1 Lunar Reconnaissance Orbiter (LRO) Overview CRaTER PDR 6/27/2005 Craig Tooley.

1

Lunar Reconnaissance Orbiter (LRO) Overview

CRaTER PDR

6/27/2005

Craig Tooley

2NASA’s Goddard Space Flight Center

Craig Tooley/431 5/22/2005

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



Develop an understanding of the Moon in support of human exploration (hazards, topography, navigation, environs)

Understand the current state and evolution of the volatiles (ice) and other resources in context

Biological adaptation to lunar environment (radiation, gravitation, dust...)

GEOLOGYGEOLOGY

EnvironsEnvirons

Prepare for Human Exploration

Prepare for Human Exploration

When • Where • Form • Amount

Topography & Environments

Polar Regions

Human adaptation

ICE

(Resources

)

LRO Mission OverviewScience and Exploration Objectives



Lunar Reconnaissance Orbiter (LRO) Mission

LRO Payload

• 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.

Early LRO Conceptual Design

LRO Timeline

2005 2006 2007 20082004 2009

4/6 FBO

6/18

AO Release

12/22

AO Select7/26 PDR

10/15

Confirm

6/26 CDR 4/2 MOR 10/15

Instrument

Delivery

12/3 PER

10/15 LRD

7/15 MRR

11/15 EOM

Extended

Mission



LRO Mission OverviewLRO Payload – Instruments & Data Products

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

Landing hazards and

some resources

LROC

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

Precision, safe navigation (3D)

LOLA

Maps of water ice in upper 1 m of Moon at

5km scales

Ice in regolithdown to 1 m ?

LEND

Maps of frosts in permanently

shadowed areas, etc.

Frosts? “atmosphere”?

LAMP

300m scale maps of Temperature, surface

ice, rocks

Surface temperatures

Diviner

Tissue equivalent response to radiation

Shielding constraints

CRaTER

DeliverablesBenefitInstrument

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

Landing hazards and

some resources

LROC

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

Precision, safe navigation (3D)

LOLA

Maps of water ice in upper 1 m of Moon at

5km scales

Ice in regolithdown to 1 m ?

LEND

Maps of frosts in permanently

shadowed areas, etc.

Frosts? “atmosphere”?

LAMP

300m scale maps of Temperature, surface

ice, rocks

Surface temperatures

Diviner

Tissue equivalent response to radiation

Shielding constraints

CRaTER

DeliverablesBenefitInstrument

(BU+MIT)

(UCLA)

(SWRI)

(Russia)

(GSFC)

(NWU+MSSS)



LRO Project Status

• All instrument TIM completed.• Level 1 ESMD requirements document draft released for review, to

go to ESMD PMC during June.• MRD (level 2 requirements) released for review and PDR use.• Propulsion subsystem procurement RFP to be released by end of

June.• Ground Network requirements baselined, acquisition of 18m S/Ka

antenna at WSGT in progress.• LRO directed to accommodate Mini-RF as technology Demonstration

– Modest impact to mission resources– Impacts ongoing spacecraft design – slip PDR to September 2005

• RLE Program and LRO Project moved from HQ SMD to HQ ESMD, transition in progress. – May have some near-term impacts to planned review activites

• LRO anticipates no further funding issues in FY05/06



LRO Mission OverviewOrbiter

Space Segment Design

LRO Configuration

Preliminary System Block Diagram

Preliminary LRO Characteristics

Mass 1272 kg

Power ( bus orbit ave.) 700-800 W

Measurement Data Volume

575 Gb/day

S-Xpndr

Ka-XmtrHGAHi-Rate

Tlm

Low-RateCmds & Tlm

Battery

PP

Propellant TankPropellant Tank

PP

RRRR

NCNCPressurantTank

PPNCNC

Pro

pu

lsion

Discretes

MIL-STD-1553 Network

SBC

Thermal

HK / IO

SSR

C&DH

Comm

Po

wer

Bu

s

ST(2)

IMU

CSS(8)

LAMP

LROC

LOLA

LAMP Sci. & HK

LVPC

HGAGimbals

PSE

SAM

Sw. andUnsw.

