SSP 42003, Part 2, Revision A National Aeronautics and Space Administration International Space Station Program Johnson Space Center Houston, Texas International Space Station Program Space Station Manned Base to Mobile Servicing System Interface Control Document Part 2 Revision A, MAY 22, 1997 Type 1 Approved by NASA
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SSP 42003, Part 2, Revision A
National Aeronautics and Space AdministrationInternational Space Station ProgramJohnson Space CenterHouston, Texas
International Space StationProgram
Space Station Manned Base toMobile Servicing SystemInterface Control DocumentPart 2
Revision A,
MAY 22, 1997
Type 1Approved by NASA
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
REVISION AND HISTORY PAGE
REV. DESCRIPTION PUB.DATE
– Initial Release (Reference per SSCD 000298, EFF. 05/08/96) 07–19–96
A Revision A (Reference per SSCD 000730, EFF. 10/23/97) 04–16–98
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
i
PREFACE
SSP 42003, Space Station Manned Base to Mobile Servicing System Interface ControlDocument, Part 2, shall be implemented on all new Program contractural and internal activityand shall be included in any existing contracts through contract changes. This document is underthe control of the Space Station Control Board (SSCB) with the concurrence of the respectiveInternational Partners, any changes or revisions will be approved by the SSCB and the respectiveInternational Partners.
/s/ Denny A. Kross 5–2–96
Program Manager, DateInternational Space Station
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
ii
NASA/CSA
INTERNATIONAL SPACE STATION PROGRAM
SPACE STATION MANNED BASE TO MOBILE SERVICING SYSTEMINTERFACE CONTROL DOCUMENT PART 2
DATE
Print Name
For NASA
C. A. Hatfield
/s/ C. A. Hatfield 3/11/96
DATE
Print Name
For CSA
R. G. Brown
/s/ R. G. Brown 3/6/96
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
iii
INTERNATIONAL SPACE STATION PROGRAM
SPACE STATION MANNED BASE TO MOBILE SERVICING SYSTEMINTERFACE CONTROL DOCUMENT PART 2
CONCURRENCE
PREPARED BY:
CHECKED BY:
SIGNATURE
SUPERVISED BY (NASA):
PRINT NAME ORGN
DATE
SIGNATURE
PRINT NAME ORGN
DATE
SUPERVISED BY (BOEING):
SIGNATURE
PRINT NAME ORGN
DATE
SIGNATURE
PRINT NAME ORGN
DATE
DQA:
SIGNATURE
PRINT NAME ORGN
DATE
Michael A. Stager
/s/ Michael A. Stager
26940
3/11/96
Steve Cox
/s/ Steve Cox
26940
3/11/96
Howard Griffin
/s/ Howard Griffin
26940
3/11/96
Frank Monahan
/s/ Frank Monahan
OB–1
3/11/96
Freddie G. Young
/s/ Freddie G. Young
OB–5
10/23/97
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
iv
CONCURRENCE
INTERNATIONAL SPACE STATION PROGRAM
SPACE STATION MANNED BASE TO MOBILE SERVICING SYSTEMINTERFACE CONTROL DOCUMENT PART 2
Product Group–1 ICWG
Product Group–3 ICWG
SIGNATURE
PRINT NAME
DATE
SIGNATURE
PRINT NAME
DATE
Representative for Concurrence
Representative for Concurrence
SPAR
SIGNATURE
PRINT NAME
DATE
Product Group–2 ICWG
SIGNATURE
PRINT NAME
DATE
Representative for Concurrence
Representative for Concurrence
Lee Archibald
/s/ Lee Archibald 3/29/96
N/A
N/A
Ralph Thompson
/s/ Lowell E. Cook for Ralph Thompson 2/22/96
P. Chadwick
/s/ P. Chadwick 4/3/96
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
v
INTERNATIONAL SPACE STATION PROGRAM
SPACE STATION MANNED BASE TO MOBILE SERVICING SYSTEM INTERFACE CONTROL DOCUMENT PART 2
LIST OF CHANGES
MAY 22, 1997
All changes to paragraphs, tables, and figures in this document are shown below:
SSCBD ENTRY DATE CHANGE PARAGRAPH(S)
TABLE(S)
FIGURE(S)
APPENDIX(ES)
ADDENDA
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
1 - 1
1.0 INTRODUCTION
1.1 PURPOSE AND SCOPE
This Interface Control Document (ICD) Part 2 defines and controls the physical and functionalinterfaces between the United States On–Orbit Segment (USOS) of International Space Station(ISS) and the Canadian Mobile Servicing System (MSS).
1.2 PRECEDENCE
In the event of conflict between SSP 41000, Space Station System Specification, and thecontents of this ICD, the requirements of SSP 41000 shall take precedence.
1.3 RESPONSIBILITY AND CHANGE
This document is prepared and maintained in accordance with SSP 30459, International SpaceStation Interface Control Plan. The National Aeronautics and Space Administration (NASA)shall delegate the responsibility for preparation and maintenance of this ICD Part 2.
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
2 - 1
2.0 APPLICABLE DOCUMENTS
The following documents of the date and issue shown include specifications, models, standards,and form a part of this document to the extent specified herein.
DOCUMENT NO. TITLE
SSQ 21635 Connectors and accessories, Electrical, Circular Miniature,IVA/EVA Compatible, Space Quality, General SpecificationFor
SSP 42000 Space Station Manned Base to Japanese Experiment ModuleRev J Interface Control Document11/7/95
SSP 42004, Part 2 Mobile Servicing System to User (Generic) InterfaceControl Document, Part 2
SSP 30256:001 EVA Standard Interface Control DocumentRev E3 Oct 94
SSP 41000 Space Station System Specification
SSP 30245 Space Station Electrical Bonding Requirements
SSP 30459 International Space Station Interface Control Plan
SSP 42003, Part 1 Space Station Manned Base to Mobile Servicing SystemInterface Control Document, Part I
SSP 30482 Electrical Power Specification and Standards, Volumes I and II
SSQ 21655 General Specifications for Cable Electrical, MIL–STD–1553,Data Bus, Space Quality
MIL–STD–1553 Digital Time Division Command/Response Multiplex Databus
CSA–SS–ID–0002 Canadian Space Vision System (CSVS) Interface ControlDocument (ICD) MRCS/AVU
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
A3 – 1
SECTION A3 MOBILE TRANSPORTER TO MRS BASE SYSTEM INTERFACE
A3 INTERFACE DEFINITION
A3.1 GENERAL
A3.1.1 INTERFACE DESCRIPTION
The physical interface (mechanical, structural, thermal and environmental) plane is defined atthe Mobile Remote Servicer (MRS) Base System (MBS) mounting surface at the MobileTransporter (MT). The electrical power, data and video interface plane is defined between theMBS electrical harness and the MT connector panel.
