CRaTER Pre-Environmental Review
Instrument Summary
The CRaTER instrument is located on the LRO science deck as shown in the figure below. A
summary of key parameters for the instrument are included in the table below.
CRaTER Placement on the LRO Spacecraft
CRaTER Pre-Environmental Review
Instrument Summary 30 August 2007
Page 1 of 17
Summary of CRaTER Parameters
Mass Allocation
6.4 kg
Power Consumption Allocation
9.0 W
Size
13.5”x 9” x 6”
Function
Tissue equivalent response to radiation
Operational Temperature Range
-30о С to +30о С
Data Rate Allocation
89.1 Kbps
The primary goal of CRaTER is to characterize the global lunar radiation environment and its
biological impacts. In order to achieve this high-priority objective, the CRaTER investigation team
established the following interrelated investigation goals:
1. Measure and characterize that aspect of the deep space radiation environment, linear energy
transfer (LET) spectra of galactic and solar cosmic rays (particularly above 10 MeV), most
critically important to the engineering and modeling communities to assure safe, long-term,
human presence in space.
2. Develop a novel instrument, steeped in flight heritage, that is simple, compact, and
comparatively low-cost, but with a sufficiently large geometric factor needed to measure LET
spectra and its time variation, globally, in the lunar orbit.
3. Investigate the effects of shielding by measuring LET spectra behind different amounts and
types of areal density, including tissue-equivalent plastic.
4. Test models of radiation effects and shielding by verifying/validating model predictions of LET
spectra with LRO measurements, using high-quality Galactic Cosmic Ray (GCR) and Solar
Proton Event (SPE) spectra available contemporaneously on ongoing/planned NASA.
The investigation hardware consists of a single, integrated sensor and electronics box with simple
electronic and mechanical interfaces to the spacecraft. The CRaTER sensor front end design is based
on standard stacked-detector, cosmic ray telescope systems that have been flown for decades, using
detectors developed for other NASA flight programs. The analog electronics design is virtually
identical to the robust and flight-proven design of the NASA/POLAR Imaging Proton Spectrometer
that has been operating flawlessly on orbit since 1996. The digital processing unit is a simple and
straightforward design also based on similar instruments with excellent spaceflight heritage. No new
technology developments or supporting research are required for the final design, fabrication, and
operation of this instrument.
The CRaTER telescope consists of six ion-implanted silicon detectors, mounted in pairs and separated
by 2 cylinders of tissue-equivalent plastic (TEP). The detectors are all 35 mm in diameter. One of
each pair is 140 microns thick; the other of each pair is 1000 microns thick.
CRaTER Pre-Environmental Review
Instrument Summary 30 August 2007
Page 2 of 17
CRaTER Assembly Layout
L13.5”x W9” x H 6”
Weight 6.4 kg max.
CRaTER Theory of Operation
CRaTER Pre-Environmental Review
Instrument Summary 30 August 2007
Page 3 of 17
Summary of Spacecraft Mechanical Requirements flowed to the CRaTER Instrument
(Excerpts from the LRO Mechanical Systems Specification, 431-SPEC-000012 Rev D)
Tailored Instrument Limit Loads (based on instrument location)
Instrument
CRaTER
Diviner Instrument
Diviner DREB
LAMP
LEND
LOLA OTA
LOLA MEB
LROC NAC
LROC WAC
LROC SCS
Mini-RF Antenna
Mini-RF Electronics Boxes
Limit Load
(g, any direction)
8.0
8.0
12.0
9.0
8.0
8.0
9.0
8.0
9.0
8.5
12.0
12.0
CRATER Instrument X-Axis Sine Vibration Environment
Protoflight/Qualification
Frequency (Hz)
Level
5 - 9.9
1.27 cm D.A.
9.9 - 50
2.5 g’s
Acceptance
Frequency (Hz)
5 - 8.8
8.8 - 50
Level
1.27 cm D.A.
2.0 g’s
CRATER Instrument Y-Axis Sine Vibration Environment
Protoflight/Qualification
Frequency (Hz)
Level
5 - 15.6
1.27 cm D.A.
