LRO Mission Overview
Craig Tooley - GSFC/431
September 7, 2005
1
2008 Lunar Reconnaissance Orbiter (LRO)
First Step in the Robotic Lunar Exploration Program
Robotic 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
2
Investigation Background
•
LRO provides major scientific and exploration benefit by 2009
–
–
–
•
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.
–
–
•
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)
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)
3
Benefit Example: Identifying Landing Sites & Resources
Temperature mapping (find cold traps)
Resource imaging
Polar Topography/shadow mapping
4
LRO Mission Overview
Flight Plan – Direct using 3-Stage ELV
•
•
•
•
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.
Moon at encounter
Cis-lunar transfer
5.1978 day transfer
Launch C3 –2.07 km2/s2
Sun direction
Lunar Orbit
Cis-Lunar Transfer
1-day
Insertion and Circularization
Impulsive Vs (m/s)
1 – 344.24
2 – 113.06
3 – 383.91
4 – 11.45
5 – 12.18
100 and 50km
mission orbits
Earth
6-hour orbit
Nominal Cis-lunar Trajectory
12-hour orbit
Solar Rotating Coordinates
5
LRO Mission Overview
Orbiter
LRO Instruments
INSTRUMENT
MODULE
•
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.
CRaTER
LROC
LOLA
AVIONICS
MODULE
LAMP
PROPULSION
MODULE
SOLAR
ARRAY
Mini-RF
LRO Preliminary Design
INSTRUMENT
MODULE
AVIONICS
MODULE
HGA
LAMP
PROPULSION
MODULE
LEND
Preliminary LRO Characteristics
Diviner
Dry: 603 kg
Mass
1317 kg
Fuel: 714 kg
SOLAR
ARRAY
Power
Measurement
Data Volume
745 W
575 Gb/day
6
Competitively Selected LRO
Instruments Provide Broad Benefits
INSTRUMENT
CRaTER
(BU+MIT)
Measurement
Exploration
Benefit
Science
Benefit
Tissue equivalent
response to radiation
Safe, lighter weight
space vehicles that
protect humans
Radiation conditions
that influence life
beyond Earth
300m scale maps of
Temperature, surface
ice, rocks
Determines conditions
for systems operability
and water-ice location
Maps of frosts in
permanently shadowed
areas, etc.
Locate potential waterice (as frosts) on the
surface
Hydrogen content in and
neutron radiation maps
from upper 1m of Moon at
5km scales, Rad > 10 MeV
Locate potential waterice in lunar soil and
enhanced crew safety
~50m scale polar
topography at < 1m
vertical, roughness
Safe landing site
selection, and
enhanced surface
navigation (3D)
Geological evolution
of the solar system by
geodetic topography
1000’s of 50cm/pixel
images (125km2), and
entire Moon at 100m in
UV, Visible
Safe landing sites
through hazard
identification; some
resource identification
Resource evaluation,
impact flux and
crustal evolution
Cosmic Ray Telescope
for the Effects of Radiation
Diviner
(UCLA)
LAMP
(SWRI)
Lyman-Alpha Mapping Project
LEND
(Russia)
Lunar Exploration Neutron Detector
LOLA
(GSFC)
Lunar Orbiter Laser Altimeter
LROC
(NWU+MSSS)
Lunar Recon Orbiter Camera
Improved
understanding of
volatiles in the solar
system - source,
history, migration and
deposition
7
LRO Spacecraft Systems Block Diagram
8
LRO C&DH Architecture Block Diagram (New-8/29/05)
Instruments
L
E
N
D
SUBSYSTEMS
(ACS, PSE,
PRO/DEP)
NAC1 NAC2 WAC
D
i
v
i
n
e
r
C
R
A
T
E
R
L
O
L
A
LROC
SpaceWire
FPGA
32 Mbps
1553B
5 Heater out
Unsw.+28V
8 to 32Mbps
(Max.)
Hi-Rate
Tlm
125Mbps
(Max.)
