451-SPEC-000913
Revision - DRAFT
Lunar Reconnaissance Orbiter
Thermal Hardware Specification
April 3, 2007
Goddard Space Flight Center
Greenbelt, Maryland
National Aeronautics and
Space Administration
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LRO Thermal Hardware Specification
451-SPEC-000913
Revision – DRAFT
CM FOREWORD
This document is a Lunar Reconnaissance Orbiter (LRO) Project Configuration Management
(CM)-controlled document. Changes to this document require prior approval of the applicable
Configuration Control Board (CCB) Chairperson or designee. Proposed changes shall be
submitted to the LRO Project CM Office (CMO), along with supportive material justifying the
proposed change. Changes to this document will be made by complete revision.
Questions or comments concerning this document should be addressed to:
LRO Project Configuration Management Office
Mail Stop 431
Goddard Space Flight Center
Greenbelt, Maryland 20771
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LRO Thermal Hardware Specification
451-SPEC-000913
Revision – DRAFT
Signature Page
Prepared by:
Charles Baker
LRO Thermal Systems Lead
GSFC/NASA, Code 545
__________
Date
Reviewed by:
David Everett
LRO Mission Systems Engineer
GSFC/599
__________
Date
Approved by:
Craig Tooley
LRO Project Manager
GSFC/NASA, Code 431
__________
Date
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LRO Thermal Hardware Specification
451-SPEC-000913
Revision – DRAFT
LUNAR RECONNAISSANCE ORBITER PROJECT
DOCUMENT CHANGE RECORD
REV
LEVEL
DESCRIPTION OF CHANGE
Sheet: 1 of 1
APPROVED
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DATE
APPROVED
LRO Thermal Hardware Specification
451-SPEC-000913
Revision – DRAFT
List of TBDs/TBRs
Item
No.
Location
Summary
Ind./Org.
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Due Date
LRO Thermal Hardware Specification
451-SPEC-000913
Revision – DRAFT
TABLE OF CONTENTS
Page
1.0
Scope................................................................................................................................ 1-1
1.1
General ................................................................................................................. 1-1
1.2
Purpose................................................................................................................. 1-1
1.3
Responsibility ...................................................................................................... 1-1
1.4
Documents ........................................................................................................... 1-2
1.4.1 Applicable Documents ............................................................................. 1-2
1.4.2 Reference Documents .............................................................................. 1-2
2.0
Heater Circuits ............................................................................................................... 2-2
2.1
Summary of all heater circuits ............................................................................. 2-1
2.2
Location of Heater Circuits ................................................................................ 2-12
3.0
Flight Interface Material Design .................................................................................. 3-1
4.0
Thermistor and PRT locations ..................................................................................... 4-3
5.0
Thermal Coatings......................................................................................................... 5-14
5.1
Thermal Radiator Coatings ................................................................................ 5-15
5.2
Launch vehicle interface and solar array Coatings ............................................ 5-16
6.0
Multi-Layer Insulation Coating Locations ................................................................ 6-17
6.1
Sunside –Y face ................................................................................................. 6-17
6.2
Anti- Sunside +Y face ........................................................................................ 6-17
6.3
NADIR -Z face .................................................................................................. 6-18
6.4
Zenith +Z face .................................................................................................... 6-19
6.5
+X face ............................................................................................................... 6-19
6.6
–X Face .............................................................................................................. 6-20
6.7
Internal Propulsion blankets .............................................................................. 6-21
6.8
Multi-Layer Insulation Blanket Grounding ....................................................... 6-21
6.9
Attachment of Multi-Layer Insulation Blankets ................................................ 6-21
Appendix A. Abbreviations and Acronyms ................................................................................1
Appendix B: Blanket Descriptions and Designations .................................................................1
LIST OF FIGURES
Figure
Page
Figure 5-1 Spacecraft Radiator Locations and Thermal Coatings ............................................. 5-15
Figure 5-2 Thermal Coatings Overview ................................................................................... 5-15
Figure 5-3 HGAs Thermal Coatings Overview ......................................................................... 5-15
Figure 5-4 Launch Vehicle Thermal Coatings........................................................................... 5-16
Figure 6-1 Orbiter Reference for MLI ....................................................................................... 6-17
Figure 6-2 Mini RF MLI Closeout ............................................................................................ 6-18
ii
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LRO Thermal Hardware Specification
451-SPEC-000913
Revision – DRAFT
Figure 6-3 Figure TBD .............................................................................................................. 6-19
Figure 6-4 High Temperature Blankets by Insertion Thrusters ................................................. 6-20
Figure 6-5 –X Propulsion Tank MLI ......................................................................................... 6-21
Figure 6-6 IM MLI Venting Scheme ......................................................................................... 6-22
Figure 6-7 Orbiter Venting Scheme ........................................................................................... 6-23
Figure 6-8 Blanket Filter ............................................................................................................ 6-24
LIST OF TABLES
Table
Page
Table 2-1 Solar Array and High Gain Heater Circuit Summary ................................................. 2-1
Table 2-2 Instrument Survival Heater Circuit Summary ............................................................. 2-2
Table 2-2 Instrument Survival Heater Circuit Summary (continued) ......................................... 2-3
Table 2-3 Instrument Operational Heater Circuit Summary........................................................ 2-4
Table 2-3 Instrument Operational Heater Circuit Summary (continued) .................................... 2-5
Table 2-5 Essential Heater Bus (Redundant Survival) Service ................................................... 2-6
Table 2-6 Software Controlled Heater Summary (Lunar Eclipse Warmup Heaters and Primary
Survival Circuit Heaters) ............................................................................................................. 2-7
Table 2-7 Unswitched Battery and OMNI Heater Summary....................................................... 2-8
Table 2-8 Propulsion Heater Circuit Summary ........................................................................... 2-9
Table 2-8 Propulsion Heater Circuit Summary ......................................................................... 2-10
Table 2-9 Redundant Propulsion Heater Circuit Summary ....................................................... 2-11
Table 2-9 Redundant Propulsion Heater Circuit Summary ....................................................... 2-12
Table 3-1 Interface Material Design ............................................................................................ 3-1
Table 4-1 MAC Thermistors and PRTs ....................................................................................... 4-3
Table 4-1 MAC Thermistors and PRTs (continued 1)................................................................. 4-4
Table 4-1 MAC Thermistors and PRTs (continued 2)................................................................. 4-5
Table 4-1 MAC Thermistors and PRTs (continued 3)................................................................. 4-6
Table 4-1 MAC Thermistors and PRTs (continued 4)................................................................. 4-7
iii
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LRO Thermal Hardware Specification
451-SPEC-000913
Revision – DRAFT
Table 4-1 MAC Thermistors and PRTs (continued 5)................................................................. 4-8
Table 4-1 MAC Thermistors and PRTs (continued 6)................................................................. 4-9
Table 4-2 GCE 1 and 2 Temperature Sensors ........................................................................... 4-10
Table 4-2 GCE 1 and 2 Temperature Sensors (continued) ........................................................ 4-11
Table 4-3 Internal Box Thermistors ........................................................................................... 4-12
Table 4-4 GSE Umbilical Temperature Telemetry.................................................................... 4-13
Table 5-1 Orbiter Thermal Coatings Overview ......................................................................... 5-14
iv
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LRO Thermal Hardware Specification
1.0
SCOPE
1.1
GENERAL
451-SPEC-000913
Revision – DRAFT
This Thermal Hardware Specification defines and controls the thermal system hardware
configuration for heaters, interface material, thermistors/PRTs, and MLI on the Lunar
Reconnaissance Orbiter (LRO) spacecraft (SC). The specification details how the system level
thermal hardware (heaters, thermistors/PRTs and MLI will be manufactured and qualified. Only
system level components will be detailed in this specification while internal telemetry or heaters
within components are on instruments will be detailed elsewhere. This document outlines:
a.
b.
c.
d.
e.
f.
