1

LRO Mission Overview

Craig Tooley - GSFC/431September 7, 2005

2

2008 Lunar Reconnaissance Orbiter (LRO)First Step in the Robotic Lunar Exploration

Program

Robotic Lunar Exploration ProgramRobotic Lunar Exploration Program

LRO Objectives

• Characterization of the lunar radiation environment, biological impacts, and potential mitigation. Key aspects of this objective include determining the global radiation environment, investigating the capabilities of potential shielding materials, and validating deep space radiation prototype hardware and software.

• Develop a high resolution global, three dimensional geodetic grid of the Moon and provide the topography necessary for selecting future landing sites.

• Assess in detail the resources and environments of the Moon’s polar regions.

• High spatial resolution assessment of the Moon’s surface addressing elemental composition, mineralogy, and Regolith characteristics

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• LRO provides major scientific and exploration benefit by 2009– Apollo provided only a small glimpse of Moon; much to be explored– LRO address both science and exploration objectives– LRO brings many benefits (e.g., future landing sites, polar resources, safety, science)

• LRO selected instruments complement other foreign efforts– Six instruments competitively selected (“next-generation payload”)– Comparison to foreign systems demonstrate uniqueness and value– LRO will also accommodate a HQ directed Technology Demonstration payload, the

Mini-RF (SAR) instrument.

• LRO will enhance our knowledge of the Moon and increase the safety of future human missions.

– 3D maps of terrain and hazards, as well as of localized resources (ice) will tell us where to land (and at what precision).

– Exploration of new sites where resources may be available requires new and timely knowledge of those sites at scales never before possible.

• Current state of knowledge does not allow us to reduce the risk and cost of humans landing and working on the Moon.

– Equatorial environment (terrain, thermal, lighting) is different from polar region.– Apollo Program flight system capability limited to equatorial region (capability)

Investigation Background

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Benefit Example: Identifying Landing Sites & Resources

Polar Topography/shadow mapping

Resource imaging

Temperature mapping (find cold traps)

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• Launch in late 2008 on a Delta II rocket into a direct insertion trajectory to the moon.

• On-board propulsion system used to capture at the moon, insert into and maintain 50 km altitude circular polar reconnaissance orbit.

• 1 year mission• Orbiter is a 3-axis stabilized,

nadir pointed spacecraft designed to operate continuously during the primary mission.

LRO Mission OverviewFlight Plan – Direct using 3-Stage ELV

Solar Rotating Coordinates

Earth

Moon at encounter

Cis-lunar transfer5.1978 day transferLaunch C3 –2.07 km2/s2

1-dayLunar Orbit

Sun direction

Nominal Cis-lunar Trajectory

Cis-Lunar Transfer

12-hour orbit

6-hour orbit

100 and 50kmmission orbits

Insertion and CircularizationImpulsive Vs (m/s)

1 – 344.242 – 113.063 – 383.914 – 11.455 – 12.18

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LRO Mission OverviewOrbiter

LRO Instruments

• Lunar Orbiter Laser Altimeter (LOLA) Measurement Investigation – LOLA will determine the global topography of the lunar surface at high resolution, measure landing site slopes and search for polar ices in shadowed regions.

• Lunar Reconnaissance Orbiter Camera (LROC) – LROC will acquire targeted images of the lunar surface capable of resolving small-scale features that could be landing site hazards, as well as wide-angle images at multiple wavelengths of the lunar poles to document changing illumination conditions and potential resources.

• Lunar Exploration Neutron Detector (LEND) – LEND will map the flux of neutrons from the lunar surface to search for evidence of water ice and provide measurements of the space radiation environment which can be useful for future human exploration.

• Diviner Lunar Radiometer Experiment – Diviner will map the temperature of the entire lunar surface at 300 meter horizontal scales to identify cold-traps and potential ice deposits.

• Lyman-Alpha Mapping Project (LAMP) – LAMP will observe the entire lunar surface in the far ultraviolet. LAMP will search for surface ices and frosts in the polar regions and provide images of permanently shadowed regions illuminated only by starlight.