A3.1.2 INTERFACE RESPONSIBILITIES
CSA is responsible for development of the MBS. NASA is responsible for development of theMT. Interface responsibilities for the MT to MBS interface are as defined in SSP 42003 Part I,Section A and as described in SSP 42003 Part II, Section A herein.
A3.1.3 ENGINEERING UNITS AND TOLERANCES
Unless otherwise noted herein, all dimensions in this document are shown in the English systemof inch pound (IP) units.
A3.2 STRUCTURAL/MECHANICAL INTERFACES
MBS structurally attaches to the MT via a four fastener interface. The MT side of the MBS toMT mechanical interface will be as shown in Figures A3.2–2 through A3.2–7 (Figure A3.2–1has been deleted). The MBS side of the MBS to MT interface will be as shown in FiguresA3.2–8 through A3.2–11.
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A3 – 2
A3.2.1 MBS/MT INTERFACE HARNESS DESIGN
The MBS/MT interface harnesses design is shown in Figure A3.2.1–1.
A3.2.2 DELETED
A3.2.3 UTILITY INTERFACES
The assigned Electrical Reference Designations for MBS/MT harness connectors are shown inFigure A3.2.1–1.
A3.3 THERMAL INTERFACES
The MT side of the MBS to MT thermal interface implementation will be as defined in FiguresA3.2–2 through A3.2–7. The MBS side of the MBS to MT thermal interface implementationwill be as defined in Figures A3.2–8 and A3.2–11.
The temperature differential will be equal to or lower than the maximum allowable. It will beachieved by an assembly procedure to allow sufficient time between initial capture of the MT bythe MBS capture latch and the attachment of four fasteners by Extravehicular Activity (EVA).
A3.4 ELECTRICAL INTERFACES
The Space Station Manned Base (SSMB) will provide power, data, and PFM copper videointerfaces to the MBS via the MT and Trailing Umbilical System (TUS) as defined in FiguresA3.4–1 and A3.4–2. The MBS will provide EVA electrical outlets for SSMB tools withelectrical interfaces as defined in Figure A3.4–3.
A3.4.1 POWER, RETURN AND GROUNDING INTERFACES
The SSMB will provide power, return, and grounding interfaces to the MBS via the MT asdefined in Figure A3.4–1. For detailed electrical schematic and connectivity diagram, includingthe harness, refer to Figure A3.2.1–1.
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A3 – 3
A3.4.2 POWER CONNECTORS AND PIN ASSIGNMENTS
The prime and redundant harness power connectors and pin assignments for the MT connectorpanel will be as defined in Figure A3.2.1–1.
The MBS EVA outlet connectors and pin assignments will be as defined in Table A3.4.2–1 andA3.4.2–2.
A3.4.3 DATA AND PULSE FREQUENCY MODULATION (PFM) SYNC AND CONTROL ANDVIDEO INTERFACES
The SSMB will support 1553 data and PFM sync and control and video interfaces between theSSMB and the MBS via the MT and TUS. PFM copper video will be carried between the MBSand the MT. For detailed electrical schematic and connectivity diagram, including the harness,refer to Figure A3.2.1–1.
A3.4.3.1 DATA AND VIDEO CONNECTORS AND PIN ASSIGNMENTS
The harness data and video connectors and pin assignments for the MBS/MT harness will be asdefined in Figures A3.2.1–1.
A3.4.3.2 MSS VIDEO PROVISIONS
During SSRMS or MBS POA operations, the MSS will provide, via the MBS, PFM sync andcontrol and video capability as defined in SSP 42004, Part 2, Table A3.4.4–1.
The External Video Switches (VSW(E)) will provide to the MBS via TUS A and TUS B, threevideo channels.
The External Video Switches (VSW(E)) will provide to the MBS, via TUS A and TUS B, twosimultaneous PFM sync and control signals.
A3.5 ENVIRONMENTS
The MBS to MT electromagnetic, grounding and bonding interface implementation will be asdefined in Figures A3.2–2 through A3.2–7 for the MT side of the interface and A3.2–8 throughA3.2–11 for the MBS side of the interface.
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A3 – 4
A3.6 SOFTWARE INTERFACES
There are no software interfaces between the MBS and the MT.
A3.7 EVA HARDWARE LOCATIONS
The MBS will provide EVA hardware at locations as defined in Figures A3.7–1, A3.7–2 andA3.7–3.
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
A3 – 5
FIGURE A3.2–1 DELETED
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
A3 – 6
Reference Astro Drawing S606955 Sheet 2 of 10
FIGURE A3.2–2 MBS TO MT MECHANICAL INTERFACE
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
A3 – 7
Reference Astro Drawing S606955 Sheet 3 of 10
FIGURE A3.2–3 MBS TO MT MECHANICAL INTERFACE
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
A3 – 8
Reference Astro Drawing S606955 Sheet 4 of 10
FIGURE A3.2–4 MBS TO MT MECHANICAL INTERFACE
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
A3 – 9
Reference Astro Drawing S606955 Sheet 5 of 10
FIGURE A3.2–5 MBS TO MT MECHANICAL INTERFACE
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
A3 – 10
Reference Astro Drawing S606955 Sheet 6 of 10
FIGURE A3.2–6 MBS TO MT MECHANICAL INTERFACE
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
A3 – 11
Reference Astro Drawing S606955 Sheet 7 of 10
FIGURE A3.2–7 MBS TO MT MECHANICAL INTERFACE
SSMB to MSS ICDSSP 42003, Part 2
May 22, 1997
A3 – 12
(Reference SPAR Drawing 51800–0011, Sheet 1 of 5)
FIGURE A3.2–8 MBS TO MT MECHANICAL INTERFACE
SSMB to MSS ICDSSP 42003, Part 2
May 22, 1997
A3 – 13
(Reference SPAR Drawing 51800–0011, Sheet 2 of 5)
FIGURE A3.2–9 MBS TO MT MECHANICAL INTERFACE
SSMB to MSS ICDSSP 42003, Part 2
May 22, 1997
A3 – 14
(Reference SPAR Drawing 51800–0011, Sheet 3 of 5)
FIGURE A3.2–10 MBS TO MT MECHANICAL INTERFACE
SSMB to MSS ICDSSP 42003, Part 2
May 22, 1997
A3 – 15
(Reference SPAR Drawing 51800–0011, Sheet 4 of 5)
FIGURE A3.2–11 MBS TO MT MECHANICAL INTERFACE
SSMB to MSS ICDSSP 42003, Part 2
May 22, 1997
A3 – 16
(Reference SPAR Drawing 51800–0011, Sheet 5 of 5)
FIGURE A3.2.1–1 MBS/MT INTERFACE HARNESS DESIGN
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
A3 – 17
FIGURE A3.4–1 MT/MBS POWER, RETURN AND GROUNDING DIAGRAM
SS
P 42003, P
art 2, Revision A
SS
MB
to MS
S IC
DM
ay 22, 1997
A3 – 18
RPDASSBA
SSBA
RPDA
4) For MBS/MT connector details refer to Figure A3.2.1–1
Figure A3.2.1–1.