1.2
Heater Circuit Ohmages and Setpoints
Interface Material
Specification of System Level Thermistors and PRTs
Location of Thermal Coatings
Location of heaters, thermostats, thermistors, and PRTs on the mechanical structure
Specification of System Level MLI
PURPOSE
The purpose of this specification is to clearly define what the LRO thermal subsystem intends on
delivering to the spacecraft. The actual installation Work Order Authorizations (WOA) will
specifically address the installation method.
1.3
RESPONSIBILITY
The Goddard Space Flight Center (GSFC) has the final responsibility for the LRO mission, the
Orbiter, its subsystems, and any requirements specifically assigned to LRO in this document.
LRO systems engineering and project management have the ultimate authority to specify thermal
requirements. This document is an implementation of those requirements. This document shall
be the vehicle by which the thermal hardware design is tracked.
1-1
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LRO Thermal Hardware Specification
1.4
451-SPEC-000913
Revision – DRAFT
DOCUMENTS
1.4.1 Applicable Documents
The following documents form a part of this Specification to the extent specified herein:
431-RQMT-000091
Lunar Reconnaissance Orbiter Thermal Systems Specification
431-SPEC-000008
Lunar Reconnaissance Orbiter Electrical Systems Specification
1.4.2 Reference Documents
GSFC-STD-7000
General Environmental Verification Standards (GEVS) for Flight
Programs and Projects
GSFC-STD-1000
Goddard Gold Rules Document
MIL-R-39009
General Specification for Resistors, Fixed, Wire-Wound (Power
Type, Chassis Mounted)
NASA GSFC S311-641
Switch, Thermostatic, Bimetallic, SPST, Narrow Differential,
Hermetic
NASA GSFC S311-P-079
Procurement Specification for Thermofoil Heaters
S-311-P-18
Specification for Thermistor, (Thermally Sensitive Resistor),
Insulated and Negative Temperature Coefficient
S-311-XXXX
Platinum Resistance Thermistor Specification
431-PLAN-000110
LRO Contamination Control Plan
2.0
HEATER CIRCUITS
This specification outlines the system level heater circuits that will be placed at thermal
interface. All heater circuits full under two designs: thermostatically controlled, and
electronically controlled with an over temperature thermostat. All thermostatic heater circuits
will be two thermostats in series. All electronically (software which switches the heater on and
off in the C&DH box or the PSE) controlled circuits will have an over-temperature thermostat in
series and on avionics panel, a secondary heater circuit that is thermostatically controlled at the
minimum setpoint. All Kapton heaters will be overtaped with 3.5 mil aluminum tape with a
minimum of 0.25” overlap. All thermostats on controlling thermistors will be bonded down with
Stycast 2850FT (?) and grounded with Eccobond (?)
2-2
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LRO Thermal Hardware Specification
2.1
451-SPEC-000913
Revision - DRAFT
SUMMARY OF ALL HEATER CIRCUITS
All mission level heater circuits are outlined in the following tables.
Table 2-1 Solar Array and High Gain Heater Circuit Summary
Circuit Location
SA Gimbal (Y)
SA Gimbal (XZ)
SA Gimbal (Y) Redundant
SA Gimbal (XZ) Redundant
SAS Damper Heater 1
SAS Damper Heater 1
HGAS Motor Y
HGAS Motor XZ
HGAS Rotary Joint Y
HGAS Rotary Joint XZ
LR Heater
HGAS Motor Y Redundant
HGAS Motor XZ Redundant
HGAS Rotary Joint Y
Redundant
HGAS Rotary Joint XZ
Redundant
Rotary Joint at HGAS Hinge
LR Heater Redundant
Circuit
Number
Overall
Resistance
(Ω)
Qty of Size Of
Htrs
Heater
(in2)
Max Watt
Density (W/in2)
@35 V
Setpoint Thermostat Part Thermostat
Range
Number
Serial Numbers
(°C)
32.00
72.00
32.00
72.00
255.15
255.15
32.00
72.00
127.00
127.00
127.00
32.00
72.00
127.00
127.00
127.00
127.00
2-1
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LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 2-2 Instrument Survival Heater Circuit Summary
Circuit Location
CRATER Surv. Heater 1
CRATER Surv. Heater 2
LOLA OTA Survival Heater
LOLA MEB Survival Heater
Surv LEND Rad Htr#1
Surv LEND Rad Htr#2
Surv LEND Rad Htr#3
LROC WAC Survival Heater
LROC NAC +X Metering Survival
Heater
LROC NAC - X Metering Survival
Heater
LROC SCS Survival Heater
LROC NAC - X Elec Survival Heater
LROC NAC +X Elec Survival Heater
Diviner Instr OBA Ext Surv #1
Diviner Instr Az Act Output Surv#2
Dirviner Instr Yoke A elbow (Node
2050) Surv#3
Diviner Instr Yoke A elbow (Node
2200) Surv #4
Diviner Instr Yoke B near El Act Surv
#5
LAMP Instrument optical bench Surv.
Heater
Surv OB -Z panelHtr#4, LROC -X
NAC
Surv OB +Y Htr#1, LAMP
Circuit
#
Overall
Resistance
(Ω)
Qty of Size Of
Htrs
Heater
(in2)
Max Watt
Density (W/in2)
@35 V
Setpoint Thermostat Part Thermostat
Range
Number
Serial Numbers
(°C)
48.70
48.70
21.90
20.10
108.00
117.00
53.50
177.80
68.80
68.80
220.90
70.80
70.80
72.9
102.1
85.05
255.2
63.79
145.80
314.00
146.00
2-2
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LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 2-3 Instrument Survival Heater Circuit Summary (continued)
Circuit Location
Surv OB +Y Htr#2, LAMP/MEB
Surv OB +Y Htr#3, MEB
Surv OB +Z Htr#1, LOLA/OTA
Surv OB +Z Htr#2, LOLA/OTA
Surv OB +Z Htr#3, LOLA/OTA
Surv OB +Z Htr#4, LROC WAC
Surv OB -Z Htr#1, LROC NAC +X
Surv OB -Z Htr#2, LROC NAC +X/-X
OB Star Cam -X Panel and SCS (~-Z
side)
Surv StarCam +X Rad Htr
Surv StarCam -X Rad Htr
Surv Diviner I/F Htr
Circuit
#
Overall
Resistance
(Ω)
Qty of Size Of
Htrs
Heater
(in2)
Max Watt
Density (W/in2)
@35 V
Setpoint Thermostat Part Thermostat
Range
Number
Serial Numbers
(°C)
85.60
73.40
157.00
157.00
157.00
220.00
157.00
389.00
73.33
34.40
55.75
85.44
2-3
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LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 2-4 Instrument Operational Heater Circuit Summary
Circuit Location
LOLA MEB Heater
LOLA 1 OTA Laser Bench
LOLA 2 OTA Housing\
LROC NAC Adaptor Plate Heater
LROC NAC Adaptor Plate Heater
LROC WAC Op Heater
LAMP Op Heater 1
Diviner I/F
CRATER Op Heater 1
CRATER Op Heater 2
OP OB+X #1 (2 heaters combined)
OP OB +X #3
OB OP +Y#2
Op Star Cam -X Radiator Heater @
star cam I/F
Op Star Cam +X Radiator Heater @
star cam I/F
OB OP +Y#3
OB OP +Y#4
OB OP +Y#5
OB OP Wac Baseplate
OB OP -Y Panel#2
OB OP -Y Panel#3
OB OP -Y Panel#4
OB OP -Z Panel#2
OB OP -Z Panel#3
Circuit
#
Overall
Resistance
(Ω)
Qty of Size Of
Htrs
Heater
(in2)
Max Watt
Density (W/in2)
@35 V
Setpoint Thermostat Part Thermostat
Range
Number
Serial Numbers
(°C)
72.10
40.05
76.70
55.20
55.20
186.90
58.00
166.6
52.1