• Cosmic Ray Telescope for the Effects of Radiation (CRaTER) – CRaTER will investigate the effect of galactic cosmic rays on tissue-equivalent plastics as a constraint on models of biological response to background space radiation.

SOLAR ARRAY

PROPULSION MODULE

AVIONICS MODULE

INSTRUMENT MODULE

Mini-RF

LOLA

LAMP

LROC

CRaTER

SOLAR ARRAY

HGA

PROPULSION MODULE

AVIONICS MODULE

INSTRUMENT MODULE

Diviner

LEND

LAMP

LRO Preliminary Design

Preliminary LRO Characteristics

Mass 1317 kgDry: 603 kg

Fuel: 714 kg

Power 745 W

Measurement Data Volume

575 Gb/day

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Competitively Selected LRO Instruments Provide Broad Benefits

1000’s of 50cm/pixel images (125km2), and entire Moon at 100m in UV, Visible

~50m scale polar topography at < 1m vertical, roughness

Hydrogen content in and neutron radiation maps

from upper 1m of Moon at 5km scales, Rad > 10 MeV

Maps of frosts in permanently shadowed

areas, etc.

300m scale maps of Temperature, surface

ice, rocks

Tissue equivalent response to radiation

Measurement

Resource evaluation, impact flux and

crustal evolution

Safe landing sitesthrough hazard

identification; some resource identification

LROC

Geological evolution of the solar system by geodetic topography

Safe landing site selection, and

enhanced surface navigation (3D)

LOLA

Improved understanding of

volatiles in the solar system - source,

history, migration and depositionLocate potential water-

ice in lunar soil and enhanced crew safety

LEND

Locate potential water-ice (as frosts) on the

surface

LAMP

Determines conditionsfor systems operability and water-ice location

Diviner

Radiation conditions that influence life

beyond Earth

Safe, lighter weight space vehicles that

protect humans

CRaTER

ScienceBenefit

ExplorationBenefit

INSTRUMENT

1000’s of 50cm/pixel images (125km2), and entire Moon at 100m in UV, Visible

~50m scale polar topography at < 1m vertical, roughness

Hydrogen content in and neutron radiation maps

from upper 1m of Moon at 5km scales, Rad > 10 MeV

Maps of frosts in permanently shadowed

areas, etc.

300m scale maps of Temperature, surface

ice, rocks

Tissue equivalent response to radiation

Measurement

Resource evaluation, impact flux and

crustal evolution

Safe landing sitesthrough hazard

identification; some resource identification

LROC

Geological evolution of the solar system by geodetic topography

Safe landing site selection, and

enhanced surface navigation (3D)

LOLA

Improved understanding of

volatiles in the solar system - source,

history, migration and depositionLocate potential water-

ice in lunar soil and enhanced crew safety

LEND

Locate potential water-ice (as frosts) on the

surface

LAMP

Determines conditionsfor systems operability and water-ice location

Diviner

Radiation conditions that influence life

beyond Earth

Safe, lighter weight space vehicles that

protect humans

CRaTER

ScienceBenefit

ExplorationBenefit

INSTRUMENT

(BU+MIT)Cosmic Ray Telescopefor the Effects of Radiation

(UCLA)

(SWRI)Lyman-Alpha Mapping Project

(Russia)Lunar Exploration Neutron Detector

(GSFC)Lunar Orbiter Laser Altimeter

(NWU+MSSS)Lunar Recon Orbiter Camera

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LRO Spacecraft Systems Block Diagram

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LRO C&DH Architecture Block Diagram (New-8/29/05)

RAD750SBC

GD-DIB# HK/IO

Ka-Comm

S-Comm

LROC

LAMP

LOLA

NAC1 WACNAC2

32 Mbps

1Mbps 38.4Kbps(UART)

ThermalCard

1553BSerial IF

LEND

Diviner

CRATER

SpaceWire (HSB)

1553B (LSB)

125 Mbps (Science Downlink)

Mini-RF

8 to 32Mbps(Max.)