+28V PwrServices

OM

PMC

OM

OM

Gimbal Ctl

Prop/Dep-A

Prop/Dep-B

Prop/Dep-C

Prop/Dep-D

Gimbal CtlPDE

SA & HGDeploy

Actuation

Omnis

IRW(4)Thermistors

Closed Loop HtrsHeat Pump LoopC&DH LVPC HK

SpaceWire Network

LEND

Diviner

CRaTER

H/W DecodedCommandDiscretes

Unsw. + 28V

SAGimbals

Solar Array

Unsw. + 28V

SpaceWire

MIL-STD-1553

SSR Sw. + 28V

*

**

*

**ACE Hardware

Mini-RF



• Launch on a Delta II class 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 is designed to be capable of performing an extended mission of up to 4 additional years in a low maintenance orbit.

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



LRO Mission Overview Ground System

• LRO Ground System and Mission Operations concepts are established

LRO Operations Synopsis •3x 45 min of Ka-band downlink/day• Near continuous S-band Tracking 30min/orbit (near-side) • Plan 1 command upload/day• Orbit adjust required every ~ 4 weeks• MOC routes Level 0 data to PI SOCs

• SOCs deliver to PDS• MOC maintains short term archive

LRO Ground Network Baseline Configuration

• 18m Ka/S station at White Sands w/ shared back-up• 2 X Upgraded S-Band Stations situated for continuous coverage• Additional S-band STDN back-ups

Ground Network

S-Band Station Ka-Band Station

S-B

and

CM

D/T

LM

Net

wo

rk

S-Band Telemetry

LRO R-TCommands

S-Band TrackingData

MeasurementData Files

CFDPStatus

Information/Ack

Mission Operations Center(GSFC)

Real-TimeTelemetry &

Control

Level – 0Data

Processing

Trending Operations

Mission Planning

Data Storage

Flight Dynamics (GSFC)

FDF

S-Band Tracking Data

Data Distribution

System

Flight DynamicsProducts

SpacecraftAttitude

Data

S-Band Telemetry

Ka-Band DataFiles

S-Band Commands

CFDP Status Information/Ack

LROC SOC

Level-0 ScienceData

Science PlanningProducts

Planetary Data System(Geosciences Node)

LRO Ground Data System Architecture

LRO Ka-Band D/L: 125 Mbps LRO S-Band D/L: ~16 to 32 kbps (Nominal) LRO S-Band U/L: ~4 kbps S-Band Data includes R-T HSK Data Ka-Band Data includes all Science data packets and

stored HSK Plan 1 command upload per day Near continuous tracking 30 min per orbit (Minimum)

Ka-B

and TLM

FDAB

Network Acq. Data

LOLA SOC LEND SOC

CRaTER SOC

Diviner SOC LAMP SOC

Mission Planning Products

Measurement/HK Data Files

Processed MeasurementProducts

HousekeepingData Files

Instrument Module

Propulsion Module

ULTRAFLEXSolar Array

High Gain Antenna

Avionics Module

X

Y

Z

Instrument Module

Propulsion Module

ULTRAFLEXSolar Array

High Gain Antenna

Avionics Module

X

Y

Z

X

Y

Z

Real-Time HK Data

Processed Measurement Products



Mission Phases OverviewMission Phase Sub-Phase

Space Segment Readiness

Ground Segment Readiness

Launch & Ascent

Separation & De-Spin

Deployment & Sun Acquisition

Lunar Cruise

Lunar Orbit Insertion (LOI)

Orbiter Commissioning

Spacecraft Commissioning

Integrated Instrument Commissioning

Routine Measurements

Station-Keeping ManeuversInstrument

Calibrations

Yaw Maneuver

Lunar Eclipse

Safe Mode

Extended Mission Operations

End-of-Mission Disposal

DescriptionIncludes instrument, spacecraft, and orbiter integration and test. Also includes launch vehicle preparations and payload integration.

Launch and Lunar Transfer

Starts approximately L-18 hours with the execution of the launch countdown script for the space segment. Activities include launch and the rocket ascent phase ending just prior to orbiter separation.

