mid-Infrared Camera• Curtain, Crater
Temperature• Curtain Morphology• Water Ice
Visible Spectrometer• Flash Spectroscopy• Water Vapor• Organics
Near Infrared Spectrometers• Curtain Water Ice &
Vapor• Hydrated minerals
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• The LCROSS Mission is a Lunar Kinetic Impactor employed to investigate the presence& nature of water ice on the Moon
– LCROSS is a 1000kg secondary payload riding on LRO launch vehicle in late 2008
– LRO/LCROSS will launch on an Atlas V – LRO separates and LCROSS utilizes lunar
gravity-assist to establish a high-ecliptic inclination, 3-4 month cruise orbit
– LCROSS separates from 2300kg Centaur stage, to enable LCROSS to observe impact and measure ejecta plume
– Centaur expected to excavate ~200 metric tons of regolith, leaving a crater the size of ~1/3 of a football field, ~15 feet deep.
– The S-S/C becomes a ~700kg 'impactor' as well– Ground and space-based observation being
organized
Mission Overview
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Science goals:• Confirm the presence or absence of water ice in
a permanently shadowed region on the Moon• Identify the form/state of hydrogen observed by
at the lunar poles• Quantify, if present, the amount of water in the
lunar regolith, with respect to hydrogen concentrations
• Characterize the lunar regolith within a permanently shadowed crater on the Moon
Perform first “in-situ” analysis of regolith from a permanently shadowed region
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308092-1 R2 Panel
308093-1 R3 Panel
308094-1 R4 Panel
308091-1 R1 Panel
308095-1 R5 Panel 308070-1
R6 Panel
308067-1 Core
Propulsion Assembly
Spacecraft Harness
Shepherding Spacecraft Configuration
(Northrop-Grumman Proprietary)
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4.00 m
Boattail Access
Doors (4 Location)
CEM
• Atlas V
• 4-m Large Payload Fairing (LPF)
Launch Vehicle Integration
Atlas V 401
LRO
LCROSS
Centaur
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LRO Mission
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Luna
Surveyor
Apollo
“Top 10” Exploration Sites+
LRO Enables Global Lunar Surface Access
Near Side Far Side
+
+
++
+
+
1112 14
15 17
16
5631
7
24
21
20
17
16
13
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3Aristarchus Plateau
OceanusProcellarum
Mare TranquillitatisRima Bode
Orientale BasinFloor
+Mare Smythii
+Central Farside
Highlands
South Pole-Aitken BasinFloor
South Pole+
North Pole+
Apollo 15-17 Panoramic Camera(unregistered)
Current Apollo heritage image set onlyCovers 4 of 10 ESAS sites.
LRO Global Topography, Imagery and Resource Maps
LRO 1m Landing Site Images
LRO extends coverage to entire Moon Most other high priority sites identified lie outside Apollo heritage area