52.1
326.00
378.00
568.60
174.00
174.00
135.00
462.00
662.00
661.00
98.90
271.00
120.00
389.00
389.00
2-4
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LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 2-5 Instrument Operational Heater Circuit Summary (continued)
Circuit Location
-X Star Cam OB I/F Heater #1
-X Star Cam OB I/F Heater #3
+X Star Cam OB I/F Heater #2
+X Star Cam OB I/F Heater #3
OB OP +Z Panel near LOLA
Circuit
#
Overall
Resistance
(Ω)
Qty of Size Of
Htrs
Heater
(in2)
Max Watt
Density (W/in2)
@35 V
Setpoint Thermostat Part Thermostat
Range
Number
Serial Numbers
(°C)
378.00
315.00
176.00
580.00
315.00
2-5
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LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 2-6 Essential Heater Bus (Redundant Survival) Service
Circuit Location
Battery Heater
RWA 1 Heater
RWA 2 Heater
RWA 3 Heater
RWA 4 Heater
ITP CDH Heatpipe Heater
ITP Sband Heatpipe
ITP DREB Heatpipe
Circuit
Number
Overall
Resistance
(Ω)
Qty of Size Of
Htrs
Heater
(in2)
Max Watt
Density (W/in2)
@35 V
Setpoint Thermostat Part Thermostat
Range
Number
Serial
(°C)
Numbers
18.23
102.06
102.06
102.06
102.06
23.20
30.93
30.93
2-6
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LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 2-7 Software Controlled Heater Summary (Lunar Eclipse Warmup Heaters and Primary Survival Circuit Heaters)
Circuit Location
RWA Software Cntrl Heaters
S-Band Pipe Software Cntrl
Heater (single ITP circuit)
KaTWTA Heatpipe Software
Cntrl Heater (single ITP circuit)
DREB Heatpipe Software Cntrl
Heater (single ITP circuit)
CDH Warm up Heatpipe
Software Cntrl Heater (single
ITP circuit)
LEND I/F Op Heater (in C&DH)
OB for LROC +X NAC I/F on Z panel Heater #1 (in C&DH)
OB for LROC -X NAC I/F on -Z
panel Heater #4 (in C&DH)
OB -X Panel near NAC Heater
#1 (in C&DH) ?
OB -Y PANEL Heater#1(in
C&DH)
LROC NAC Structure Op
Heater +X
LROC NAC Structure Op
Heater -X
OB +Y Panel, Heater #1
-X Star Tracker OB I/F Heater
#2
+X Star Tracker OB I/F Heater
#1
Circuit Number
Overall
Qty of
Resistance Htrs
(Ω)
7.08 4
Size Of
Heater (in2)
Max Watt Density
(W/in2) @35 V
21.40
21.40
21.40
9.42
80.30
321.00
156.80
100.80
161.00
40.50
40.50
103.00
212.00
294.00
2-7
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Control Sensor
Setpoint
Range (deg C)
or PSE
LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 2-8 Unswitched Battery and OMNI Heater Summary
Circuit Location
Battery 1/2 of Survival Heater
Battery 1/2 of Survival Heater
OMNI 1 Heater
OMNI 2 Heater
OMNI 1 Redundant Heater
OMNI 2 Redundant Heater
Circuit
Number
Overall
Qty
Resistance of
(Ω)
Htrs
Size Of
Heater
(in2)
Max Watt
Density
(W/in2) @35
V
Setpoint
Range (°C)
18.00
18.00
291.60
291.60
291.60
291.60
2-8
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Thermostat
Part Number
Thermostat
Serial
Numbers
LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 2-9 Propulsion Heater Circuit Summary
Circuit Location
+X Tank Heater Circuit 1 (equator)
+X Tank Heater Circuit 2 (+X pole)
+X Tank Heater Circuit 3 (-X pole)
-X Tank Heater Circuit 1 (equator)
-X Tank Heater Circuit 2 (equator)
-X Tank Heater Circuit 3 (equator)
-X Tank Heater Circuit 4 (equator)
-X Tank Heater Circuit 5 (+X pole)
-X Tank Heater Circuit 6 (-X pole)
HP Fill Drain Heater
LP Fill Drain Heater
Pressurant Tank Heater
HP/LP Heater 1
HP/LP Heater 2
HP/LP Heater 3
HP/LP Heater 4
Insertion Thruster Heater 1
Insertion Thruster Heater 2
Insertion Thruster Heater 3
Insertion Thruster Heater 4
Circuit
Number
Overall
Qty of Size Of
Resistance Htrs
Heater
(Ω)
(in2)
Max Watt
Setpoint
Density
Range (°C)
2
(W/in ) @35 V
145.80
146.00
179.20
91.00
91.00
91.00
91.00
146.00
44.80
145.80
145.80
145.80
145.80
145.80
145.80
145.80
189.00
189.00
189.00
189.00
2-9
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Thermostat
Part Number
Thermostat
Serial Number
LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 2-10 Propulsion Heater Circuit Summary
Circuit Location
ACS Thruster Heater 1
ACS Thruster Heater 2
ACS Thruster Heater 3
ACS Thruster Heater 4
ACS Thruster Heater 5
ACS Thruster Heater 6
ACS Thruster Heater 7
ACS Thruster Heater 8
Insertion Prop Line 1
Insertion Prop Line 2
Insertion Prop Line 3
ACS Prop Line 1
ACS Prop Line 2
ACS Prop Line 3
ACS Prop Line 4
Fill Drain Line 1
Fill Drain Line 2
Tank Liquid Line +X
Tank Liquid Line -X
Insertion Thruster Deck Heater
Circuit
Number
Overall
Qty of Size Of
Resistance Htrs
Heater
(Ω)
(in2)
Max Watt
Setpoint
Density
Range (°C)
2
(W/in ) @35 V
198.00
198.00
198.00
198.00
198.00
198.00
198.00
198.00
42.53
2-10
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Thermostat
Part Number
Thermostat
Serial Number
LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 2-11 Redundant Propulsion Heater Circuit Summary
Circuit Location
+X Tank Heater Circuit 1 (equator)
+X Tank Heater Circuit 2 (+X pole)
+X Tank Heater Circuit 3 (-X pole)
-X Tank Heater Circuit 1 (equator)
-X Tank Heater Circuit 2 (equator)
-X Tank Heater Circuit 3 (equator)
-X Tank Heater Circuit 4 (equator)
-X Tank Heater Circuit 5 (+X pole)
-X Tank Heater Circuit 6 (-X pole)
HP Fill Drain Heater
LP Fill Drain Heater
Pressurant Tank Heater
HP/LP Heater 1
HP/LP Heater 2
HP/LP Heater 3
HP/LP Heater 4
Insertion Thruster Heater 1
Insertion Thruster Heater 2
Insertion Thruster Heater 3
Insertion Thruster Heater 4
Circuit #
Overall
Qty of Size Of
Resistance Htrs
Heater
(Ω)
(in2)
Max Watt
Setpoint
Density
Range (°C)
2
(W/in ) @35 V
145.80
146.00
179.20
91.00
91.00
91.00
91.00
146.00
44.80
145.80
145.80
145.80
145.80
145.80
145.80
145.80
189.00
189.00
189.00
189.00
2-11
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Thermostat
Part Number
Thermostat
Serial
Numbers
LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 2-12 Redundant Propulsion Heater Circuit Summary
Circuit Location
ACS Thruster Heater 1
ACS Thruster Heater 2
ACS Thruster Heater 3
ACS Thruster Heater 4
ACS Thruster Heater 5
ACS Thruster Heater 6
ACS Thruster Heater 7
ACS Thruster Heater 8
Insertion Prop Line 1
Insertion Prop Line 2
Insertion Prop Line 3
ACS Prop Line 1
ACS Prop Line 2
ACS Prop Line 3
ACS Prop Line 4
Fill Drain Line 1
Fill Drain Line 2
Tank Liquid Line +X
Tank Liquid Line -X
Insertion Thruster Deck
2.2
Circuit #
Overall
Qty of Size Of
Resistance Htrs
Heater
(Ω)
(in2)
Max Watt
Setpoint
Density
Range (°C)
2
(W/in ) @35 V
198.00
198.00
198.00
198.00
198.00
198.00
198.00
198.00
42.53
LOCATION OF HEATER CIRCUITS
The location of the heater circuits in Table 1 are outlined in Appendix C.