15.6 - 25
6.25 g’s
25 - 50
3.125 g’s
Acceptance
Frequency (Hz)
5 - 14.0
14.0 - 25
25 - 50
Level
1.27 cm D.A.
5.0 g’s
2.5 g’s
CRATER Instrument Z-Axis Sine Vibration Environment
Protoflight/Qualification
Frequency (Hz)
Level
5 - 17.1
1.27 cm D.A.
17.1 - 25
7.5 g’s
25 - 50
3.125 g’s
CRaTER Pre-Environmental Review
Instrument Summary 30 August 2007
Acceptance
Frequency (Hz)
5 - 15.3
15.3 - 25
25 - 50
Level
1.27 cm D.A.
6.0 g’s
2.5 g’s
Page 4 of 17
Generic Instrument Random Vibration Environment
Frequency (Hz)
20
20 - 50
50 - 800
800 - 2000
2000
Over All
Protoflight/Qual Level
0.026 g2/Hz
+6dB/Octave
0.160 g2/Hz
-6dB/Octave
0.026 g2/Hz
14.1 grms
Acceptance Level
0.013 g2/Hz
+6dB/Octave
0.080 g2/Hz
-6dB/Octave
0.013 g2/Hz
10.0 grms
CRaTER shock response spectrum
Frequency (Hz)
100
100 - 1000
1000 - 10000
CRaTER Pre-Environmental Review
Instrument Summary 30 August 2007
Level (Q=10)
15 g
+9.3 dB/Octave
525 g
Page 5 of 17
Summary of Spacecraft Thermal Requirements flowed to the CRATER Instrument
(Excerpts from the LRO Thermal Systems Specification, 431-SPEC-000091 Rev C)
Spacecraft Interface Temperature Range
Subsystem
CRATER
Component
S/C at I/F to CRATER
Op I/F Limit
-30 to +35
Temperature Range (C)
Qual I/F Limit
Surv I/F Limit
-40 to +35
-40 to +35
Temporal Gradient Requirements
Subsystem
CRATER
Component
S/C I/F to the Instrument
Temporal Gradient (C/min)
None
Spatial Gradient Requirements
Subsystem
CRATER
Component
S/C I/F to the Instrument
Spatial Gradient between mounting feet (C)
None
(Excerpts from the CRATER to Spacecraft Thermal ICD, 431-ICD-000119 Rev A)
CRATER Reference Location Temperature Limits
Min/Max Temp. Limits (°C)
#
Description
Node #
1
Telescope Wall
CR_XMAX7 -30 to +30
CRaTER Pre-Environmental Review
Instrument Summary 30 August 2007
OPER.
SURV.
QUAL.
-40 to +50
-40 to +40
Page 6 of 17
LRO Thermal Design Drivers
(External environmental fluxes)
 = 0 case (Noon Orbit, Hot Condition)
Lunar IR environment - Temperature varies – 100
to 400 K (Subsolar point).