SS Buffer AmplifierBus CouplerBus TerminatiotionRemote Power Distribution Assembly
Notes:1) The Transient Voltage Limits & Time Duration are as defined in SSP 30482.2) Table reflects the design to peak power requirement and the associated minimum voltage at the interface plane.3) Connector specifications are per SSQ 21635.4) Rated output current capability of MBS CRPCM providing power to EVA outlet.
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
A3 – 23
TABLE A3.4.2–2 MBS EVA OUTLET #2 CONNECTOR AND PIN ASSIGNMENTS
ÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁ
ÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁ
CONNECTOR ID (3)ÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁ
Notes:1) The Transient Voltage Limits & Time Duration are as defined in SSP 30482.2) Table reflects the design to peak power requirement and the associated minimum voltage at the interface plane.3) Connector specifications are per SSQ 21635.4) Rated output current capability of MBS CRPCM providing power to EVA outlet.
SSMB to MSS ICDSSP 42003, Part 2
May 22, 1997
A3 – 24
(Reference SPAR Drawing 51800–0001, Sheet 1 of 3)
FIGURE A3.7–1 LOCATION OF EVA HARDWARE ON MBS
SSMB to MSS ICDSSP 42003, Part 2
May 22, 1997
A3 – 25
(Reference SPAR Drawing 51800–0001, Sheet 2 of 2)
FIGURE A3.7–2 LOCATION OF EVA HARDWARE ON MBS
SSMB to MSS ICDSSP 42003, Part 2
May 22, 1997
A3 – 26
(Reference SPAR Drawing 51800–0001, Sheet 3 of 3)
FIGURE A3.7–3 LOCATION OF EVA HARDWARE ON MBS
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
B3 – 1
SECTION B3 RESERVED
B3 RESERVED
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
C3 – 1
SECTION C3 AVU TO USL INTERFACE
C3.0 INTERFACE DEFINITION
C3.1 GENERAL
C3.1.1 INTERFACE DESCRIPTION
The Artificial Vision Unit (AVU) to U.S. Laboratory mated on–orbit configuration is shown inFigure C3.1.1–1. The structural and mechanical interface is at the plane between the twointerfacing units as documented herein. Utility interface planes exist at the connectors betweenthe AVU and the USL rack harness.
C3.1.2 INTERFACE RESPONSIBILITIES
CSA is responsible for procurement of the AVU for delivery to NASA as Government FurnishedEquipment (GFE). PG–3 is responsible for develoment of the U.S. Laboratory (U.S. Lab).Interface responsibilities for the AVU to U.S. Lab interface are as defined in SSP 42003 Part I,Section C and as described in SSP 42003 Part II, Section C herein.
C3.1.3 ENGINEERING UNITS AND TOLERANCES
Unless otherwise noted herein, all dimensions in this document are shown in the English systemof inch pound (IP) units. Implied tolerances on linear dimensions are defined in Table C3.1.3–1.
C3.2 STRUCTURAL/MECHANICAL INTERFACES
C3.2.1 GENERAL
AVU structurally attaches to the USL rack via a coldplate attachment system. The AVU tocoldplate fastener pattern will be as shown in Figures C3.2.1–1 and C3.2.1–2.
C3.2.2 UTILITY INTERFACE(S)
The assigned Electrical Reference Designations for AVU connectors are shown in FigureC3.2.1–1, prefaced by the letter ”J”. The assigned reference designations for USL rack harnessconnectors are prefaced by the letter ”P”.
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
C3 – 2
C3.3 FLUID INTERFACE(S)
N/A
C3.4 ELECTRICAL INTERFACE(S)
C3.4.1 ELECTRICAL CONNECTIVITY
The electrical interface(s) (Including Power, Data, & Video interfaces) between the AVU andU.S. Lab consists of a series of electrical connectors with associated cabling. The power, data,and video system interfaces are reflected in Figures C3.4.1–1 and C3.4.1–2.
C3.4.1.1 DETAILED ELECTRICAL INTERFACE(S)
Control of the detailed electrical interface between the AVU and the USL rack harness consistsof identifying the particular jack/plug pair, configuration, location, part number andfunctionality. Table C3.4.1.1–1 thru C3.4.1.1–4 define these controlling parameters for thepower, data, cursor control device, and video respectively. For Tables C3.4.1.1–1 throughC3.4.1.1–4, the following definitions apply:
Not Used – Pin location not used (by ORU or wire harness).Reserved – Pin used by ORU only.Spare – Pin used by wire harness only.
C3.4.2 ELECTRICAL BONDING
The electrical bonding interface for the AVU is a Class R bond through the USL coldplate thatcomplies with the requirements of SSP 30245. The AVU bonding is accomplished via sixteenthreaded fasteners that compress the AVU Electroless Nickel mounting surface against the USLcoldplate Stainless steel (CRES 347) mounting surface as defined in Figures C3.2.1–1 andC3.2.1–2.
C3.4.3 SOFTWARE INTERFACES
The AVU software interfaces to the Robotic Workstation (RWS) are as specified inCSA–SS–ID–0002.