2-12
CHECK WITH LRO DATABASE AT: https://lunarngin.gsfc.nasa.gov
TO VERIFY THAT THIS IS THE CORRECT VERSION PRIOR TO USE.
Thermostat
Part Number
Thermostat
Serial
Numbers
LRO Thermal Hardware Specification
3.0
451-SPEC-000913
Revision - DRAFT
FLIGHT INTERFACE MATERIAL DESIGN
Table 2 outlines the interface material requirements between various components and their
mounting surfaces. Table 2 below lists the design temperature limits at the SC thermal interface.
Table 3-1 Interface Material Design
Subsystem/Instrument
Component
Interface Material
Power
Power Subsystem Electronics S/C I/F
at PSE
NuSil CV-2946/Teflon Film
S/C I/F at Battery
Dry Joint
S/C I/F at Star Trackers (Radiator I/F)
Cho- Seal 1285
S/C I/F at Inertial Measurement Unit
Cho- Seal 1285
S/C I/F at Reaction Wheels
Chotherm
S/C I/F at Coarse Sun Sensors
Dry Joint
Propulsion and Deployables
Electronics (PDE)
S/C I/F at PDE
Dry Joint/Cho- Seal 1285
C&DH
S/C I/F at C&DH
NuSil CV-2946/Teflon Film
S/C I/F at 9500 Oscillator
Dry Joint
S Band Comm
S/C I/F at S-band components
NuSil CV-2946/Teflon Film
Ka Band Comm
S/C I/F at Ka Baseband Modulator
Cho- Seal 1285
S/C I/F at Ka TWT
NuSil CV-2946/Teflon Film
S/C I/F at EPC
Cho- Seal 1285
S/C I/F at Gimbal Control Electronics
1 (Hi-Gain)
Cho- Seal 1285
S/C I/F at Gimbal Control Electronics
2 (S/A)
Cho- Seal 1285
Cosmic Ray Telescope of the
Effects of Radiation
(CRaTER)
S/C at I/F to CRaTER
Dry Joint
Diviner
S/C at I/F to Diviner Instr
Dry Joint
S/C at I/F to remote electronics box
Dry Joint
Lyman-Alpha Mapping
Project (LAMP)
S/C I/F at base of LAMP’s feet
Dry Joint
Lunar Exploration Neutron
Detector (LEND)
S/C at I/F to LEND
Dry Joint
S/C at I/F to Optics Package
Dry Joint
S/C at I/F to Instrument Electronics
Dry Joint
S/C at base of NAC
Dry Joint
S/C I/F at base of WAC
Dry Joint
S/C I/F at base of SCS
Dry Joint
Attitude Control System
(ACS)
Mechanisms
Lunar Orbiter Laser
Altimeter (LOLA)
Lunar Reconnaissance
Orbiter Camera (LROC)
3-1
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TO VERIFY THAT THIS IS THE CORRECT VERSION PRIOR TO USE.
LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Subsystem/Instrument
Component
Interface Material
Mini RF
S/C I/F at base of antennae’s feet
Dry Joint
S/C I/F at base of electronics feet
NuSil CV-2946/Teflon Film
RWA Heat Pipe Joints
RWA Baseplate HPs
RWA Baseplate HPs to Header HPs
NuSil CV-2946
Header HPs to Isotherm Panel
3-2
CHECK WITH LRO DATABASE AT: https://lunarngin.gsfc.nasa.gov
TO VERIFY THAT THIS IS THE CORRECT VERSION PRIOR TO USE.
LRO Thermal Hardware Specification
4.0
451-SPEC-000913
Revision - DRAFT
THERMISTOR AND PRT LOCATIONS
Table 3 specifies the number of spacecraft monitored temperature sensors allocated to each
component. The telemetry types listed only apply to the column in the table labeled ‘Number of
Telemetry Points’. The ‘Internal Box Telemetry’ sensors can be alternative telemetry types since
they may be read by alternative avionics. The current baseline for temperature sensors is 2252
ohms 311P18-02-A-101 or Platinum Resistance Thermometer (PRT) (0118MM2000CEALGC,
2000 ohms @ 0°C) as specified by the LRO Thermal Systems Lead. The thermistor/PRT shall
be capable of being read over all specified temperature ranges. The thermistor sensors shall be
accurate within 1.5 degree C from -40 to +75 C. The PRT sensors shall be accurate within 3.0
degree C from -170 to +145 C. The thermistor electrical interface shall be per the relevant
electrical ICD and the physical placement of each thermistor per the relevant thermal ICD
Table 4-1 below outlines the conventions and limits for all MAC, GCE, and PSE external
telemetry limits.
Table 4-1 MAC Thermistors and PRTs
Subsystem
Details
Telemetry
Pt. #
Op Limit
Surv Limit
Comp.
Instrument
Module
IM +Y face Top near Star
Trackers in –Z, +X
IM +Y face Top in –Z, -X
corner
IM +Y face in +Z, -X corner
IM +Y face in +Z, +X corner
IM +Y face
IM +X face
IM +X face
(+Z) Nadir Face near WAC
(+Z) Nadir Face near LOLA
(+Z) Nadir Face
-X Nadir Face corner
IM -Y face in -Z, +X corner
flexure
IM -Y face in +Z, +X corner
flexure
IM -Y face in +Z, -X corner
flexure
IM -Y face in -Z, -X corner
flexure
THM-1
THM-2
THM-3
THM-4
THM-5
THM-6
THM-7
THM-8
THM-9
THM-10
THM-11
THM-12
THM-13
THM-14
THM-15
4-3
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TO VERIFY THAT THIS IS THE CORRECT VERSION PRIOR TO USE.
Reference
Htr Circuit
LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 4-2 MAC Thermistors and PRTs (continued 1)
Subsystem
Details
(-Z) Zenith face near Star
Tracker -X
(-Z) Zenith face near Star
Tracker +X
(-Z) Zenith face near NAC1
(-Z) Zenith face near NAC 2
(-Z) Zenith face near –X corner
Star Tracker Radiator
Star Tracker Radiator
Telemetry
Pt. #
Op Limit
Surv Limit
THM-16
THM -17
THM-18
THM-19
THM -20
THM-21
THM-22
Thermal
Avionics Radiator
Avionics Radiator
Calorimeter
Calorimeter
Spare
Spare
Spare
THM-23
THM-24
THM-25
THM-26
THM-27
THM-28
THM-29
HGAS Deployment
Hinge/Rotary Joint
HGAS Damper
SAS Dampers +Z
SAS Dampers –Z
S/A GCE 2 Box IF
HGA GCE 1 Box IF
THM-30
Mechanisms
Thermal
Thermal
Control
Heaters (two
sensors per
heater)
THM-31
THM-32
THM-33
THM-34
THM-35
Rationale: If thermistor fails,
circuit fails
RWA Software Heater Cntrl
RWA Software Heater Red
Cntrl
ITP Heat Pipe Software Heater
Cntrl
ITP Heat Pipe Software Heater
Red Cntrl
LEND Op Heater (in C&DH)
LEND Op Heater (in C&DH)
Red Cntrl
THM-36
THM-37
THM-38
THM-39
THM-40
THM-41
4-4
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TO VERIFY THAT THIS IS THE CORRECT VERSION PRIOR TO USE.