View from Sun
 = 90 case (Terminator Orbit, Cold Condition)
Instrument exposed to full direct Solar flux
Lunar IR (~ 150 K continuous)
CRaTER Pre-Environmental Review
Instrument Summary 30 August 2007
Page 7 of 17
Summary of Spacecraft Contamination Control Requirements flowed to the CRATER Instrument
(Excerpts from the LRO Contamination Control Plan, 431-PLAN-000110 Rev -)
Contamination Budget for LRO Instruments
Instrument
Delivery To
LRO
1
Internal Laser
300 A/2
Flight Optics1
300 A/2
External Surfaces 450 A/2
I&T
LEND
LAMP
External Surfaces 450 A/2
Internal Surfaces1 400 A/20
External Surfaces 450 A/2
450 A/2 450 A
500 A
400 A/20 400 A/20 400 A/20
450 A/2 450 A
500 A
550 B
440 A/15
575 A
LROC
External Surfaces 450 A/2
450 A/2
450 A
500 A
550 B
CRaTER
DIVINER
Internal Surfaces1 250 A/5
External Surfaces 450 A/2
Optical Bench
400 A/2
Assembly1
External Surfaces 400 A/2
250 A/5
450 A/2
400 A/2
250 A/5
450 A
400 A/2
250 A/5
500 A
400 A/2
250 A/5
550 B
450 A
450 A/2
450 A/2
500 A
550 B
External Surfaces 450 A/2
450 A/2
450 A
500 A
550 B
LOLA
Mini-RF
Component
300 A/2
300 A/2
450 A/2
At Launch Beginning-Of- End-Of-Life
Life (BOL)
(EOL)
300 A/2 300 A/2
300 A/2
300 A/2 300 A/2
300 A/2
450 A
500 A
550 B
Outgassing Requirements for Instruments
LRO Instruments
Outgassing Rate or Level (g/cm2/sec)
CRaTER
LEND
<5.0E-11
Electronics box (ebox) module <5.0E-11
Doppler Aperture <5.0E-11
Laser Bench <5 E-13
Aft Optics Mod <5.0E-13
Radiator <5.0E-11
<2.78 E-11
<5.0E-11
<5.0E-11
<5.0E-11
LOLA
Diviner
LAMP
LROC/NAC1
LROC/NAC2
(same as NAC1)
LROC/WAC
LROC/Radiators
Instrument MLI (all)
CRaTER Pre-Environmental Review
Instrument Summary 30 August 2007
<5.0E-11
<5.0E-11
<2.5E-12 g/cm2/sec
Predicted Max Operating
temperature (deg C) at the
S/C Interface
35oC
50 oC
35oC
45oC
50oC
35oC
40oC
40oC
40oC
40oC
40oC
Page 8 of 17
Summary of Spacecraft Electrical Requirements flowed to the CRATER Instrument
(Excerpts from the LRO Electrical Systems Specification, 431-SPEC-000008 Rev E)
EMI/EMC Applicability and References
CE01
CE03
CE06
RE02
CS01
CS02
CS03
CS04
CS05
CS06
RS03
Components **
X
X
X
X
X
X
X
ESS Section
3.3.1.1
3.3.1.1
3.3.1.2
3.3.2
3.3.3.1
3.3.3.2
3.3.3.3
3.3.3.4
3.3.3.5
3.3.3.6
3.3.4
** Subsystems may be tested as individual components or assemblies where applicable. Subsystems
include instruments.
Narrowband Conducted Emissions CE01/CE03 Limits
CE01 (30 Hz - 14 KHz)
CE03 (14 KHz-50 MHz)
140
120
Instrument or Component Level
Test Limits (Differential Mode)
100
80
dBuA
Instrument or Component Level Test
Limits (Common Mode)
60
40
20
Bandwidth (Hz)
0
1.00E+01
1.00E+02
5 Hz
1.00E+03
500 Hz
1.00E+04
1.00E+05
5 KHz
1.00E+06
1.00E+07
50 KHz
1.00E+08
FREQUENCY (Hz)
CRaTER Pre-Environmental Review
Instrument Summary 30 August 2007
Page 9 of 17
RE02 Limits for Components that are OFF from launch to vehicle separation
(vertical axis is dBmicrovolts/meter)
80
30 GHz
70
60
50
40
d
14 kHz
B
u
V/ 30
m
20
10
Components and Instrument Levels
(for components and instruments that
are OFF from launch to vehicle
separation)
0.01
0.1
20 dB uV/m
2091.3967 +/- 6 MHz
(LRO S-band RX)
8 dB uV/m
2380 +/- 15 MHz
(LRO Mini-RF S-band RX)
10
100
Frequency (MHz)
1
8 dB uV/m
7140 +/- 15 MHz
(LRO Mini-RF Xband RX)
1,000
100,000
10,000
CS01/CS02 Limits
6
5
V rms
4
30 Hz
2.8 Vrms
1.5 kHz
3
2
50 kHz
400 MHz
1.0 Vrms
1
0.00001
(10 Hz)
0.0001
(100 Hz)
0.001
(1 kHz)
0.01
(10 kHz)
0.1
(100 kHz)
1
10
100
Frequency (MHz)
CRaTER Pre-Environmental Review
Instrument Summary 30 August 2007
Page 10 of 17
1,000
CS06 Conducted Susceptibility Test Pulse
64
CS06 Positive 25Vdc 10uS Pulse
56
48
40
25Vdc
31
10us
24
Volts
16
NOTE: The SC Power Bus Pulse
shall not exceed 56Vdc at anytime.