BAE SpaceWire

ASIC

1553 Summit

3U-cPCI

SpaceWire FPGA

SpaceWire FPGA

SpaceWire FPGA

SpaceWire FPGA

SpaceWire FPGA

C&DH

Instruments

LVPC

SUBSYSTEMS (ACS, PSE, PRO/DEP)

Unsw. +28V

Backplane

HGA

Hi-RateTlm125Mbps (Max.)

S-Xpndr

Ka-Xmtr

HGAGimbalsLow-Rate

Tlm 2Mbps Max & Command 4Kbps

UnSw. +28V (SBC)

1553 Summit

5 Heater out Unsw.+28V

Sw. +28V (Ka-Comm)

UnSw. +28V (S-Comm)

+3.3V (B), +5V (B)

+/-15V, +5V, +3.3V (A)

I/O

( A) (B)

Sw. +28V (Heater)2 Mbps Max. (HK Downlink)

2 Mbps Max. (LAMP Tlm)

+28V Power

1PPS

6U-cPCI

GD-DDAGD-DDA

ATA IF

#Changed

cPCI Backplane

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LRO Spacecraft Systems Capabilities

LRO Capability Highlights

Mass: 1480 kg

Power: 823 W orbit average @ 35V

Battery: Lithium Ion Chemistry

80 Amp-Hour Capacity

Data Storage Capacity: 400 Gb

Data Rate: 100 Mbps Down – Ka Band

2.186 Mbps Up/Down – S Band

Timing relative to UTC: 3ms

Delta V Capability: 1326 m/sec

Pointing Accuracy: 60 Asec relative to GCI

Pointing Knowledge: 30 Asec relative to GCI

LRO Capability Highlights

Mass: 1480 kg

Power: 823 W orbit average @ 35V

Battery: Lithium Ion Chemistry

80 Amp-Hour Capacity

Data Storage Capacity: 400 Gb

Data Rate: 100 Mbps Down – Ka Band

2.186 Mbps Up/Down – S Band

Timing relative to UTC: 3ms

Delta V Capability: 1326 m/sec

Pointing Accuracy: 60 Asec relative to GCI

Pointing Knowledge: 30 Asec relative to GCI

LRO Overview

6 Instruments and 1 Technical Demonstration

3 Spacecraft Modules – Instrument, Propulsion, Avionics

2 Deployable Systems – High Gain Antenna, Solar Array

2 Data Buses – Low Rate 1553, High Rate Spacewire

2 Comm Links – S Band, Ka Band

Monopropellant System – Hydrazine, Single Tank design

LRO Overview

6 Instruments and 1 Technical Demonstration

3 Spacecraft Modules – Instrument, Propulsion, Avionics

2 Deployable Systems – High Gain Antenna, Solar Array

2 Data Buses – Low Rate 1553, High Rate Spacewire

2 Comm Links – S Band, Ka Band

Monopropellant System – Hydrazine, Single Tank design

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Ground System Architecture Overview

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LRO Mission Phases Overview

No Phase Sub-Phases Description

1Pre-Launch/ Launch

Readiness

Space Segment Readiness Ground Segment Readiness

Includes instrument I&T, spacecraft/orbiter I&T, space/ground segment testing as well as operations preparation and ground readiness testing leading up to launch.

2

Launch & Lunar Transfer

Launch and Ascent Separation and De-spin Deployment and Sun Acq. Lunar Cruise Lunar Orbit Insertion

Includes all activities & operations from launch countdown sequence to Lunar Orbit Insertion (LOI). LOI includes all maneuvers necessary to obtain the temporary parking orbit for Orbiter activation and commissioning. During the cruise phase, initial spacecraft checkout will be performed to support activities for mid course correction (MCC) and LOI.

3

Orbiter Commissioning

Spacecraft Commissioning Integrated Instrument

Commissioning

Configure and checkout the spacecraft subsystems and ground systems prior to instrument turn-on. Instrument integrated activation will be developed to complete instruments turn-on and commissioning. Instrument commissioning includes any calibration activities needed in the temporary orbit.

4

Routine Operations

Measurements (Routine Ops) Station-keeping Momentum Management Instrument Calibrations Lunar Eclipse Yaw Maneuver Safe Mode

One year of nominal science collection in the 50 (+/- 20) km orbit.