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
C3–4
TABLE C3.1.3–1 LINEAR TOLERANCES
English Dimensions Implied Tolerances (inches)
x.xx +/– 0.030
x.xxx +/– 0.010
SS
P 42003, P
art 2S
SM
B to M
SS
ICD
May 22, 1997
C3–5
DIMENSIONING & TOLERANCINGPER ANSI Y 14.5 M–1982
UNLESS OTHERWISE SPECIFIEDDIMENSIONS ARE IN INCHESTOLERANCES: ANGLES + 1DECIMALS .XX +.03DECIMALS .XXX +.010RIVET & BOLT EDGE MARGIN +.05BEND RADII +.01 ON .03 & .06+.03 ON .09 & GREATERSHEET METAL CORNER RADIIINTL .26 EXT .25 .22 .00DIMENSIONS AND SURFACE TEXTUREDESIGNATIONS APPLY BEFOREPLATING OR FINISH COATINGUNLESS OTHERWISE NOTED
ELECTROLESS NICKEL PLATE PER MIL–C–26074, CLASS 4, GRADE A
DENOTES ESTIMATED CENTRE OF GRAVITY
HARD DISK DRIVE SHOWN FOR REFERENCE ONLY: NOT INSTALLED FORLAUNCH CONFIGURATION: NOT INCLUDED FOR C OF G ESTIMATE.
ORU MOUNTING FASTENERS WILL BE TORQUED TO 25–30 IN. LBS.
NOTES:
CONNECTOR J5 NOT USED FOR ISS APPLICATION.
5.6
7 MASTER CONNECTOR KEYWAY LOCATION
ALL CORNERS AND EDGES RADIUS OR CHAMFER TO .03 MIN.
75 PLACES
8 CONNECTORS ARE LOCATED ON ”FRONT” OF AVU
FIGURE C3.2.1–1 INTERFACE CONTROL DRAWING OF AVU (NOT TO SCALE)
SS
P 42003, P
art 2S
SM
B to M
SS
ICD
May 22, 1997
C3–6
FIGURE C3.2.1–2 INTERFACE CONTROL DRAWING OF AVU (NOT TO SCALE)
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
C3–7
Data Normal Hi (T Ball 1+)
Primary
AVU
RPCMType V3.5 A
AVU2 Power 16ga
AVU2 Return 16ga
MSS–PDGF LB A HI 22ga
MSS–PDGF LB A LO 22ga
Video O/P #2 Plus
CSA provided
connectors
NASA provided
connectors
J1
J2
J3
J4
W1186P2
W1181P3
W1187P2
J5
Video O/P #2 Minus
Video O/P #1 PlusVideo O/P #1 Minus
Video I/P #2 PlusVideo I/P #2 Minus
Video I/P #1 PlusVideo I/P #1 Minus
Sync I/P PlusSync I/P Minus
CEU Video O/P #1 PlusCEU Video O/P #1 Minus
CEU Video O/P #2 PlusCEU Video O/P #2 Minus
ControlElectronics
Unit(CEU)
CVIU
CVIU
Data Normal Lo (T Ball 1–)
D&CPanel*
A
B
C
D
E
910
11
12
15
17
21
22
MSS–PDGF LB B HI 22ga
MSS–PDGF LB B LO 22ga
8
RT address 2nd MSB
RT address MSB
RT address 3rd MSB
RT address 4th MSB
RT address LSB
Parity Bit
W1182P3
1
2
34
5
67
3736
3433
2726
2423
3029
32
65
5
6
11
12
13
16
14
15
AVU Location Address(dec)
Address(binary)
Parity
Primary LAS 5 11 01011 0
Links
1&2,5&6,11&12
RT Address Selection
Spare (T Ball 2+)
18
17
Interface between DCP wire harness andAVU CCD defined in Section G.
Spare (T Ball 2–)
Spare (T Ball 3+)
Spare (T Ball 3–)
Spare (T Ball 4+)
Spare (T Ball 4–)
Spare (T Ball 5+)
Spare (T Ball 5–)
Rack InterfacePanel*
Note: * Rack Interface Panel and DCP informationis included for reference only
FIGURE C3.4.1–1 PRIMARY AVU ELECTRICAL SYSTEM DIAGRAM
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
C3–8
Secondary
AVU
RPCMType V3.5 A
AVU1 Power 16ga
AVU1 Return 16ga
MSS–PDGF LB A HI 22ga
MSS–PDGF LB A LO 22ga
Video O/P #2 Plus
CSA provided
connectors
NASA provided
connectors
Video O/P #2 Minus
Video O/P #1 PlusVideo O/P #1 Minus
Video I/P #2 PlusVideo I/P #2 Minus
Video I/P #1 PlusVideo I/P #1 Minus
Sync I/P PlusSync I/P Minus
CEU Video O/P #1 PlusCEU Video O/P #1 Minus
CEU Video O/P #2 PlusCEU Video O/P #2 Minus
ControlElectronics
Unit(CEU)
CVIU
CVIU
A
B
C
D
E
910
11
12
15
17
21
22
MSS–PDGF LB B HI 22ga
MSS–PDGF LB B LO 22ga
8
RT address 2nd MSB
RT address MSB
RT address 3rd MSB
RT address 4th MSB
RT address LSB
Parity Bit
1
2
34
5
67
3736
3433
2726
2423
3029
32
65
AVU Location Address(dec)
Address(binary)
Parity
Secondary LAP 5 8 01000 0
Links
1&2,5&6,7&8,9&10, 11&12
RT Address Selection
J1
J2
J4
W1281P3
W1287P2
J5
W1282P3
J3
W1286P2
5
6
11
12
13
16
14
15
18
17
Interface between DCP wire harness and AVU CCDdefined in SectionG
Data Normal Hi (T Ball 1+)
Data Normal Lo (T Ball 1–)
D&CPanel*
Spare (T Ball 2+)
Spare (T Ball 2–)
Spare (T Ball 3+)
Spare (T Ball 3–)
Spare (T Ball 4+)
Spare (T Ball 4–)
Spare (T Ball 5+)
Spare (T Ball 5–)
Rack InterfacePanel*
Note: * Rack Interface Panel and DCP informationis included for reference only
FIGURE C3.4.1–2 SECONDARY AVU ELECTRICAL SYSTEM DIAGRAM
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C3–9
TABLE C3.4.1.1–1 DETAILED ELECTRICAL DESCRIPTION OF AVU CONNECTOR J1(POWER)
CSANASA
AVUInterface Plane
J1P3
AVU
CONNECTOR
Insert ArrangementInsert 15–5 Per SSQ 21635
A
B
CD
E
+X–X
+Y
–Y
CONNECTOR LOCATION
CONNECTOR ID AVU (POWER)Ref. Des J1 Part Number D38999/20FD5PN Wire Harness Number NA
Ref. Des P3 Part Number NATC06G15N5SN Wire Harness Number LAS5–W1181
LAP5–W1281
PIN FUNCTION TABLECont
ID
Signal
Function
Maximum
Pwr [W]
EMC
Class
AWG RPCM GND
Loc’n
Sig
Source
Notes
A Not used
B AVU1 Power 175 EO 16 3.5 amp MSS
rack
Twisted with AVU 1
Return
C AVU1 Return 175 EO 16 3.5 amp MSS
rack
Twisted with AVU 1
Power
D Reserved For Orbiter
application
E Reserved For Orbiter application
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
C3–10
TABLE C3.4.1.1–2 DETAILED ELECTRICAL DESCRIPTION OF AVU CONNECTOR J2(DATA)
114
1521
22–X +X
–Y
+Y
CSANASA
AVUInterface Plane
J2P3
AVU
CONNECTOR
Insert ArrangementInsert 13–35 Per SSQ 21635
*Note: For 1553B address and parity lines:Closed loop equivalent to logic ’0’Open loop equivalent to logic ’1’