Reference
Htr Circuit
LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 4-3 MAC Thermistors and PRTs (continued 2)
Subsystem
Details
Optical Bench for LROC +X
NAC I/F on –Z Panel (in
C&DH)
Optical Bench for LROC +X
NAC I/F on –Z Panel (in
C&DH) Red Cntrl
Optical Bench for LROC -X
NAC I/F on –Z Panel (in
C&DH)
Optical Bench for LROC -X
NAC I/F on –Z Panel (in
C&DH) Red Cntrl
Optical Bench for LROC -X
Panel near NAC (in C&DH)
Optical Bench for LROC -X
Panel near NAC (in C&DH)
Red Cntrl
Optical Bench for LROC +Z
panel near NAC (in C&DH)
Optical Bench for LROC +Z
panel near NAC (in C&DH)
Red Cntrl
LROC Instrument –X NAC
Structure Op Heater
LROC Instrument –X NAC
Structure Op Heater Red Cntrl
LROC Instrument +X NAC
Structure Op Heater
LROC Instrument +X NAC
Structure Op Heater Red Cntrl
LROC OB +Y Panel
LROC OB +Y Panel Red Cntrl
LROC OB -Y Panel
LROC OB -Y Panel Red Cntrl
Star Tracker OB I/F +X Panel
Star Tracker OB I/F +X Panel
Red Cntrl
Star Tracker OB I/F -X Panel
Star Tracker OB I/F -X Panel
Red Cntrl
Telemetry
Pt. #
Op Limit
Surv Limit
THM- 42
THM- 43
THM-44
THM- 45
THM-46
THM- 47
THM-48
THM- 49
THM-50
THM-51
THM-52
THM-53
THM-54
THM-51
THM-52
THM-53
THM-54
THM-55
THM-56
THM-57
4-5
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TO VERIFY THAT THIS IS THE CORRECT VERSION PRIOR TO USE.
Reference
Htr Circuit
LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 4-4 MAC Thermistors and PRTs (continued 3)
Subsystem
Propulsion
System
Details
Rationale: Need be able to
turn off a thermostatic heater
circuit if problematic. Fuel
temperatures must be
controlled.
+X Tank +X face circuit #2
+X Tank equator circuit #1
+X Tank –X face circuit #3
-X Tank +X face circuit #8
-X Tank equator circuit #4
-X Tank equator circuit #5
-X Tank equator circuit #6
-X Tank equator circuit #7
-X Tank -X face circuit #9
Cylinder Heater Circuit +X
hemisphere circuit
Cylinder Heater Circuit -X
hemisphere circuit Sensor #2
Pressurant Tank Heater Circuit
Sensor #1
Pressurant Tank Heater Circuit
Sensor #2
Insertion Prop Line 1
Insertion Prop Line 2
Insertion Prop Line 3
ACS Prop Line 1
ACS Prop Line 2
ACS Prop Line 3
ACS Prop Line 4
Fill Drain Line 1
Fill Drain Line 2
Tank Liquid Line +X
Tank Liquid Line –X
High Pressure Panel
Low Pressure Panel
Insertion Thruster Deck
Insertion Thruster Valve #1
Sensor #1
Insertion Thruster Valve #2
Sensor #1
Insertion Thruster Valve #3
Sensor #1
Insertion Thruster Valve #4
Sensor #1
Telemetry
Pt. #
Op Limit
Surv Limit
THM-58
THM-59
THM-60
THM-61
THM-62
THM-63
THM-64
THM-65
THM-66
THM-67
THM-68
THM-69
THM-70
THM-71
THM-72
THM-73
THM-74
THM-75
THM-76
THM-77
THM-78
THM-79
THM-80
THM-81
THM-82
THM-83
THM-84
THM-85
THM-86
THM-87
THM-88
4-6
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TO VERIFY THAT THIS IS THE CORRECT VERSION PRIOR TO USE.
Reference
Htr Circuit
LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 4-5 MAC Thermistors and PRTs (continued 4)
Subsystem
Cat Bed
Details
ACS Thruster Valve #1 Sensor
#1
ACS Thruster Valve #2 Sensor
#1
ACS Thruster Valve #3 Sensor
#1
ACS Thruster Valve #4 Sensor
#1
ACS Thruster Valve #5 Sensor
#1
ACS Thruster Valve #6 Sensor
#1
ACS Thruster Valve #7 Sensor
#1
ACS Thruster Valve #8 Sensor
#1
Cat Bed PRTs Insertion
Thrusters #1
Cat Bed PRTs Insertion
Thrusters #2
Cat Bed PRTs Insertion
Thrusters #3
Cat Bed PRTs Insertion
Thrusters #4
Cat Bed PRTs ACS Thruster
#1
Cat Bed PRTs ACS Thruster
#2
Cat Bed PRTs ACS Thruster
#3
Cat Bed PRTs ACS Thruster
#4
Cat Bed PRTs ACS Thruster
#5
Cat Bed PRTs ACS Thruster
#6
Cat Bed PRTs ACS Thruster
#7
Cat Bed PRTs ACS Thruster
#8
Telemetry
Pt. #
Op Limit
Surv Limit
THM-89
THM-90
THM-91
THM-92
THM-93
THM-94
THM-95
THM-96
PRT-151
PRT-152
PRT-153
PRT-154
PRT-155
PRT-156
PRT-157
PRT-158
PRT-159
PRT-160
PRT-161
PRT-162
4-7
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TO VERIFY THAT THIS IS THE CORRECT VERSION PRIOR TO USE.
Reference
Htr Circuit
LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 4-6 MAC Thermistors and PRTs (continued 5)
Telemetry
Pt. #
Subsystem
Details
Gimbals
S/A Gimbal Y axis Actuator
S/A Gimbal X axis Actuator
HG Gimbal Y axis Actuator
HG Gimbal X axis Actuator
+Y HGAS Rotary Joint Heater
Circuit
+X HGAS Rotary Joint Heater
Circuit
High Gain Antenna
High Gain Antenna
High Gain Antenna
S Band Patch
LEND Radiator (?)
THM-97
THM-98
THM-99
THM-100
PRT-163
CRaTER Radiator
LR Telescope
THM-102
PRT-169
Battery SC I/F
PSE SC I/F
Solar Array Substrate CSS
Monitor +Z
Solar Array Substrate CSS
Monitor –Z
PDE S/C I/F
+X Star Tracker S/C I/F
-X Star Tracker S/C I/F
IMU S/C I/F
Reaction Wheel +X +Y S/C I/F
Reaction Wheel +X -Y S/C I/F
Reaction Wheel -X +Y S/C I/F
Reaction Wheel -X –Y S/C I/F
C&DH Box Essential Heater
Location
9500 Oscillator Internal
Chassis (30 kohm thermistor)
9500 Oscillator Internal Oven
(30 kohm thermistor)
TT&C XPDR Stack (xmit)
TT&C XPDR Stack (Rec)
TT&C Omni Antenna +X
TT&C Omni Antenna -X
THM-103
THM-104
THM-105
Instrument
Radiators
Laser Receiver
Telescope
Power
ACS
C&DH
S-Comm
Op Limit
Surv Limit
PRT-164
PRT-165
PRT-166
PRT-167
PRT-168
THM-101
THM-106
THM-107
THM-108
THM-109
THM-110
THM-111
THM-112
THM-113
THM-114
THM-115
THM-116
THM-117
THM-118
THM-119
THM-120
THM-121
4-8
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TO VERIFY THAT THIS IS THE CORRECT VERSION PRIOR TO USE.