S-Xpndr
HGA
Ka-Xmtr
38.4Kbps Serial IF
(UART)
1Mbps
Low-Rate
Tlm 2Mbps Max
& Command 4Kbps
#Changed
ATA IF
I/O
L
A
M
P
SpaceWire
FPGA
GD-DDA
Sw. +28V (Heater)
UnSw. +28V (SBC)
MiniRF
2 Mbps Max. (HK Downlink)
2 Mbps Max. (LAMP Tlm)
125 Mbps (Science Downlink)
Unsw. +28V
HGA
Gimbals
Sw. +28V (Ka-Comm)
UnSw. +28V (S-Comm)
1PPS
1553
Summit
LVPC
( A)
(B)
Thermal
Card
BAE
1553
Summit SpaceWire
ASIC
SpaceWire
FPGA
RAD750
SBC
GD-DIB
#
6U-cPCI
3U-cPCI
+3.3V (B), +5V (B)
KaComm
SpaceWire
FPGA
SComm
cPCI Backplane
+/-15V, +5V, +3.3V (A)
C&DH
HK/IO
SpaceWire
FPGA
+28V Power
SpaceWire (HSB)
Backplane
1553B (LSB)
9
LRO Spacecraft Systems Capabilities
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 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
10
Ground System Architecture Overview
11
LRO Mission Phases Overview
No
1
Phase
Pre-Launch/ Launch
Readiness
2
Launch & Lunar
Transfer
3
Sub-Phases


Space Segment Readiness
Ground Segment Readiness
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



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.


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.







Measurements (Routine Ops)
Station-keeping
Momentum Management
Instrument Calibrations
Lunar Eclipse
Yaw Maneuver
Safe Mode
Orbiter Commissioning
4
Routine Operations
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.
One year of nominal science collection in the 50 (+/- 20) km orbit.
Extended 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 operations
may be to perform relay comm. operations. Alternatively additional measurement
operations may be performed for a shorter period in a continued low orbit.
End-of-Mission Disposal
Includes planning and execution of end-of-life operations. LRO will impact lunar
surface.
5
6
Description
12
LRO Project Organization
LRO Project Manager
C. Tooley
Project Scientist
G. Chin
600
Deputy Project Manager
TBD
System Assurance
Manager
R. Kolecki 300
Deputy Project Manager/
Resources
P. Campanella
Safety Manager
D. Bogart
Manufacturing Engineer
N. Virmani
Materials Engineer
P. Joy
RM Coordinator
A. Rad
Financial
Manager
B. Sluder
400
Mission Business Mgr.
J. Smith
Orbiter Systems Engineer
M. Pryzby
GN&C Systems Engineer
E. Holmes
General Business
D. Yoder/P. Gregory
Scheduling
A. Eaker
Operations System Engineer
M. Beckman/D. Folta
SW/HW Systems Engineer
C. Wilderman
Mission Success Engineer
K. Deily
CM/DM
D. Yoder
Contamination Control
C. Lorenston
MIS
A. Hess/J. Brill
Launch Vehicle
Manager
T. Jones
400
Payload Systems
Manager
A. Bartels
500
ACS Hardware
J. Simpson
J. Baker
L. Hartz
Flight Dynamics
M. Beckman/D. Folta
Power
T. Spitzer
400
Payload Systems
Engineers
Communications
J. Soloff
ACS Analyst
J. Garrett
Ground Network
& Operations
R. Saylor
400
C&DH
Q. Nguyen
Software
M. Blau
200
Avionics Systems Engineer
P. Luers
Project Support
Manager
K. Opperhauser
500
400
Mission System
Engineer
M. Houghton 500
400
Orbiter
I & T Lead
J. Baker
Contracting
Officer
J. Janus
M. Reden
CRaTER
D. Spence
Boston University
LROC
M. Robinson
Northwestern Univ.
Diviner
D. Paige
UCLA
Mini - RF
LEND
I. Mitrofanov
LOLA
D. Smith
NAWC
ISR, Moscow
GSFC
LAMP
S. Stern
SWRI
Thermal
C. Baker
Propulsion
C. Zakrzwski
Electrical
R. Kinder
Mechanical
G. Rosanova
08/31/2005
13
LRO Mission
Schedule
LRO Mission Schedule
Mission PDR target: November 14
Ver. 0.9
7/31/05
2004
CY
Q2
Q3
2005
Q4
Q1
Q2
AO Release
Q3
IPDR
LRO Mission Milestones
2006
Q4
Q1
PDR
Q2
ICDR
Q3
2007
Q4
CDR
Q1
M RD
SRR
Q3
2008
Q4
Q1
Q2
2009
Q3
Q4
FOR/ORR
M OR
Conf.
Review
Q1
Q2
Q3
Q4
Launch
IPSR
IBR
AO Sel.