Starts with the orbiter detecting separation from the launch vehicle. The orbiter is de-spun to rates that allow the on-board systems to deploy the solar array and acquire the Sun.

Prelaunch OperationsIncludes ground system integration and test, operations testing, and end-to-end system testing.

Starts after the orbiter is de-spun and the orbiter deploys the solar array. After the deployment, the orbiter looks for and acquires the Sun to enter into a power position state. The last activity in this sub-phase is to verify ground communications with the orbiter.

Integrated instrument commissioning will commissioning the instruments in parallel to minimize time. Instruments will be powered and functionally checked. Commissioning also includes instruments initial calibration/validation of instruments performance. The final step is to insert the orbiter into the mission orbit.

Begins the nominal measurement observations from the instruments. Instruments collect measurement data and is dumped to the LRO ground system. The LRO ground system collects and transfers the data to the Science Operations Centers for data processing.

Monthly station-keeping maneuvers are needed to maintain the nominal mission orbit. Each month, one orbit will be designated to perform the maneuver.

Measurement Operations

After the ~1 year of nominal operations, the orbiter will enter extended mission operations. Goals for extended missions operation may include communication relay and extended measurement collections.

At end of mission, NASA requires disposal of LRO by de-orbiting S/C into lunar surface

Mission Overview

Monthly instruments calibrations will be coordinated approximately on the same day as the monthly orbit maintenance activities. A integrated calibration plan will be developed and Twice a year the orbiter will require a 180° yaw maneuver to maintain the Sun on the correct side of the orbiter.

Sub-phase last approximately 4-5 days during the cruise to the Moon. During this period, the initial checkout and orbiter commissioning is started. The period ends at the start of the first Lunar Orbit Insertion burn.LOI includes 4-5 separate thruster maneuvers that allow LRO to capture into the commissioning orbit.

Potentially twice a year, Lunar eclipses may force the orbiter to be placed into a low power mode. The low power mode will allow the orbiter to survive and minimize impact on science operations.

Orbiter will have capabilities to detect and place the itself into lower modes. The lowest mode will be a low power, minimal hardware mode that will allow the orbiter to survive long periods of time to enable the ground to analysis and correct the problem.

Spacecraft commissioning include activities to power on components and functionally check out spacecraft systems. Some activities will be started during the lunar cruise phase.



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

6/1/05

LRO Mission Schedule

Task

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

Conf.

ICDR

CDR

MOR

IPSR

PER

FOR/ORR

MRR

PSR

LRR

LRO Launch

Instr. PDR's6/16-8/25

Network Acquisition

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

Ship to KSC

LRO LAUNCH

(1M Float)

s/c bus

s/c subsys

GDS

s/c subsys

s/csubsys

Payload(1M Float)

(1M Float)

Ver. 0.7

(1M Float)

CY



LRO Requirements Development & Flow-Down

• NASA HQ– ORDT defined measurement objectives– Established the Robotic Lunar Exploration Program (RLEP)– ESMD defines LRO level 1 requirements (in draft review)

• RLEP– Specifies relevant GSFC guidelines and direction– Develops MAR and Project Plan– LRO Project baselined as 1st mission

• LRO Project Plan• PAIP• SEMP• MRD (in draft release)

– Level 2 requirements– Level 3 requirements



LRO Requirements Development and Flowdown

Robotic LunarExploration

Program* MAR* RLEP Project Plan

ORDT - ScienceObjectives

* Characterize lunar radiation environment and mitigations* Produce 3D global map* Assess resources including H20 and landing sites at poles* Global resource mapping

NASA HQ Directives* Budget Constraints* Schedule Constraints* Russian Federal Space Agency Partnership* NPR, NPD

LRO ConceptFormulation

Studies* Architecture Trades* Implementation Trades* Instrument Trades* S/C Design Studies

LRO Mission OperationsConcept

* Nominal Operations: Data Flows Spacecraft Ops Ground Element Ops* Special Operations: Launch and Early Orbit End of Mission Attitude Maneuvers Lunar Orbit Maneuvers Extended mission* Contingency Operations: Data Flows Spacecraft Ground Elements