CONNECTOR LOCATION
CONNECTOR ID – AVU (1553)Ref. Des J2 Part Number D38999/20FC35PA Wire Harness
NumberNA
Ref. Des P3 Part Number NATC06G13N35SA Wire HarnessNumber
LAS5–W1182
LAP5–W1282
PIN FUNCTION TABLEContID
Signal Function EMCClass
AWG SignalSource
SignalDestination
Notes
1 RT ADDRESS MSB N/A 22 AVU AVU Address*
2 GROUND FOR MSB N/A 22 AVU AVU Address*
3 RT ADDRESS 2ND MSB N/A 22 AVU AVU Address*
4 GROUND FOR 2ND MSB N/A 22 AVU AVU Address*
5 RT ADDRESS 3RD MSB N/A 22 AVU AVU Address*
6 GROUND FOR 3RD MSB N/A 22 AVU AVU Address*
7 RT ADDRESS 4TH MSB N/A 22 AVU AVU Address*
8 GROUND FOR 4TH MSB N/A 22 AVU AVU Address*
9 RT ADDRESS LSB N/A 22 AVU AVU Address*
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
C3–11
TABLE C3.4.1.1–2 DETAILED ELECTRICAL DESCRIPTION OF AVU CONNECTOR J2(DATA) (CONTINUED)
10 GROUND FOR LSB N/A 22 AVU AVU Address*
11 PARITY BIT N/A 22 AVU AVU Address*
12 GROUND FOR PARITY
BIT
N/A 22 AVU AVU Address*
13 NOT USED
14 NOT USED N/A N/A
15 MSS PDGF LB B LO RF 22 N/A N/A 1553B per SSQ 21655
16 NOT USED
17 MSS PDGF LB A LO RF 22 N/A N/A 1553B per SSQ 21655
18 NOT USED
19 NOT USED
20 NOT USED
21 MSS PDGF LB B HI RF 22 N/A N/A 1553B per SSQ 21655
22 MSS PDGF LB A HI RF 22 N/A N/A 1553B per SSQ 21655
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
C3–12
TABLE C3.4.1.1–3 DETAILED ELECTRICAL DESCRIPTION OF AVU CONNECTOR J3(CURSOR CONTROL DEVICE)
CSANASA
AVUInterface Plane
J3P2
AVU
CONNECTOR
Insert ArrangementInsert 13–35 Per
SSQ 21635
1
15
22
21
14
+Y
+X
–Y
–X
CONNECTOR LOCATION
CONNECTOR ID – AVU (CURSOR CONTROL DEVICE)
Ref. Des J3 Part Number D38999/20FC35PN Wire HarnessNumber
NA
Ref. Des P2 Part Number NATC06G13N35SN Wire HarnessNumber
LAS5–W1186
LAP5–W1286
PIN FUNCTION TABLEContID
Signal Function EMCClass
AWG SignalDestination
SignalSource
Notes
1 RESERVED For Orbiter Application
2 RESERVED For Orbiter Application
3 RESERVED For Orbiter Application
4 RESERVED For Orbiter Application
5 Data Normal Hi RF 22 AVU AVU CCD T Ball 1+
6 Data Normal Lo RF 22 AVU AVU CCD T Ball 1–
7 RESERVED For Orbiter Application
8 RESERVED For Orbiter Application
9 RESERVED For Orbiter Application
10 NOT USED
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
C3–13
TABLE C3.4.1.1–3 DETAILED ELECTRICAL DESCRIPTION OF AVU CONNECTOR J3(CURSOR CONTROL DEVICE)(CONTINUED)
11 SPARE HO 22 AVU AVU CCD T BALL 2+
12 SPARE HO 22 AVU AVU CCD T BALL 2–
13 SPARE HO 22 AVU AVU CCD T BALL 3+
14 SPARE HO 22 AVU AVU CCD T BALL 3–
15 SPARE HO 22 AVU AVU CCD T BALL 4+
16 SPARE HO 22 AVU AVU CCD T BALL 4–
17 SPARE HO 22 AVU AVU CCD T BALL 5+
18 SPARE HO 22 AVU AVU CCD T BALL 5–
19 RESERVED FOR ORBITER AP-PLICATION
20 RESERVED FOR ORBITER AP-PLICATION
21 RESERVED FOR ORBITER AP-PLICATION
22 RESERVED FOR ORBITER AP-PLICATION
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
C3–14
TABLE C3.4.1.1–4 DETAILED ELECTRICAL DESCRIPTION OF AVU CONNECTOR J4(VIDEO)
CSANASA
AVUInterface Plane
J4P2
AVU
CONNECTOR
Insert ArrangementInsert 15–35 Per
SSQ 21635
1
2131
+Y
+X
–Y
–X
CONNECTOR LOCATION
CONNECTOR ID – AVU (VIDEO)Ref. Des J4 Part Number D38999/20FD35PA Wire Harness Number N/A
Ref. Des P2 Part Number NATC06G15N35SA Wire Harness Number LAS5–W1187
LAP5–W1287
PIN FUNCTION TABLEContID
Signal Function EMCClass
AWG SignalSource
SignalDestination
Notes
1 NOT USED
2 CEU Video O/P #1 Minus RF 22 AVU CEU TSP 1
3 CEU Video O/P #1 Plus RF 22 AVU CEU TSP 1
4 NOT USED
5 CEU Video O/P #2 Minus RF 22 AVU CEU TSP 2
6 CEU Video O/P #2 Plus RF 22 AVU CEU TSP 2
7 Not used
8 Not used
9 Not used
10 Not used
11 Not used
12 Not used
13 Not Used
14 Not Used
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
C3–15
TABLE C3.4.1.1–4 DETAILED ELECTRICAL DESCRIPTION OF AVU CONNECTOR J4(VIDEO) (CONTINUED)
15 Not Used
16 Not Used
17 Not Used
18 Not Used
19 Not Used
20 Not Used
21 Not Used
22 Not used
23 Video O/P #2 Minus RF 22 AVU CVIU TSP 3
24 Video O/P #2 Plus RF 22 AVU CVIU TSP 3
25 Not used
26 Video O/P #1 Minus RF 22 AVU CVIU TSP 4
27 Video O/P #1 Plus RF 22 AVU CVIU TSP 4
28 Not used
29 Sync I/P Minus RF 22 CVIU AVU TSP 5
30 Sync I/P Plus RF 22 CVIU AVU TSP 5
31 Not used
32 Not used
33 Video I/P #2 Minus RF 22 CVIU AVU TSP 6
34 Video I/P #2 Plus RF 22 CVIU AVU TSP 6
35 Not used
36 Video I/P #1 Minus RF 22 CVIU AVU TSP 7
37 Video I/P #1 Plus RF 22 CVIU AVU TSP 7
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
D3 – 1
SECTION D3 SSMB TO PDGF INTERFACE
D3 INTERFACE DEFINITION
D3.1 GENERAL
D3.1.1 INTERFACE DESCRIPTION
The physical interface (mechanical, structural, thermal and environmental) plane is defined atthe Power Data Grapple Fixture (PDGF) Mounting Ring mounting surface at the Modules. Theutility interface plane (power, data and video) is defined between the PDGF harness and theModule connector panel. A Video Signal Converter (VSC) is required to convert the PFM fiberoptic video from the SSMB to PFM electrical video that is compatible with the PDGF andSpace Station Remote Manipulator System (SSRMS). The interfaces between the VSC and themodules are as defined in SSP 42003, Section H.