8
0
0
10
20
30
40
50
60
70
80
Time useconds
64
CS06 Negative 31Vdc 10uS Pulse
56
48
40
10us
31
24
Volts
16
NOTE: The SC Power Bus Pulse
shall not go below 0Vdc at anytime.
8
0
0
10
20
30
40
50
60
70
80
Time useconds
CRaTER Pre-Environmental Review
Instrument Summary 30 August 2007
Page 11 of 17
LRO Operational RS Test Limits
Frequency Range
14 KHz - 2 GHz
2 GHz - 12 GHz
12 GHz - 28 GHz
2.271 GHz +/- 5 MHz
Test Level (V/m)
2
5
10
12
Test Level (dBuV/m)
126
134
140
142
25.5 GHz - 28.0 GHz
28
149
2.380 GHz +/- 15 MHz
5
134
7.14 GHz +/- 15 MHz
5
134
Requirement Source
GSFC-STD-7000
GSFC-STD-7000
GSFC-STD-7000
LRO S-Band
Transmitter
LRO Ka-Band Indirect
Radiation
LRO Mini-RF S-band
Indirect Radiation
LRO Mini-RF X-band
Indirect Radiation
Launch Site/Vehicle RS Test Levels
Payload Processing
and Launch Pad
Environment
Frequency Range
14 kHz - 2.700 GHz
2.700 - 2.900 GHz
2.900 - 5.400 GHz
5.400 - 5.900 GHz
V/m
20
25
20
40
dBuV/m
146
148
146
152
Source
GPN-20 & WSR-88D
C-Band Tracking
Radars
5.900 - 30 GHz
Atlas V Radiated
Emissions
Frequency Range
14 kHz - 2.206 GHz
20
146
V/m
20
dBuV/m
146
Source
2.206 - 2.216 GHz
20
146
Atlas V Second Stage
S-band T/M
2.216 - 5.759 GHz
20
146
5.759 - 5.771 GHz
58
155
5.771 - 30 GHz
20
146
CRaTER Pre-Environmental Review
Instrument Summary 30 August 2007
Atlas V Second Stage
C-band beacon (peak
transmit)
Page 12 of 17
CRATER Deliverables Status Tracking Spreadsheet
(as negotiated with LRO Payload Systems Manager and LRO System Assurance Manager)
CDRL # DID #
1
Due Date
1 week before I-PDR
Received
Complete
IAR
Complete
3
Deliverable Item
Instrument Preliminary Design Review (IPDR) Package
Instrument Accommodation Review
Package
Instrument-to-Spacecraft ICD inputs
30 days after contract award
Complete
4
Peer Reviews
1 week after review
Complete
5
Instrument Functional and Performance
Requirements Document
Phases C/D/E Implementation and Cost
Plans
Performance Assurance Implementation
Plan (PAIP)
Monthly Technical Progress Report
(template provided by LRO)
Monthly Schedule Status Report (can be
part of monthly technical progress report)
Preliminary at I-PDR, Final 30 days prior to I-CDR Complete
#32-01205
15-Jun-05
Complete
2
6
7
By 5th of each month covering previous month
Complete
#32-01204
In Compliance
By 5th of each month covering previous month
In Compliance
10
Monthly Risk Management Report (can be By 5th of each month covering previous month
part of monthly technical progress report)
In Compliance
11
NASA Contractor Financial Management
Reports (533M/533Q)
533M, by the 15th of each month; 533Q, by the
15th of every quarter as negotiated between
Instrument team and Project
In Compliance
12
Computer Aided Design (CAD) model
Final 60 days prior to I-CDR, Updates as required Complete
13
Structural Math Model
If required by 431-RQMT-000012, preliminary I- Complete
PDR - 60 days, Final at I-CDR - 60 days. Updates
as required
14
Thermal Math Model
Thermal TSS and Sinda model drops are
Complete To-Date
expected at: 1) I-PDR - 60 days, 2) I-CDR - 60
days, 3) pre-thermal vac including test setup
fixturing and chamber conditions, and 4) I-PSR 10 days after post-thermal balance correlation
15
Subcontracting Plan in accordance with
As required by FAR Clause 52.219-9
FAR 52.219-9