Level 1 LRO Requirements* Measurement Requirements* Lifetime* Launch* Orbit* S/C* S/C Instrument* Accommodations* Measurement Investigation* Data Policies and Validation

Level 2 LRO MissionRequirements

* Space Segment: Instruments Spacecraft* Ground Segment: Ground Station Mission Op Center Science Op Center Ground Network Data Distribute & Archive* Overall Mission Launch Services:* Instruments* Process Requirements* Science Requirements

LRO Project* LRO Project Plan* PAIP* Configuration Management

LRO SystemsEngineering Plan

Requirement ManagementDesign TrackingRisk ManagementResource Tracking

PDR

LRO Mission ElementRequirements

* Instruments LOLA LROC LEND Diviner LAMP CRaTER* Spacecraft* Ground NASA Mission Operations 18m Ground Station Ground Validation & Cal Global Lunar Data Processing

GSFCManagementGuidelines

* GPR* GSFC-STD-1000* GEVS

Accept L2 RequirementsPresent Verification Plan

Review & AcceptElement Requirements

Verify Flow Down



LRO Instrument Requirements Documents

LRO Program Requirements DocumentESMD Controlled Document

Contains Level 0 & 1

LRO Mission Requirements Document 431-RQMT-00004 Contains Level 2

RLEP Mission Assurance Requirements

430-RQMT-000006

Payload Assurance Implementation Program

CRaTER, Diviner, LAMP, LEND, LOLA, LROC

LRO Electrical Systems ICD 431-ICD-000008

CRaTER Electrical ICD431-ICD-00094

DLRE Electrical ICD431-ICD-00095

LAMP Electrical ICD431-ICD-00096

LEND Electrical ICD431-ICD-00097

LOLA Electrical ICD431-ICD-00098

LROC Electrical ICD431-ICD-00099

CRaTER Data ICD431-ICD-000104

DLRE Data ICD431-ICD-000105

LEND Data ICD431-ICD-000107

LOLA Data ICD431-ICD-000108

LAMP Data ICD431-ICD-000106

LROC Data ICD431-ICD-000109

LRO Radiation Requirements 431-RQMT-000045

Contamination Control Plan431-PLAN-000110

Observatory Verification Plan

431-PLAN-000101

Integration and Test Plan431-PLAN-000100

LRO Space WireSpecification

431-SPEC-000102

Mission Concept of Operations Document

431-OPS-000042

See pg.2

See pg.2

GEVSGSFC-STD-7000

NASA Software EngineeringRequirementsNPR 7150.2

Mechanical Environments and Verification Requirements

431-RQMT-000012



LRO Instrument Requirements Documents (cont.)

General Thermal Subsystem Specification

431-SPEC-000091

Thermal Modeling Requirements Document

431-RQMT-000092

CRaTER TICD431-ICD-000118

DLRE TICD431-ICD-000116

LAMP TICD431-ICD-000115

LEND TICD431-ICD-000119

LOLA TICD431-ICD-000117

LROC TICD431-ICD-000114

LRO Program Requirements DocumentESMD Controlled Document

Contains Level 0 & 1

LRO Mission Requirements Document 431-RQMT-00004 Contains Level 2

CRaTER MechanicalICD

431-ICD-000085

DLRE MechanicalICD

431-ICD-000086

LAMP MechanicalICD

431-ICD-000087

LEND MechanicalICD

431-ICD-000088

LOLA MechanicalICD

431-ICD-000089

LROC MechanicalICD

431-ICD-000090

MID Guidelines Handbook431-HDBK-000093

CRaTER Mechanical –Thermal

Interface Drawing

DLRE Mechanical – Thermal

Interface Drawing

LAMP Mechanical –Thermal

Interface Drawing

LEND Mechanical –Thermal

Interface Drawing

LOLA Mechanical – Thermal

Interface Drawing

LROC Mechanical –Thermal

Interface Drawing

LRO Ground System ICD431-ICD-000049

LRO Detailed Mission Requirements (DMR) for the LRO Ground System

431-RQMT-000048

Mission Concept of Operations Document

431-OPS-000042

1 Lunar Reconnaissance Orbiter (LRO) Overview CRaTER PDR 6/27/2005 Craig Tooley.

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