D3.1.2 INTERFACE RESPONSIBILITIES
CSA is responsible for development of the PDGF. NASA is responsible for procurement of thePDGF and PDGF harness for the United States Laboratory (USL) and Hab. NASA isresponsible for development of the USL and Hab. National Space Development Agency ofJapan (NASDA) is responsible for development of the Japanese Experiment Module –Pressurized Module (JEM–PM) and procurement of the PDGF and PDGF harness for theJEM–PM.
D3.1.3 ENGINEERING UNITS AND TOLERANCES
Unless otherwise noted herein, all dimensions in this document are shown in the English systemof inch pound (IP) units.
D3.2 STRUCTURAL/MECHANICAL INTERFACES
The PDGF structurally attaches to the modules via a PDGF mounting ring. The PDGF mountingring attaches to the Modules via eight fasteners. The bolt hole pattern and related mechanicalinstallation details are defined in SSP 42004 Part 2, Figures A3.2–1 through A3.2–3.
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
D3 – 2
D3.2.1 USL MODULE PDGF LOCATION
A PDGF will be mounted on the USL Module at the location defined in Figure D3.2.1–1. ThePDGF connector panel location on the USL will be as shown in Figure D3.2.1–1.
D3.2.2 HAB MODULE PDGF LOCATION
A PDGF will be mounted on the Hab Module at the location defined in Figure D3.2.2–1(TBD#4). The PDGF connector panel location on the Hab will be as shown in Figure D3.2.2–1.
D3.2.3 JEM–PM PDGF LOCATION
A PDGF will be mounted on the JEM–PM at the location defined in SSP 42000, Figure3.8.1.1.1–1. The PDGF connector panel location on the JEM–PM will be as shown in SSP42000, Figure 3.8.2.1.1–1.
D3.2.4 DELETED
D3.3 THERMAL INTERFACES
The PDGF to Modules thermal interface implementation will be as defined in SSP 42004 Part 2,Figures A3.2–1 through A3.2–3.
D3.4 ELECTRICAL INTERFACES
The Modules will provide power, data and PFM video interfaces to the SSRMS via the PDGF asdefined in Figures D3.4–1 through D3.4–6. The SSRMS Backup Drive power and datainterfaces are provided by USL and Hab modules only.
D3.4.1 POWER RETURN AND GROUNDING INTERFACES
The Modules will provide power return and grounding interfaces to the SSRMS via the PDGF asdefined in Figures D3.4–1 through D3.4–6.
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
D3 – 3
The Module PDGF external wiring diagram is defined in Figure D3.4.1–1.
D3.4.2 DELETED
D3.4.2.1 USL POWER CONNECTORS AND PIN ASSIGNMENTS
The PDGF harness power connectors and pin assignments for the USL module will be as definedin Tables D3.4.2.1–1 through D3.4.2.1–3.
D3.4.2.2 HAB POWER CONNECTORS AND PIN ASSIGNMENTS
The PDGF harness power connectors and pin assignments for the Hab module will be as definedin Tables D3.4.2.2–1 through D3.4.2.2–3.
D3.4.2.3 JEM–PM POWER CONNECTORS AND PIN ASSIGNMENTS
The PDGF harness power connectors and pin assignments for the JEM–PM will be as defined inTables D3.4.2.3–1 through D3.4.2.3–2.
D3.4.2.4 DELETED
D3.4.3 DATA AND PFM SYNC AND CONTROL AND VIDEO INTERFACES
The USL, Hab, and JEM–PM will support data, PFM sync and control and video interfacesbetween the SSMB and the SSRMS via the PDGF. PFM sync and control and video will betransmitted and received by copper lines between the VSC and the SSRMS. The PFM FiberOptic video from the Modules will be converted to copper for the PDGF by the VSC.
D3.4.4 DATA AND VIDEO CONNECTORS AND PIN ASSIGNMENTS
D3.4.4.1 USL DATA AND VIDEO CONNECTORS AND PIN ASSIGNMENTS
The PDGF harness data and video connectors and pin assignments for the USL module will beas defined in Tables D3.4.4.1–1 through D3.4.4.1–5.
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
D3 – 4
D3.4.4.2 HAB DATA AND VIDEO CONNECTORS AND PIN ASSIGNMENTS
The PDGF harness data and video connectors and pin assignments for the Hab module will be asdefined in Tables D3.4.4.2–1 through D3.4.4.2–3.
D3.4.4.3 JEM–PM DATA AND VIDEO CONNECTORS AND PIN ASSIGNMENTS
The PDGF harness data and video connectors and pin assignments for the JEM–PM will be asdefined in Tables D3.4.4.3–1 through D3.4.4.3–3.