Q2
PSR
PER
M RR
LRR
Mission Feasibility Definition
Payload Proposal
Development
Instr. PDR's
9/6-9/29
Payload Preliminary Design
System Definition
S/C &GDS/OPS Preliminary
Design
Payload Design (Final)
(1M Float)
Spacecraft Design (Final)
Network Decision
GDS/OPS Definition/ Design
Payload Fab/Assy/Test
(7 Instruments)
Payload com plete (Final Delivery to I&T)
(LAMP/LOLA/LROC/Diviner/CraTer/LEND/M ini-RF)
S/C Fab/Assy/Bus Test
S/C com plete (Final delivery to I&T)
GND Net Test Ready
GDS/OPS Development
Implemention & Test
S/C BUS
Integration and Test
(1M Float)
Payload
Envir. Testing
(1M Float)
Launch Site Operations
Ship to KSC
(1M Float)
Launch
Mission Operations
14
LRO Project Overall Status
•
Project almost fully staffed
–
–
•
Project infrastructure in-place
–
•
45 civil servants & 23 support contractor at present (FTEs & WYEs)
Project level augmentations in-work as Program/Project resources are phased out.
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
15
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
–
–
–
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
–
•
Low lunar polar orbit is significantly different than Mars missions
where most instrument heritage is from.
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
16
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.
17
LRO Requirements Development
Roadmap
LRO Level 1 Requirements
ESMD-RQMT-0010
Project Requirements
Measurement Requirements &
Instrument Specific Expected Data Products
Level 2 Requirement Synthesis
LRO Mission Requirements
Document
431-RQMT-000004
Mini-RF
Allocations
Electrical Spec
LROC
LOLA
LAMP
LEND
CRaTER
Diviner
Mechanical Spec
Thermal Spec
Level 2
Performance & SOC
Requirements
Operations
Contamination
Radiation
Mission Assurance
Launch Vehicle
Spacecraft, Instrument & Ground
Level 3 Requirements Documents & ICDs
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
Preliminary Engineering
18
LRO Mission Requirements Hierarchy
CM Key
ESMD
Document
ESMD-RLEP-0010
LEVEL 1
Released
LRO Level 1
Requirements
Document
In CCB for Release
Document
DRAFT
Launch
Vehicle
LRO Mission
LEVEL 2
431-RQMT-000004
Mission Requirements
Document (MRD)
Mission Requirements Documents
JPL-D-32399
JPL-D-32375
DRLE Instrument
Performance RD
DRLE Functional
Requirements Doc
431-RQMT-000174
431-SPEC-000112
431-SPEC-000113
431-PLAN-000100
431-PLAN-000110
431-SPEC-000012
431-SPEC-000008
431-SPEC-000091
LRO Mission
Assurance Reqt
LRO Tech
Resoures Alloc
LRO Pointing &
Alignment Alloc
LRO Integration
and Test Plan
LRO Contamination
Control Plan
Mechanical
Systems Spec
LRO Electrical
Systems Spec
Thermal Systems
Spec
431-RQMT-000045
431-PLAN-000101
431-RQMT-000092
431-HDBK-000093
431-SPEC-000103
LRO Radiation
Reqt
LRO Observatory
Verification Plan
Thermal Modeling
Reqt Document
Component MICD
Guidelines HDBK
LRO SpaceWire
Spec
MISSION
ASSURANCE
11239-IRD-01
32-01205 01
RESOURCE ALLOCATIONS
LOLA-RQMT-00002
LEND IRD 01
MSSS-LROC-001
SYSTEMS
LAMP IRD
LOLA Science &
Functional RD
CRaTER IRD
LEND IRD
JPL-D-32400
11239-DMP-01
DRLE Data
Management Plan
DRLE Data Product
Specification
LAMP Data
Management Plan
LAMP Instrument
Requirements
DRLE Instrument Requirements
CRaTER Data
Management Plan
CRaTER Instrument
Requirements
To Be Written
8/12/2005
MDC 00H0016
Delta II Payload
Planners Guide
431-REF-000172
GENERAL SPECS
LV Questionnaire