Reference
Htr Circuit
LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 4-7 MAC Thermistors and PRTs (continued 6)
Subsystem
Details
Ka Comm
Ka Baseband Modulator
Ka EPC
Ka TWTA Sensor#1
Ka TWTA Sensor#2
Isolator
CRaTER Telescope
Diviner OBA
Diviner Az Actuator
Diviner Elev Actuator
Diviner DREB
Diviner Yoke
LAMP Reference Point
LAMP (instrument requested
thermistor)
LEND Elect
LEND Doppler Detector
LOLA OTA Laser Bench
LOLA OTA Receiver Tube
Flange
LOLA MEB PCA Sidewall
SCS FPGA
WAC Focal Plane
NAC+X FPGA
NAC+X Focal Plane
NAC+X Metering Structure
NAC –X FPGA
NAC –X Focal Plane
NAC –X Metering Structure
Mini-RF Transmitter Box
Mini-RF Processor Box
Mini-RF Analog Receiver Box
(instrument requested
thermistor)
Mini-RF Antenna
EPOC Camera
Instruments
EPOC
Telemetry
Pt. #
Op Limit
Surv Limit
THM-122
THM-123
THM-124
THM-125
THM-126
PRT-170
THM-127
THM-128
THM-129
THM-130
THM-131
THM-132
THM-133
THM-134
THM-135
THM-136
THM-137
THM-138
THM-139
THM-140
THM-141
THM-142
THM-143
THM-144
THM-145
THM-146
THM-147
THM-148
THM-149
PRT-171
THM-150
171 Total
4-9
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TO VERIFY THAT THIS IS THE CORRECT VERSION PRIOR TO USE.
Reference
Htr Circuit
LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 4-8 GCE 1 and 2 Temperature Sensors
Telemetry
Designation
GCE Specification
GCE 1 Primary Side
GCE 1 Primary Side
GCE 1 Primary Side
GCE 1 Primary Side
GCE 1 Primary Side
GCE 1 Primary Side
GCE 1 Primary Side
GCE 1 Primary Side
GCE 1 Redundant
Side
GCE 1 Redundant
Side
GCE 1 Redundant
Side
GCE 1 Redundant
Side
GCE 1 Redundant
Side
GCE 1 Redundant
Side
GCE 1 Redundant
Side
GCE 1 Redundant
Side
GCE 2 Primary Side
GCE 2 Primary Side
GCE 2 Primary Side
GCE 2 Primary Side
GCE 2 Primary Side
GCE 2 Primary Side
GCE 2 Primary Side
GCE 2 Primary Side
Details
GCE1 Internal
L/V I/F at S/C I/F
HPCM
LPCM
Avionic Structure
+Z face
Avionic Structure -Z
face
Avionics Structure
+Y face
Avionics Structure Y face on Solar
Array support
structure
GCE1 Internal
GCE1PRTR-1
L/V I/F at S/C I/F
GCE1PRTR-2
HPCM
GCE1PRTR-3
LPCM
GCE1PRTR-4
Avionic Structure
+Z face
Avionic Structure -Z
face
Avionics Structure
+Y face
Avionics Structure Y face on Solar
Array support
structure
GCE2 Internal
AP Radiators +Y
+X Corner
AP Radiators -Y +X
Corner
AP Radiators +Y -X
Corner
AP Radiators -Y X Corner
AP Radiator
Battery Radiator +Y
side
Battery Radiator -Y
side
GCE1PRTR-5
Operational
Limit
Survival
Limit
GCE1PRTP-1
GCE1PRTP-2
GCE1PRTP-3
GCE1PRTP-4
GCE1PRTP-5
GCE1PRTP-6
GCE1PRTP-7
GCE1PRTP-8
GCE1PRTR-6
GCE1PRTR-7
GCE1PRTR-8
GCE2PRTP-1
GCE2PRTP-2
GCE2PRTP-3
GCE2PRTP-4
GCE2PRTP-5
GCE2PRTP-6
GCE2PRTP-7
GCE2PRTP-8
4-10
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TO VERIFY THAT THIS IS THE CORRECT VERSION PRIOR TO USE.
Heater
Circuit
Reference
LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 4-9 GCE 1 and 2 Temperature Sensors (continued)
Telemetry
Designation
GCE Specification
GCE 2 Redundant
Side
GCE 2 Redundant
Side
GCE 2 Redundant
Side
GCE 2 Redundant
Side
GCE 2 Redundant
Side
GCE 2 Redundant
Side
GCE 2 Redundant
Side
GCE 2 Redundant
Side
Operational
Limit
Survival
Limit
Details
GCE2PRTR-1
GCE2 Internal
AP Radiators +Y
+X Corner
AP Radiators -Y +X
Corner
AP Radiators +Y -X
Corner
AP Radiators -Y X Corner
AP Radiator
Battery Radiator +Y
side
Battery Radiator -Y
side
GCE2PRTR-2
GCE2PRTR-3
GCE2PRTR-4
GCE2PRTR-5
GCE2PRTR-6
GCE2PRTR-7
GCE2PRTR-8
4-11
CHECK WITH LRO DATABASE AT: https://lunarngin.gsfc.nasa.gov
TO VERIFY THAT THIS IS THE CORRECT VERSION PRIOR TO USE.
Heater
Circuit
Reference
LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 4-10 Internal Box Thermistors
Subsystem
Mechanis
ms
Details
Measurement
Location
Telemetry
Designation
PSE internal
PSE internal
PSE internal
PSE internal
PSE internal
PSE internal
PSE internal
Battery internal
Battery internal
S/A Panels
S/A Panels
S/A Panels
S/A Panels
PSETHM-1
PSETHM-2
PSETHM-3
PSETHM-4
PSETHM-5
PSETHM-6
PSETHM-7
PSEPRT-1
PSEPRT-2
PSEPRT-3
PSEPRT-4
PSEPRT-5
PSEPRT-6
Reaction Wheel
+X +Y internal
Reaction Wheel
+X -Y internal
Reaction Wheel
-X +Y internal
Reaction Wheel
-X –Y internal
RWATHM-1
C&DH Internal
#1
C&DH Internal
#1
C&DH Internal
#1
C&DH Internal
#1
C&DH Internal
#1Heater
C&DH Internal
#1
C&DH Internal
#1
CDHTHM-1
Op
Limit
Surv
Limit
ACS
RWATHM-2
RWATHM-3
RWATHM-4
C&DH
CDHTHM-2
CDHTHM-3
CDHTHM-4
CDHTHM-5
CDHTHM-6
CDHTHM-7
Total
Allowable
4-12
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TO VERIFY THAT THIS IS THE CORRECT VERSION PRIOR TO USE.
Heater
Circuit
Reference
LRO Thermal Hardware Specification
451-SPEC-000913
Revision - DRAFT
Table 4-11 GSE Umbilical Temperature Telemetry
Telemetry
Designation
Subsystem
Propulsion
Op Limit
Details
+X Prop Fuel Tank -X
Hemisphere
+X Prop Fuel Tank +X
Hemisphere
-X Prop Fuel Tank +X
Hemisphere
-X Prop Fuel Tank -X
Hemisphere
Pressurant Tank
UTHM-1
UTHM-2
UTHM-3
UTHM-4
UTHM-5
Total
Allowable
4-13
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TO VERIFY THAT THIS IS THE CORRECT VERSION PRIOR TO USE.