D3.4.4.4 DELETED
D3.5 ENVIRONMENTS
The PDGF to Modules electromagnetic, grounding and bonding interface implementation will beas defined in SSP 42004, Part 2, Figures A3.2–1 through A3.2–3.
D3.6 SOFTWARE INTERFACES
There are no software interfaces between the PDGF and the Modules.
D3.7 SSRMS EVA HARDWARE LOCATIONS
The SSRMS will provide EVA hardware locations as defined in Figure D3.7–1.
SS
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D3 – 5
PDGF and ConnectorPanel Location
PDGF DATA
Radius = 90.6”Angle = 52.5o
12.00”36.20”
56.20”
USL Cof FWD MID Ring
Keel Pin
Forward
Nadir
Nadir
Starboard
FIGURE D3.2.1–1 PDGF LOCATION ON USL
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
D3 – 6
(TBD#8)
FIGURE D3.2.2–1 PDGF LOCATION ON US HAB
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
D3 – 7
FIGURE D3.2.4–1 DELETED
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
D3 – 8
MSS PDGF LB A INMSS PDGF LB A OUT
VIDEO PDGF – 1
VIDEO PDGF – 3
SYNC PDGF – 1
ÃÃÃÃ
J304
PDGF LOWERCONNECTOR PANEL
S0 / LAB / LDACONNECTOR PANEL
ÃÃ
J300
ÃÃÃ
ÃÃÃ
J302
ÃÃÃ
ÃÃÃ
J303
ÃÃÃ
ÃÃÃ
J301
PG–3
P111
P109
P110
P108
P454
P450
P453
P451
W9151
W9152
W9251
W9252
PG–1 CSAFWD PORTDEBRIS SHIELD
VIDEO PDGF – 2
SSRMS 1 Power & Return
(RIGID UMBILICAL)
MSS PDGF LB B OUT
NOTE: The Launch Deployment Assembly (LDA) is installed onthe Lab Cradle Assembly (LCA).
ÃÃÃJ407
ÃÃÃÃ
J404
ÃÃÃ
J400
ÃÃÃJ402
ÃÃÃ
ÃÃÃ
J403
ÃÃÃÃ
J401
ÃÃÃJ406
ÃÃÃÃ
J111
ÃÃÃÃ
J109
ÃÃÃÃ
J110
ÃÃÃÃ
J108
Ground
Ground
SYNC PDGF – 2
MSS PDGF LB B IN
P300
P301
P303
P304
vscORU
J1 J4
J1
J2
J3
J4
FSEGF
2
1
2
1
*Payload 1 Pwr and Rtn
P400
P401
P402
P403
P404
P407
P406
SSRMS 2 Power & Return
1 TSP
*1 TSP
1 Fiber
1 Fiber
1 Fiber
1 Fiber
1 Fiber
1 TSP
*1 TSP
*Payload 2 Pwr and Rtn
*SSRMS BUD Pwr and Rtn
*Ground
*2 TSP *3 TSP
6A1 – The FSEGFpower, data, and video utilities are routed from
the PG1 Rigid Umbilical via the Lab Fwd Port Debris Shield
LAB
LEGEND
* Unused in this configuration
J405J305*1 Fiber
*1 TSP MSS BUD LB A
Bus Coupler
& Terminator
Bus Coupler
& Terminator
*1 TSPMSS BUD LB B
Interface Plane
P1 P4
J2 J3
P2 P3
RPCM25A
Type VI
RPCM25A
Type VI
FIGURE D3.4–1 LAB EXTERNAL HARNESSES AND INTERFACES (FLIGHT 6A 1)
SSP 42003, Part 2, Revision A SSMB to MSS I CMay 22, 1997
D3 – 9
J304
PDGF LOWERCONNECTOR PANEL
S0 / LAB / LDACONNECTOR PANEL
J300
J302
J303
J301
PG–3
P109
P110
P450
P453
P451
W9151
W9152
W9251
PG–1FWD PORTDEBRIS SHIELD
(RIGID UMBILICAL)
NOTE: 6A2 – The SSRMS has walked on to the Lab PDGF. Removed & Stowed
LEGEND
ÃÃÃ
ÃÃÃ
J400
ÃÃÃJ407
ÃÃÃ
ÃÃÃ
J402
ÃÃÃJ403
ÃÃÃJ401
ÃÃÃJ406
ÃÃÃÃ
J109
ÃÃJ110
P1
P9
P11
P3
LAB
SSRMS 1 Power & Return
Ground
Ground
SSRMS 2 Power & Return
P108ÃÃJ108
2
1
2
1
P402
MSS PDGF LB A IN
MSS PDGF LB A OUT
VIDEO PDGF – 1
VIDEO PDGF – 3
SYNC PDGF – 1
1 TSP
1 Fiber
1 Fiber
*1 Fiber
P111 P454W9252
VIDEO PDGF – 2
MSS PDGF LB B OUT
ÃÃÃ
ÃÃÃ
J404ÃÃÃÃ
J111
SYNC PDGF – 2
MSS PDGF LB B IN
P71 Fiber
1 Fiber
1 TSP
1 TSP
P403
P404
*3 Fiber
*2 TSP
*2 Fiber
*2 TSP
*2 TSP *3 TSP
P407
P406
P400
P401
The Lab PDGF power, data, and video utilities are routed fromthe PG1 Rigid Umbilical.
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
E3 – 1
SECTION E3 PWP TO MBS INTERFACE
E3 INTERFACE DEFINITION
E3.1 GENERAL
E3.1.1 INTERFACE DESCRIPTION
The physical interface (mechanical, structural, thermal and environmental) plane is definedbetween the Worksite Interface Fixture (WIF) on the MBS and the EVA Portable Workplatform(PWP) probe.
There is no electrical interface between the EVA PWP and the MBS.
E3.1.2 INTERFACE RESPONSIBILITIES
The MBS WIF is supplied to CSA as GFE. NASA is responsible for development of the EVAPWP. Interface responsibilities for the EVA PWP to MBS WIF interface are as defined in SSP42003 Part 1, Section E and as described in SSP 42003 Part 2, Section E herein.
E3.1.3 ENGINEERING UNITS AND TOLERANCES
Unless otherwise noted herein, all dimensions are shown in the English system of inch pound(IP) units.
E3.2 STRUCTURAL/MECHANICAL INTERFACES
The EVA PWP probe attaches to the MBS WIF. Refer to Figure A3.7–1, A3.7–2, and A3.7–3for WIF locations on the MBS.