5Extended Mission

Operations

After 1-year of science observations, orbiter will be boosted into a higher orbit to reduce maintenance requirements. Potential purpose for extended mission operationsmay be to perform relay comm. operations. Alternatively additional measurementoperations may be performed for a shorter period in a continued low orbit.

6End-of-Mission Disposal

Includes planning and execution of end-of-life operations. LRO will impact lunar surface.

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LRO Project OrganizationLRO Project Manager

C. Tooley

400

System AssuranceManagerR. Kolecki

08/31/2005

Deputy Project ManagerTBD

Deputy Project Manager/Resources

P. Campanella

Materials EngineerP. Joy

Manufacturing EngineerN. Virmani

Safety ManagerD. Bogart

RM CoordinatorA. Rad

Project ScientistG. Chin

FinancialManagerB. Sluder

Project SupportManager

K. Opperhauser

CM/DMD. Yoder

SchedulingA. Eaker

General BusinessD. Yoder/ P. Gregory

MISA. Hess/ J. Brill

Mission Business Mgr.J. Smith

ContractingOfficerJ. Janus

OrbiterI & T Lead

J. Baker

ACS HardwareJ. Simpson

CommunicationsJ. Soloff

C&DHQ. Nguyen

Flight DynamicsM. Beckman/ D. Folta

SoftwareM. Blau

ThermalC. Baker

PowerT. Spitzer

ACS AnalystJ. Garrett

PropulsionC. Zakrzwski

ElectricalR. Kinder

MechanicalG. Rosanova

Mission SystemEngineer

M. Houghton

GN&C Systems EngineerE. Holmes

Avionics Systems EngineerP. Luers

Orbiter Systems EngineerM. Pryzby

Operations System EngineerM. Beckman/ D. Folta

SW/HW SystemsEngineerC. Wilderman

Contamination ControlC. Lorenston

Mission Success EngineerK. Deily

Payload SystemsManagerA. Bartels

Ground Network& Operations

R. Saylor

Payload SystemsEngineers

CRaTERD. Spence

Boston University

DivinerD. Paige

UCLA

LENDI. Mitrofanov

ISR, Moscow

LAMPS. Stern

SWRI

LROCM. Robinson

Northwestern Univ.

Mini -RF

NAWC

LOLAD. Smith

GSFC

L. Hartz

J. Baker

M. Reden

Launch VehicleManagerT. Jones

200

600

300

400

400

500

500 400 400 400

500

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LRO Mission Schedule

2004 2005 2006 2007 2008 2009Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4

7/31/05

LRO Mission Schedule

LRO Mission Milestones

Mission Feasibility Definition

Payload Proposal Development

Payload Preliminary Design

System Definition

S/C &GDS/OPS Preliminary Design

Payload Design (Final)

Spacecraft Design (Final)

GDS/OPS Definition/ Design

Payload Fab/Assy/Test(7 Instruments)

S/C Fab/Assy/Bus Test

GDS/OPS DevelopmentImplemention & Test

Integration and Test

Launch Site Operations

Mission Operations

AO Release

AO Sel. MRD

SRR

IPDR PDR

IBRConf. Review

ICDR CDR MOR

IPSR

PER

FOR/ORR

MRR

PSR

LRR

Launch

Instr. PDR's9/6-9/29

Network Decision

Payload complete (Final Delivery to I&T)(LAMP/LOLA/LROC/Diviner/CraTer/LEND/Mini-RF)

S/C complete (Final delivery to I&T)

GND Net Test Ready

S/C BUS Payload

Ship to KSC

Launch

(1M Float)

(1M Float)

(1M Float)

Ver. 0.9

(1M Float)

CY

Envir. Testing

Mission PDR target: November 14

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LRO Project Overall Status• Project almost fully staffed

– 45 civil servants & 23 support contractor at present (FTEs & WYEs)– Project level augmentations in-work as Program/Project resources are phased out.