Surv Limit
LRO Thermal Hardware Specification
5.0
451-SPEC-000913
Revision - DRAFT
THERMAL COATINGS
The S/C has six distinct radiator locations on its main body and four distinct radiators on the
deployables. The isolated instruments all have radiators whose coatings are controlled by the
instrument developers but verified via system level thermal analysis and instrument level thermal
balance testing. The remainder of the spacecraft will be covered in MLI blankets with the
exception of the solar array, instrument and RF apertures and antennas, launch vehicle interface
and propulsion thruster shields and portions of the thrusters.
Table 5-1 Orbiter Thermal Coatings Overview
Subsystem
Power
ACS
Mechanisms
Instruments
Location
Back of Solar Array
CSS Mount
SAS Actuator Radiators Qty 2 but different
designs
HGAS Actuator Radiators Qty 2 but different
designs
2 Omni Antennas
Feed Horn
+X Star Tracker Radiator
-X Star Tracker Radiator
LEND Radiator
CRaTER Radiator
Battery Radiator
Avionics Radiator
LROC WAC radiator and radiator shield
LROC NAC+X and –X radiator and radiator
shield
LROC SCS radiator and radiator shield
Instruments
Instruments
Instruments
LAMP Radiator
LOLA OTA
LOLA MEB
HGAS
Comm
Comm
Thermal
Thermal
Thermal
Thermal
Thermal
Thermal
Instruments
Instruments
Thermal Coating
RM-400
NS43C
NS43C Outside
Z306 Black Paint inside
NS43C Outside
Z306 Black Paint inside
A276
NS43C
NS43C
NS43C
5 mil ITO OSRs
5 mil ITO OSRs
5 mil ITO OSRs
5 mil ITO OSRs
NS43C outside + VDA inside
NS43C outside + VDA inside
NS43C on top face of
electronics only
NS43C
NS43C
NS43C
5-14
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LRO Thermal Hardware Specification
5.1
451-SPEC-000913
Revision - DRAFT
THERMAL RADIATOR COATINGS
Small radiators, including the two star tracker radiators and the four deployables actuator
radiators, will be coated with NS43C white paint. All of the remaining large radiators, including
the Avionics radiator, will be coated with 5 mil Pilkington Optical Solar Reflectors (OSRs) TBD
part number. The two small spacecraft radiators for the LEND and CRaTER instruments will
also be covered with the same OSRs. The radiator locations are shown on Figure 5-2 and 5-3 for
the spacecraft and deployables respectively.
Figure 5-1 Spacecraft Radiator Locations and Thermal Coatings
Avionics Radiator (OSRs)
Battery
Radiator
(OSRs)
CRaTER
Radiator
(OSRs)
Star
Tracker
Radiators
(NS43C)
LEND
Radiator
(OSRs)
Figure 5-2 Thermal Coatings Overview
Figure 5-3 HGAs Thermal Coatings Overview
5-15
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LRO Thermal Hardware Specification
5.2
451-SPEC-000913
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LAUNCH VEHICLE INTERFACE AND SOLAR ARRAY COATINGS
The launch vehicle interface shall be covered to the largest extent allowable with MLI blankets.
This is to minimize the radiative and flux coupling with the environment. The solar array has a
M55J honeycomb structure. On the active side all gaps between the cells shall be left in bare
M55J. On the backside of the array, all surfaces shall be covered with RM-400 white paint.
The launch vehicle interface shall be coated as shown in Figure 5-4.
White Paint
Irridite
Blanketed
1.2”
1.5”
Additional
White
Paint
0.6”
0.9”
Figure 5-4 Launch Vehicle Thermal Coatings
5-16
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LRO Thermal Hardware Specification
6.0
451-SPEC-000913
Revision - DRAFT
MULTI-LAYER INSULATION COATING LOCATIONS
Appendix B outlines all of the blanket layups used on the spacecraft and assigns them B1-B7
designations.
6.1
SUNSIDE –Y FACE
The blankets on the –Y FACE shall have a B3 blanket. This includes the OMNI boom. The only
exceptions are the solar array standoffs which will be aluminum taped (?) and at the solar array
deployment hinge, where MLI will be minimal so as not to interfere with deployment.
6.2
ANTI- SUNSIDE +Y FACE
The blankets on the orbiter body shall be B3 Blankets. The Instrument Module (IM) shall have
B5 Blankets. The instruments shall also have B5 blankets on their non-radiator surfaces.
Between the IM and the orbiter body there will be MLI closeout. This closeout will be a single
layer of 2.6mil scrim Germanium Black Kapton (GBK). See Figure 6.2 for reference.
Figure 6-1 Orbiter Reference for MLI
.
6-17
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LRO Thermal Hardware Specification
6.3
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Revision - DRAFT
NADIR -Z FACE
The blankets on the –Z orbiter body shall be B3 Blankets. There will be an opening in the MLI to
access the propulsion high pressure panel. This opening will be able to be closed after the last
propulsion activity on the pad. The MiniRF antenna will have a blanket closeout to the spacecraft
body. This closeout will be a single layer (TBD) of 2.6mil GBK. The design is shown in figure
6.3.
Figure 6-2 Mini RF MLI Closeout
6-18
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LRO Thermal Hardware Specification
6.4
451-SPEC-000913
Revision - DRAFT
ZENITH +Z FACE
The blankets on the +Z orbiter body shall be B3 Blankets where possible. This side of the
spacecraft is mainly the avionics and battery radiator. There are cutouts in the radiator to allow
for High Gain Antenna (HGA) stowing and deployment. These areas shall be blanketed as much
as possible with B3 and single layer GBK without interfering with the deployment of the HGA.
Around the radiator there shall be a light tight closeout to prevent straylight from entering behind
the radiator. This closeout will be single layer GBK. The MLI will closeout to the radiator. This
attachment will be made with silver Teflon tape for 1” around the perimeter of the radiator.
Under the tape there will be no blanket. Rather, the blanket shall end on the edge of the radiator.
This will be done in order to minimize the amount of ineffective radiator.
6.5
+X FACE
This face of the spacecraft has the battery mounted to it. This face is also framed with raised
spacecraft walls that act as the HGA mounting structure. In order for sunlight not to get trapped
in the crevices, the battery has an extra large MLI tent on all sides. See figure 6.5 for an
illustration. This tent, as well as the rest of the deck MLI, will be made of B3 blankets.
Figure 6-3 Figure TBD
6-19
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6.6
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–X FACE
The –X face of the orbiter has a couple of unique features. There is a launch vehicle adapter
(LVA) ring. This ring will be painted as well as blanketed (see Section 5.2 for more details). The
blanket will be a B4 blanket with Kapton facing out. This face also has an insertion thruster
deck, where the four twenty pound insertion thrusters are mounted. This deck will have a B4
blanket on the entire deck. Right around the thrusters there will be a B6 and B7 blanket on top of
the B4 blanket. See figure 6.6 for sketch. Each of the thruster bodies (by the valves) will be
wrapped in a B4 blanket. On top of the thruster mounting bracket there will a “hat” of B4
blankets. The front face of the thruster mounting bracket will have a B7 blanket on top of the B4
blanket. The ACS thrusters shall have B6 and B7 blankets on the thruster side of the bracket. The
rest of the ACS bracket will be covered in B4 blankets. The aft deck is also located on the –X
face of the orbiter. It is important for the aft deck to be well insulated due to the fact that the aft
propulsion fuel tank mounts directly to it. The aft deck will have a B3 blanket on the +X side of
the deck and a B4 blanket on the –X side of the deck. The –X side of the deck is deeply hogged
out and the ACS propellant lines are routed there. In order to well insulate the propellant lines
and facilitate the blanketing of a highly non planar surface, the –X aft deck blanket will be stood
off of the deck by approximately 3” by using L-brackets designed for MLI attachment.