Semi-Annual Subcontracting Plan Reports As required by GSFC Clause 52.219-90
(SF 294 and SF 295)
Reporting of Inventions
As required by FAR Clause 52.227-11
8
9
16
17
18
19
NASA Property in the Custody of
Contractors (NF 1018 Reporting)
IT Security Plan
CRaTER Pre-Environmental Review
Instrument Summary 30 August 2007
Final: 30 days prior to I-CDR
Complete
#32-04004
Not Required
Not Required
As required by NASA FAR Clause 18-52.245-73 Not Required
Initial at Ground System (GS) Single Design
Review (SDR) + 30 days
Final at MOR - 60 days
Complete
#32-01208
Page 13 of 17
CDRL # DID #
20
1-1
Deliverable Item
Heritage matrix/report
Due Date
Initial at I-PDR - 30 days;
Final at I-CDR - 45 days
Initial at I-PDR - 30 days;
Final at I-PDR + 45 days
Updates prior to implementation
Received
Complete
#32-04013
Complete
#32-01204
21
2-1
Quality manual/ PAIP
22
2-2
Problem Failure Reports
Within 24 hours of occurrence
In Compliance
23
2-3
Final at I-PSR - 10 days
24
3-1
Subcontractor Assurance Verification
Matrix
System Safety Program Plan
Complete
#32-04004
Included in PAIP
25
3-2
26
3-3
Safety Requirements Compliance
Checklist
Preliminary Hazard Analysis
27
3-4
Operations hazard analysis
Preliminary 45 days prior to ship;
Final 15 days prior to ship
28
3-5
Safety Assessment Report
Preliminary at I-PDR + 30 days;
Update at I-CDR - 30 days;
Final 30 days prior to delivery
Inputs Received
29
3-6
MSPSP (Inputs)
Provide input as needed
Will comply
30
3-7
Verification Tracking Log
Provide input as needed
Complete via #3204014
31
3-8
Ground operations procs, I&T Hazards
GSFC procedures First Use - 7 days
Launch range procedures Draft at I-PDR - 60 days;
Final at I-PSR - 60 days;
Submit to range First Use - 45 days
In Compliance
32
3-9
Safety Variances
As Required
In Compliance
33
3-10
Orbital Debris Assessment
Provide input as needed
In Compliance
34
4-1
Reliability Program Plan
In Compliance
35
4-2
Probabilistic Risk Assessment
36
4-3
Failure Modes and Effects Analysis
I-PDR - 30 days
Updates as required
Preliminary at I-CDR - 30 days;
Final at I-CDR + 30 days
Final at M-CDR - 30 days
37
4-4
Fault Tree Analysis
38
4-5
Parts Stress Analysis
Preliminary at I-CDR - 30 days;
Final at I-CDR + 30 days
Final at M-CDR - 30 days
39
4-6
Worst Case Analysis
Final at M-CDR - 30 days
40
4-7
Reliability Assessments and Predictions
41
4-8
Trend Analysis
Preliminary at I-CDR - 30 days;
Final at I-CDR + 30 days
Draft at I-CDR; Final at I-PER
CRaTER Pre-Environmental Review
Instrument Summary 30 August 2007
Draft at I-PDR + 45 days;
Update at I- CDR + 45 days
Concurrent with each SSPP/MSPSP
submittal
I-PDR - 30 days
Inputs Received
Complete
#32-04015
N/R - will provide
inputs as needed
P(s) required
Complete
#32-04009
In Compliance
Complete
#32-04010
Complete
#32-04011-01;
#32-04011-02
Complete
#32-04003
Complete
#32-04008
Page 14 of 17
CDRL # DID #
42
4-9
Deliverable Item
Limited Life Items List
43
5-1
Software Assurance Plan
Due Date
Preliminary at I-CDR - 30 days;
Final at I-CDR + 30 days
Final at I-CDR
44
5-2
Software Management Plan
Final at I-CDR
Not Required
45
5-3
Software Configuration Management Plan Final at I-CDR
Not Required
46
5-4
Software Reliability Plan
Final at I-CDR
Not Required
47
5-5
Software Requirements Specification
Final at I-CDR
Not Required
48
7-1
