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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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are needed to see this picture.Exploration Roadmap

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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are needed to see this picture.LRO Mission Overview

• 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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are needed to see this picture.LRO Spacecraft

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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are needed to see this picture.Mission Goals

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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Click to play

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

9

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

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