• Project infrastructure in-place– Project organization and staffing being adjusted in reaction to RLEP transfer to ARC

• Project Plan drafted for November 2004 Program review– Currently being revised to reflect RLEP move to ARC & to comply with NPR 7120.5 rev.

C

• Mission SRR successfully conducted August 16-17

• Major system trades nearly complete– C&DH Architecture– Propulsion System – Ground Network – Data Recorder Technology – High Accuracy Tracking Methodology

• Level 2 & Level 3 Requirements established and moving thru review/approval cycles – SRR successfully completed

• Overall integrated mission development schedule developed and in review– Baselined after PDR in preparation for Confirmation

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LRO Element Development Status

• Instruments – high heritage proposed designs converging to preliminary designs– Design efforts primarily focused in two areas

• Design modifications to adapt to LRO command/data interfaces• Design modifications driven by lunar thermal environment

– Low lunar polar orbit is significantly different than Mars missions where most instrument heritage is from.

– Interfaces with spacecraft well defined – ICDs in review/release cycle• Allocations released and agreed upon

– LRO Payload Science Working Group formed and functioning• Consists of PI’s lead by LRO Project Scientist

– Integral part of LRO mission operations planning

• Spacecraft bus – AO design concept evolving to preliminary design– All subsystems on track for mission PDR this Fall

• Propulsion subsystem moved in-house at GSFC – leverages HST-DM surplus hardware• Spacecraft Computer specified and under development on ESES contract• SQ-RAID (hard disk) technology selected for data recorder. Acquisition now in-work.• Subsystem technical Peer Review being conducted Sept. - November• Approximately $15M in direct procurements planned during Sept.-Dec.

• Ground Systems – architecture and acquisition approach defined– Mission Operations Center

• Preliminary design established based on GSFC heritage systems• Location established, initial facility agreements in-place

– Ground Network• Requirements and architecture established• Primary 18m antenna procurement contract in place• GSFC Ground Networks providing end-to-end system

– Development tasks on NENS contract established

• SRR Planned for November

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LRO Requirements

• Mission SRR held 9/16-17/2005 – judged very successful– Review covered development and flow down of level 2 and 3

requirements from the NASA ESMD Level 1 requirements• Instruments presented flow down of Level 1 measurement and data

product requirements to their level 2 and 3 performance and functional requirements

• Project presented flow down of level 2 and 3 mission, spacecraft, and ground system requirements

• ~ 50 RFAs/Comments, none specific to instruments.

• Level 1 requirements being refined by ESMD with Project and assistance.

– Ongoing work includes establishment of Mission Success Criteria

– SRR demonstrated that instrument requirements are established, understood, and realizable.

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LRO Requirements Development Roadmap

LRO Level 1 RequirementsESMD-RQMT-0010

Mini-RFAllocationsElectrical Spec

Mechanical SpecThermal Spec

LRO Mission RequirementsDocument

431-RQMT-000004

Level 2 Performance & SOC

Requirements

Level 2 Requirement Synthesis

Instrument Proposals & LRO AO/PIP+

Instrument Questionnaires+

Instrument-Project TIMs+

Instrument Accommodation Review+

Mission Trade Studies+

Collaborative Drafting of ICDs

Instrument interface requirements & constraints on spacecraft

Spacecraft and Ground Requirements

Operations

Contamination

RadiationMission Assurance

LOLALROC

LAMPLEND

CRaTERDiviner

Project Requirements

Measurement Requirements & Instrument Specific Expected Data Products

Spacecraft, Instrument & Ground Level 3 Requirements Documents & ICDs

Preliminary Engineering

Launch Vehicle

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LRO Mission Requirements Hierarchy

ESMD

Launch Vehicle

LRO OrbiterInstrumentsSpacecraft Bus

Tech Demo

FSW Power

Flight Dynamics

Propulsion

Communication

Electrical

C&DHMechanical

LAMP LROC LEND DRLE LOLACRaTER

LRO Mission

Ground System

LRO Level 1Requirements

ESMD-RLEP-0010

LEVEL 2

LEVEL 3

LEVEL 1

Mission Assurance

MISSIONASSURANCE

Mission Requirements Documents

Mission Requirements Document (MRD)