Risk Management Plan
Final at I-CDR + 30 days
49
9-1
Final at M-CDR - 30 days
50
9-2
System Performance Verification
Plan/Matrix
Performance Verification Procedure
Complete
#32-01202
Complete
#32-01206
In Compliance
51
9-3
Verification Reports
Verification Reports:
Preliminary 72 hours after test;
Final 30 days after verification activity
System Performance Verification Report:
Preliminary at I-CDR;
Final report 30 days following on-orbit check out
In Compliance
52
10-1
PWB Coupon Analysis Approval
Prior to population
N/A
53
11-1
Materials and Process Control Plan
54
11-2
As Designed/As Built M&P lists
Initial at I-PDR - 30 days;
Final at I-PDR +45 days
Preliminary at I-CDR - 30 days;
Final as part of End Item Data Package
Complete
#32-04001
Complete
#32-04001;
04001_01_r01
55
11-3
Materials Usage Agreements
As Required
In Compliance
56
11-4
Stress Corrosion Evaluation Form
In Compliance
57
11-5
Polymerics and Composites List
Initial at I-CDR - 30 days;
Final at I-CDR + 30 days
Initial at I-CDR - 30 days;
Final at I-CDR + 30 days
58
11-6
Material Waiver Form
First Use - 15 days
In Compliance
59
11-7
Inorganic Materials List
Initial at I-CDR - 30 days;
Final at I-CDR + 30 days
Complete
#32-04001;
04001_01_r01
60
11-8
Fastener Control Plan
In Compliance
61
11-11
Materials Process Utlization List
Initial at I-PDR - 30 days;
Final at I-PDR +45 days
Initial at I-PDR - 30 days;
Final at I-CDR - 30 days
62
11-12
Certificate of Raw Material Compliance
Maintain for GSFC
In Compliance
63
12-1
EEE Parts Control Plan
64
12-2
Parts Control Board Reports
Initial at I-PDR - 30 days;
Final at I-PDR + 45 days
Provide input as needed
Complete
#32-04002
In Compliance
CRaTER Pre-Environmental Review
Instrument Summary 30 August 2007
30 days prior to test
Received
Complete via #3204005
Not Required
Complete
#32-04001;
04001_01_r01
Complete
#32-04001;
04001_01_r01
Page 15 of 17
CDRL # DID #
65
12-3
66
12-4
Due Date
Initial at I-PDR - 30 days;
Final at I-CDR - 30 days
Alert/Advisory Disposition and Preparation Within 25 days of Alert
67
13-1
Contamination Control Plan
Final at I-CDR - 30 days
68
14.1
ESD Control Plan
69
16*
End Item Data Package
Initial at I-PDR - 30 days;
Final at I-PDR + 45 days
At I-PSR
70
Deliverable Item
EEE Parts Identification List
Received
Complete
#32-04002
In Compliance
Complete
#32-01203
In Compliance
Future Delivery
5 working days prior to I-CDR
Complete
5 working days prior to I-PER
Future Delivery
5 working days prior to I-PSR
Future Delivery
73
Instrument Critical Design Review (I-CDR)
Package
Instrument Pre-Environmental Test
Readiness Review (I-PER) Package
Instrument Pre-Ship Review (I-PSR)
package
Inputs to Mission CDR package
15 working days prior to M-CDR
Complete
74
Inputs to Mission PER Package
15 working days prior to M-PER
Future Delivery
75
Inputs to Mission PSR Package
15 working days prior to M-PSR
Future Delivery
76
Inputs to Mission Operations Review
(MOR)
Inputs to Mission Launch Readiness
Review (LRR)
Phase C/D/E Cost Plan yearly update
15 working days prior to MOR
Future Delivery
15 working days prior to LRR
Future Delivery
As agreed-upon between the Project office and
Instrument team to support the yearly federal
budget process
In Compliance
79
Instrument Mechanical Interface Drawing
(MID)
