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
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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
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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
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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)
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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
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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
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• 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
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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
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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.
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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
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
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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
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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
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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
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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