431-RQMT-000004

ACS

LOLA to Spacecraft Electrical ICD

431-ICD-000098

DLRE Electrical ICD

431-ICD-000095

LEND Electrical ICD

431-ICD-000097

LROC Electrical ICD

431-ICD-000099

LAMP Electrical ICD

431-ICD-000096

CRaTER Electrical ICD

431-ICD-000094

Tech Demo Requirements

Mini RF Requirements and Goals Document

431-RQMT-000157

GROUND/OPERATION

GENERAL SPECSSYSTEMS

Thermal

CM Key

Released

Document

In CCB for Release

Document

DRAFT

Document

To Be Written

Document

LV Questionnaire

431-REF-000172

Delta II Payload Planners Guide

MDC 00H0016

Range Safety User Requirements

AFSPCMAN 91-710

Thermal Modeling Reqt Document

431-RQMT-000092

Component MICD Guidelines HDBK

431-HDBK-000093

LRO SpaceWire Spec

431-SPEC-000103

Thermal Systems Spec

431-SPEC-000091

LRO Electrical Systems Spec

431-SPEC-000008

Mechanical Systems Spec

431-SPEC-000012

LRO Mission Assurance Reqt

431-RQMT-000174

LRO Mission Concept of Operations

431-OPS-000042

LRO Data Management Plan

431-PLAN-000182

LRO Observatory Verification Plan

431-PLAN-000101

LRO Contamination Control Plan

431-PLAN-000110

LRO Integration and Test Plan

431-PLAN-000100

LRO Radiation Reqt

431-RQMT-000045

DRLE Instrument Requirements

DRLE Instrument Performance RD

JPL-D-32399

DRLE Functional Requirements Doc

JPL-D-32375

DRLE Data Management Plan

JPL-D-32477

DRLE Data Product Specification

JPL-D-32400

LRO Spacecraft Payload Assurance

Implementation Plan

431-PLAN-000131

LRO Mechanical Systems Req’ts

431-RQMT-000183

Thermal Level III Requirements

431-RQMT-000205

Electrical Systems Reqt Doc

431-RQMT-000140

C&DH System Requirements

431-RQMT-000168

C&DH EICD

431-ICD-000141

C & DH MICD/TICD

431-ICD-TBD

LRO Flight Software Rqmt

431-RQMT-000139

LRO Communication

Systems Requirements

431-RQMT-000137

Comm System EICD

431-ICD-000146

RF ICD Between LRO and the Lunar

Network

451-RFICD-LRO/LN

Flight Dynamics Specification

431-SPEC-000184

LRO GNC ACS Spec

431-SPEC-000162

LRO PROP Subsystem SOW &

SPEC

431-PROP-000017

Propulsion to Spacecraft EICD

431-ICD-000147

Propulsion to Spacecraft MICD

431-ICD-TBD

LRO Electrical Power Subsystem

Spec

431-SPEC-000013

Power Subsystem Electronics EICD

431-ICD-000142

Solay Array EICD

431-ICD-000150

Battery EICD

431-ICD-000151

Mini RF Electrical ICD

431-ICD-000152

Mini RF Data ICD

431-ICD-000160

Mini RF TICD

431-ICD-000159

Mini RF Mechanical ICD

431-ICD-000158

Mini RF PAIP

431-PLAN-000181

Detailed Mission Reqt (DMR) for

LRO Ground System

431-RQMT-000048

LRO Ground System ICD

431-ICD-000049 CRaTER Data ICD

431-ICD-000104

LAMP Data ICD

431-ICD-000106

LROC Data ICD

431-ICD-000109

LEND Data ICD

431-ICD-000107

DLRE Data ICD

431-ICD-000105

LOLA Data ICD

431-ICD-000108

CRaTER TICD

431-ICD-000118

LAMP TICD

431-ICD-000115

LROC TICD

431-ICD-000114

LEND TICD

431-ICD-000119

DLRE TICD

431-ICD-000116

LOLA TICD

431-ICD-000117

CRaTER Mechanical ICD

431-ICD-000085

LAMP Mechanical ICD

431-ICD-000087

LROC Mechanical ICD

431-ICD-000090

LEND Mechanical ICD

431-ICD-000088

DLRE Mechanical ICD

431-ICD-000086

LOLA Mechanical ICD

431-ICD-000089