Updates as required to version released prior to I- Complete
PDR as part of mechanical ICD development
#GC 2096501
80
Requirements Verification Traceability
Final 30 days prior to M-CDR
Matrix (plan can be part of System
Performance Verification Plan, final can be
part of Acceptance Data Package)
In Compliance
81
Inputs to Mission Operations Plan
Complete
82
Inputs to Orbiter Integration and Test Plan 60 days prior to I-CDR or as required by Project
Complete
83
Instrument Configuration Management
Final 60 days prior to I-CDR
Plan
Documentary photographs of Instrument 10 working days prior to I-PSR
fabrication and integration (may be part of
Acceptance Data Package)
Complete
#32-01201
Future Delivery
71
72
77
78
84
CRaTER Pre-Environmental Review
Instrument Summary 30 August 2007
As required by Project
Page 16 of 17
CDRL # DID #
85
Deliverable Item
Instrument Engineering Layout Drawings
per SOW Item 2003 (may be part of
Acceptance Data Package)
Due Date
10 working days prior to I-PSR
Received
Future Delivery
86
Instrument Electrical Schematic Drawings 10 working days prior to I-PSR
per SOW Item 2004 (may be part of
Acceptance Data Package)
Complete and OnFile
87
Flight Rules and Constraints
Inputs Received
88
Instrument Grounding Diagram
Preliminary 30 days prior to M-CDR; updates as
required for I-PSR
Final 60 days prior to I-CDR
89
Remove/Install Before Flight List
Final 60 days prior to I-CDR
90
Instrument-to-Spacecraft Integration Plan
Final 60 days prior to I-PSR
91
Final 10 days prior to I-PSR
Preliminary 90 days prior to GS SDR; Final 30
days prior to GS SDR
As required by Project
Complete
94
Orbiter-level test procedures in ITOScompatible format
Instrument User's Manual for Mission
Operations Center (MOC)
Science Operations Center (SOC) Data
Management and Archive Plan
Inputs for MOC-to-SOC ICDs
95
SOC Requirements Document
Final 30 days prior to M-CDR
96
SOC Test Plan
Complete
#32-01209
Draft Complete
97
98
EDR Data Product Sofware Interface
Specification (SIS)
EDR Archive Volume SIS
99
RDR Data Product SIS
92
93
Complete
#32-03001-01
Complete
#32-04007
Future Delivery
LRO-generated;
Inputs Received
Future Delivery
Final 60 days prior to I-PSR
Inputs Received
101
Inputs to the LRO Ground Segment ICD
Draft due 7/31/07
Final due 9/30/07
Preliminary 2 months after GS SDR;
Final 4 months after GS SDR
Preliminary 2 months after GS SDR;
Final 4 months after GS SDR
Preliminary 5 months after MOR;
Final 7 months after MOR
Preliminary 5 months after MOR;
Final 7 months after MOR
As required by Project
102
As-delivered Flight Software Code
Final 10 days prior to I-PSR
Inputs Received
N/A
RDR Archive Volume SIS
100
Complete
#32-01211
Complete
#32-01211
Complete
#32-01211
Complete
#32-01211
Final Report
Thirty (30) days after Launch Plus 15 Months
Future Delivery
103
104
Mass Simulator
30 days after M-CDR
Complete
105
Instrument Simulator
30 days after M-CDR
106
Flight Instrument
No Later Than 10/15/07
Complete
Future Delivery
Instrument GSE, including shipping
container
Three flight quality mating connectors for
every Instrument connector
Delivered with Flight Instrument
Future Delivery
I-PER
Complete
107
108
CRaTER Pre-Environmental Review
Instrument Summary 30 August 2007
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