LROC IRD
431-RQMT-000157
JPL-D-32477
Document
LOLA-PLAN-00005
LEND DMP 01
MSSS-LROC-010
LOLA Data
Management Plan
LOLA Instrument
Requirements
LEND Data
Management Plan
LEND Instrument
Requirements
LROC Data
Management Plan
Instrument
Requirements
Mini RF
Requirements and
Goals Document
Tech Demo Requirements
431-OPS-000042
431-PLAN-000182
LRO Mission
Concept of
Operations
LRO Data
Management Plan
AFSPCMAN 91-710
Range Safety User
Requirements
GROUND/OPERATION
LRO Orbiter
LEVEL 3
Ground
System
431-RQMT-000048
Detailed Mission
Reqt (DMR) for
LRO Ground
System
431-ICD-000049
LRO Ground
System ICD
Spacecraft Bus
431-PLAN-000131
LRO Spacecraft
Payload Assurance
Implementation
Plan
Mission
Assurance
431-RQMT-000168
C&DH System
Requirements
431-ICD-000141
C&DH EICD
431-RQMT-000137
431-SPEC-000162
LRO
Communication
Systems
Requirements
LRO GNC ACS
Spec
431-ICD-000146
431-PROP-000017
431-ICD-000142
LRO PROP
Subsystem SOW &
SPEC
Power Subsystem
Electronics EICD
Comm System
EICD
ACS
431-RQMT-000183
431-ICD-TBD
LRO Mechanical
Systems Req’ts
C & DH
MICD/TICD
451-RFICD-LRO/LN
Mechanical
C&DH
RF ICD Between
LRO and the Lunar
Network
Propulsion to
Spacecraft EICD
431-RQMT-000205
431-RQMT-000139
Communication
431-ICD-TBD
Thermal Level III
Requirements
LRO Flight
Software Rqmt
Thermal
FSW
431-SPEC-000184
Electrical Systems
Reqt Doc
Flight Dynamics
Specification
Electrical
Flight Dynamics
431-SPEC-000013
431-ICD-000152
431-ICD-000094
431-ICD-000096
431-ICD-000099
431-ICD-000097
431-ICD-000095
431-ICD-000098
LRO Electrical
Power Subsystem
Spec
Mini RF Electrical
ICD
CRaTER Electrical
ICD
LAMP Electrical
ICD
LROC Electrical
ICD
LEND Electrical
ICD
DLRE Electrical
ICD
LOLA to Spacecraft
Electrical ICD
431-ICD-000160
431-ICD-000104
431-ICD-000106
431-ICD-000109
431-ICD-000107
431-ICD-000105
431-ICD-000108
Mini RF Data ICD
CRaTER Data ICD
LAMP Data ICD
LROC Data ICD
LEND Data ICD
DLRE Data ICD
LOLA Data ICD
431-ICD-000118
431-ICD-000115
431-ICD-000114
431-ICD-000119
431-ICD-000116
431-ICD-000117
431-ICD-000159
431-ICD-000150
Mini RF TICD
Solay Array EICD
431-ICD-000158
431-ICD-000151
Mini RF Mechanical
ICD
CRaTER TICD
LAMP TICD
LROC TICD
LEND TICD
DLRE TICD
LOLA TICD
431-ICD-000085
431-ICD-000087
431-ICD-000090
431-ICD-000088
431-ICD-000086
431-ICD-000089
CRaTER
Mechanical ICD
LAMP Mechanical
ICD
LROC Mechanical
ICD
LEND Mechanical
ICD
DLRE Mechanical
ICD
LOLA Mechanical
ICD
431-ICD-000147
Propulsion to
Spacecraft MICD
Propulsion
431-RQMT-000140
Instruments
Battery EICD
431-PLAN-000181
Power
Mini RF PAIP
32-01204
PAIP-05-15-11239
MSSS-LROC-7001
LEND PAIP 01
JPL-D-31796
LOLA-PLAN-0003
CRaTER PAIP
LAMP PAIP
LROC PAIP
LEND PAIP
DLRE PAIP
LOLA PAIP
CRaTER
LAMP
LROC
LEND
DRLE
LOLA
Tech Demo
19
LRO Overview
Back-Ups
20
LRO Timeline to Confirmation
Instrument
Contract
Awards
Project
Funded
Instrument
Selection
Level 1
Requirements
Baselined
Mission SRR
Requirements Definition & Preliminary Design
1/05
2/05
3/05
Instrument
K.O. Mtg.
4/05
5/05
6/05
7/05
8/05
9/05
Instrument
Accommodation
Rvw.
LEND US-Russian
Implementing Agree
draft into HQ-State
Dept. review.
IPDRs
IBR
Baseline Establishment
10/05
11/05
Ground SRR
Phase C/D/E
12/05
Mission PDR
NAR
21
LRO Lifecycle Cost Estimate
Initial Cost Estimate ($M)
Management & Sys. Engr.
25
Spacecraft
120
• LRO LCC estimate is in process.
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
22