CRaTER PAIP

32-01204

LAMP PAIP

PAIP-05-15-11239

LROC PAIP

MSSS-LROC-7001

LEND PAIP

LEND PAIP 01

DLRE PAIP

JPL-D-31796

LOLA PAIP

LOLA-PLAN-0003

8/12/2005

LAMP Instrument Requirements

LAMP IRD

11239-IRD-01

LAMP Data Management Plan

11239-DMP-01

CRaTER Instrument Requirements

CRaTER IRD

32-01205 01

CRaTER Data Management Plan

LOLA Instrument Requirements

LOLA Science & Functional RD

LOLA-RQMT-00002

LOLA Data Management Plan

LOLA-PLAN-00005

LEND Instrument Requirements

LEND IRD

LEND IRD 01

LEND Data Management Plan

LEND DMP 01

Instrument Requirements

LROC IRD

MSSS-LROC-001

LROC Data Management Plan

MSSS-LROC-010

RESOURCE ALLOCATIONS

LRO Pointing & Alignment Alloc

431-SPEC-000113

LRO Tech Resoures Alloc

431-SPEC-000112

20

LRO Overview

Back-Ups

21

LRO Timeline to Confirmation

Instrument

Selection

Project Funded

InstrumentK.O. Mtg.

1/05 2/05 3/05 4/05 5/05 7/056/05 8/05 9/05

InstrumentAccommodation

Rvw.

Instrument ContractAwards

Mission SRR

Requirements Definition & Preliminary Design

Level 1Requirements

Baselined

LEND US-Russian Implementing Agree draft into HQ-State Dept. review.

10/05 11/05 12/05

IPDRs

Mission PDR

IBR

NAR

Baseline Establishment Phase C/D/E

Ground SRR

22

LRO Lifecycle Cost Estimate

• LRO LCC estimate is in process.

Initial Cost Estimate ($M)

Management & Sys. Engr. 25

Spacecraft 120

Instruments

CRaTER 6.8

Diviner 11.9

LAMP 5.5

LEND 5.1

LOLA 19.7

LROC 17.3

Launch Vehicle 90

Ground Network/MOC & Mission Ops. 39

I&T 11

Reserve 56

Total 407

Initial Guiding Boundary Conditions• 2008 launch•Delta II class LV•Accommodate Investigations sought

by ORDT/AO• $400M cost target put forth in FAD

Conceptual Cost Estimates• Parametric estimate based on historical

data for recent mission with similarities• Application of simple CERsby Project

Initial Grassroots Estimates• Done at subsystem level

-Subsystem estimates experience based- Instruments per AO

LCC estimate for Confirmation Process• Results from reconciliation of Grassroots

& RAO estimates. Reviewed by GSFC PMC

Refined Grassroots Estimates• Done at subsystem level

-Subsystem estimates prelim. design based- Instruments per proposals, C/D/E contracts

In Progress

GSFC RAO Cost Modeling• Mission input data defined/delivered

by Project

In Progress

POP 05

POP 06

“Discovery Class”Initial Guiding Boundary Conditions• 2008 launch•Delta II class LV•Accommodate Investigations sought

by ORDT/AO• $400M cost target put forth in FAD

Conceptual Cost Estimates• Parametric estimate based on historical

data for recent mission with similarities• Application of simple CERsby Project

Initial Grassroots Estimates• Done at subsystem level

-Subsystem estimates experience based- Instruments per AO

LCC estimate for Confirmation Process• Results from reconciliation of Grassroots

& RAO estimates. Reviewed by GSFC PMC

Refined Grassroots Estimates• Done at subsystem level

-Subsystem estimates prelim. design based- Instruments per proposals, C/D/E contracts

In Progress

GSFC RAO Cost Modeling• Mission input data defined/delivered

by Project

In Progress

POP 05

POP 06

“Discovery Class”