Figure 6-4 High Temperature Blankets by Insertion Thrusters
6-20
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6.7
451-SPEC-000913
Revision - DRAFT
INTERNAL PROPULSION BLANKETS
The bottom of the –X propulsion tank will be blanketed with a B1 blanket. See figure 6.7 for a
photo of the MLI on a mock up. The +X side of the –X propulsion tank shall have a single layer
of VDA2 Kapton that covers the tank from the flange up for 4” towards the +X pole. The +X
side of the +X propulsion tank shall have a single layer of VDA2 Kapton covering the entire half
of the tank. Supporting the +X tank is the propulsion support cylinder. Running on the exterior
of this cylinder are 75% of the propulsion lines, the high pressure, the low pressure and the filter
panels. The cylinder, as well as all propulsion lines and panels within 5” (TBD) will be enclosed
in one B1 blanket. This blanket will be supported off the walls of the cylinder by two (TBD)
rings that will be stood off of the cylinder walls. All propulsion lines not supported off of the
heater portion of the cylinder will be individually blanketed with B2 blankets, except for the
insertion lines which will be blanketed with single layer of VDA2. The pressurant tank will also
be blanketed. The pressurant tank will be surrounded by a 0.08” (TBD) thick aluminum
expandable shell. This shell will support the MLI blanket as well as the pressurant tank heaters
and thermostats. The MLI in this area will need to be loose enough to accommodate a 1”
increase in diameter of the pressurant tank when it is fully pressurized.
Figure 6-5 –X Propulsion Tank MLI
6.8
MULTI-LAYER INSULATION BLANKET GROUNDING
All blankets shall be grounded in accordance with the Lunar Reconnaissance Orbiter Electrical
Systems Specification (431-ICD-000008).
6.9
ATTACHMENT OF MULTI-LAYER INSULATION BLANKETS
All exterior MLI blankets shall be mechanically constrained at least at one point or mechanically
captured by another blanket or mechanical component.
6-21
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LRO Thermal Hardware Specification
6.10
451-SPEC-000913
Revision - DRAFT
VENTING OF MULTI-LAYER INSULATION
MLI shall be vented according to Contamination Engineering specifications outlined in the
following two figures.
Figure 6-6 IM MLI Venting Scheme
6-22
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451-SPEC-000913
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Figure 6-7 Orbiter Venting Scheme
The maximum acceptable pressure differential within a thermal blanket during launch/ascent
depressurization has been established as 0.1 psf (0.007 psi) to prevent “ballooning” of the
blanket and possible detachment during launch/ascent depressurization. For the Delta II launch
vehicle, having approximately 0.3psi/secdecay during launch/ascent, this requires 1 in2 of
effective vent area for each 4000 in3 of enclosed volume.
The use of filters to minimize particulate contamination from being blown out during
depressurization requires vent sizing using the effective open area of the filter material. GSFC
practice is to vent thermal blankets at the perimeter with filtered gaps in the taped edge closeout.
These filters must present sufficient open vent area (AOPEN) to meet the maximum pressure
differential requirement specified above. The standard filter used in NASA GSFC thermal
blankets fabricated in Building 7 is a 70m filter (SpectraMesh PN: P-06630-74F) that
provides 20% open area and has been approved (TBC) by the LRO contamination engineer
based on GLAS testing. The filter “efficiency” proportionally reduces the volume that can
adequately be vented to 800 in3 of enclosed volume for each 1 in2 of vent area.
LRO vent/filters should be as shown in Figure 6-8, with a minimum of 1.0” exposed filter length
(Figure 6-8) with care taken not to compress the edge of the blanket to < 1/8”. This should
provide an area of 0.125 in2 per vent, which could theoretically vent up to 100 in3 of blanket
(approximately 28” x 28” x 1/8” thick). However, to prevent air from being trapped in pockets
created from conforming the blankets to the surfaces they are mounted to, blanket design should
have a minimum of one vent per edge for regularly shaped blankets with a maximum spacing of
24” between vents around the blanket perimeter. For odd shaped blankets, at least 1 vent shall be
provided in any “isolated” section of the blanket with each section subject to the perimeter
spacing requirements above.
6-23
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Venting of the all honeycomb panels requires much larger vent areas due to the large internal
volumes to be vented. [Vent areas needed go here] Again, at least one vent should be used on
each edge of the honeycomb panels with no more than 24” spacing between them.
All blankets mounted to components internal to the main LRO volume will be vented into the
volume, but directed preferentially away from contamination sensitive optical surfaces, to the
maximum extent practical. The volume is defined as the sum of the volumes formed by the
planes of the Propulsion Panels.
All blankets exposed to space are to be vented directly to space and not into the main LRO
volumes. These vents shall be located away from thermal radiator surfaces and apertures (Star
Tracker and Instrument) to the maximum extent practical.
Figure 6-8 Blanket Filter
6-24
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Appendix A. Abbreviations and Acronyms
Abbreviation/
Acronym
ACS
ºC
C&DH
CBE
CCB
CCR
CDR
CM
CMO
CRaTER
Diviner
ELV
EPC
EVD
GEVS
GSFC
HGA
HKIO
Htrs
I&T
I/F
ICD
IR
IMU
Km
LAMP
LEND
LOLA
LROC
LRO
LVPC
Max.
Min.
MLI
Mo.
MTG
N/A
NAC
NASA
NC
OP
DEFINITION
Attitude Control System
Degrees Centigrade
Command and Data Handling
Current Best Estimate
Configuration Control Board
Configuration Change Request
Critical Design Review
Configuration Management
Configuration Management Office
Cosmic Ray Telescope of the Effects of Radiation
Diviner Instrument
Expendable Launch Vehicle
Electrical Power Conditioner
Engine Valve Driver
General Environmental Verification Standards
Goddard Space Flight Center
High Gain Antenna
House Keeping Input Output
Heaters
Integration and Test
Interface
Interface Control Document
Infared
Inertial Measurement Unit
Kilometer
Lyman-Alpha Mapping Project
Lunar Exploration Neutron Detector
Lunar Orbiter Laser Altimeter
Lunar Reconnaissance Orbiter Camera
Lunar Reconnaissance Orbiter
Low Voltage Power Converter
Maximum
Minimum
Multi-Layer Insulation
Months
Mounting
Not Applicable
Narrow Angle Camera
National Aeronautics and Space Administration
Normally Closed
Operational
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LRO Thermal Hardware Specification
Abbreviation/
Acronym
PDE
PDR
PER
PRT
PSE
Psi
Pts
Pwr
RF
RGMM
RTMM
RWA
S/A
SBC
SC
SCS
Sec.
SINDA
SOL
Spec.
SSR
STS
TBD
TBR
TSS
TT&C
TWTA
USB
VDA
W
w/o
W/cm2
W/in2
W/m2
WAC
XPDR
V
451-SPEC-000913
Revision - DRAFT
DEFINITION
Propulsion and Deployable Electronics
Preliminary Design Review
Pre-Environmental Review
Platinum Resistance Thermistor
Power Subsystem Electronics
Pounds per square inch
Points
Power
Radio Frequency
Reduced Geometric Math Model
Reduced Thermal Math Model
Reaction Wheel Assembly
Solar Array
Single Board Computer
Spacecraft
Sequencing and Compressor System
Seconds
Systems Improved Numerical Differencing Analyzer
Solar
Spectularity
Solid State Recorder
Space Transportation System
To Be Determined
To Be Reviewed
Thermal Synthesizer System
Telemetry Tracking and Control
Traveling Wave Tube Amplifier
Universal System Bus
Vapor Deposited Aluminum
Watt
Without
Watts per centimeter squared
Watts per inch squared
Watts per meter squared
Wide Angle Camera
Transponder
Volt(s)
A-2
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Appendix B: Blanket Descriptions and Designations
B-1
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B-2
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LRO Thermal Hardware Specification
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B-3
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LRO Thermal Hardware Specification
451-SPEC-000913
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B-4
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