For structural and mechanical details of the WIF, refer to SSP 30256:001.
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
E3 – 2
E3.2.1 INTERFACE LOCATIONS
The location of the WIF on the MBS will be as defined in Figure A3.7–1, A3.7–2, and A3.7–3.
The physical orientation of the PWP in the WIF on the MBS will be as defined in FigureE3.2.1–1.
E3.3 SOFTWARE INTERFACES
There are no software interfaces between the EVA PWP and the MBS .
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
E3 – 3
FIGURE E3.2.1–1 PORTABLE WORK PLATFORM (PWP) STOWED ON MBS
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
F3 – 1
SECTION F3 SSMB LSA TO SSRMS INTERFACE
F3 INTERFACE DEFINITION
F3.1 GENERAL
F3.1.1 INTERFACE DESCRIPTION
The physical interface (mechanical, structural, thermal and environmental) plane is defined atthe Flight Support Equipment Grapple Fixture (FSEGF) and FSE brackets mounting surface atthe SSMB Launch Support Assembly (LSA). The utility interface plane (power, data and video)is defined between the FSEGF harness and the USL connector panel.
F3.1.2 INTERFACE RESPONSIBILITIES
CSA is responsible for development of the SSRMS, FSEGF, FSE brackets and FSEGF Harness.NASA is responsible for development of the SSMB LSA.
F3.1.3 ENGINEERING UNITS AND TOLERANCES
Unless otherwise noted herein, all dimensions are shown in the English system of IP units.
F3.2 STRUCTURAL/MECHANICAL INTERFACES
The FSEGF attaches to the SSMB LSA via eight fasteners.
The detailed mechanical interface between the SSMB LSA and the SSRMS via the FSEGF andFSE brackets is defined in Figures F3.2–1 and F3.2–2.
F3.2.1 FSEGF AND FSE BRACKET LOCATION
Two FSEGFs and four FSE brackets will be mounted on the SSMB LSA at the locations definedin Figures F3.2–1 and F3.2–2.
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
F3 – 2
F3.3 THERMAL INTERFACES
Reserved
F3.4 ELECTRICAL INTERFACES
The USL will provide power, data and PFM video interfaces to the SSRMS via the FSEGFharness as defined in Figures F3.4–1 and F3.4–2.
F3.4.1 POWER RETURN AND GROUNDING INTERFACES
The USL will provide power return and grounding interfaces to the SSRMS via the FSEGFharness as defined in Figures F3.4–1.
F3.4.2 POWER CONNECTORS AND PIN ASSIGNMENTS
The FSEGF harness power connectors and pin assignments for the SSMB connector panel willbe as defined in Tables F3.4.2–1 through F3.4.2–2.
F3.4.3 DATA AND PFM SYNC AND CONTROL AND VIDEO INTERFACES
The USL will support data and video interfaces between the SSMB and the SSRMS via theFSEGF harness. PFM sync and control and video will be transmitted and received by copperlines between the FSEGF and the SSRMS. The PFM Fiber Optic video from the SSMB will beconverted to copper for the FSEGF by the VSC located within the FSEGF.
F3.4.4 DATA AND VIDEO CONNECTORS AND PIN ASSIGNMENTS
The FSEGF harness data and video connectors and pin assignments for the SSMB connectorpanel will be as defined in Tables F3.4.4–1 and F3.4.4–2.
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
F3 – 3
F3.5 ENVIRONMENTS
The FSEGF to SSMB LSA electromagnetic, grounding and bonding interface implementationwill be as defined in Figures F3.2–1 and F3.2–2.
F3.6 SOFTWARE INTERFACES
There are no software interfaces between the FSEGF and the USL.
SSMB to MSS ICDSSP 42003, Part 2, Revision A
May 22, 1997
F3 – 4
(Reference SPAR Drawing 51612–0037, Sheet 1 of 2)
FIGURE F3.2–1 FSEGF TO SSMB LSA BOLT PATTERN
SSMB to MSS ICDSSP 42003, Part 2, Revision A
May 22, 1997
F3 – 5
(Reference SPAR Drawing 51612–0037, Sheet 2 of 2)
FIGURE F3.2–2 FSEGF TO SSMB LSA BOLT PATTERN
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
F3 – 6
FIGURE F3.2–4 DELETED
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
F3 – 7
FIGURE F3.2–5 DELETED
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
F3 – 8
FIGURE F3.2–6 DELETED
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
F3 – 9
FIGURE F3.2–7 DELETED
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
F3 – 10
FIGURE F3.2–8 DELETED
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
F3 – 11
FIGURE F3.2–9 DELETED
SS
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F3 – 12
P233To VSC (J2)20ga
12ga
12ga
12ga
12ga
12ga
2
2
2
2
1
2
2
1
8ga
8ga
8ga
2
2
1
8ga
8ga
8ga
SSRMS 1Pwr & Rtn
*Pyld 1 Pwr & Rtn
Ground
S0/Lab/LDAConnector Panel
InterfacePlane
FSEGFHarness &Connectors
LabHarness &Connectors J300 P300
J3
20gaP233To VSC (J2)
P344To VSC (J3)20ga
12ga
12ga
12ga
12ga
12ga
2
2
2
2
1
2
2
1
8ga
8ga
8ga
2
2
1
8ga
8ga
8ga
SSRMS 2
*Pyld 2 Pwr & Rtn
Ground
J301 P301
20gaP344To VSC (J3)
J4
28ga*SSRMS BUD Pwr & Rtn
8ga*Ground
J302
Note: Return lines not shown
* Unused in this configuration
FSEGF
Pwr & Rtn
RPCM25AType II
RPCM25AType II
FIG
UR
E F
3.4–1 FS
EG
F TO
US
L ELE
CT
RIC
AL S
YS
TE
M D
IAG
RA
M
SS
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F3 – 13
Video Channel #1 CU PFM
Video Channel #2 CU PFM
Sync & Control #1 CU PFM
J4J1
J3J2
VSC
Power Connectors
Video Channel #3 CU PFM
Sync & Control #2 CU PFM
LB MSS–PDGF A In 22ga
22ga*LB MSS–PDGF A Out
Video PDGF #1
Video PDGF #3
Sync PDGF #1
Fo
Fo
Fo
FSEGFHarness &Connectors
InterfacePlane
Video PDGF #2
Sync PDGF #2
LB MSS–PDGF B In
*LB MSS–PDGF B Out
Fo
Fo
22ga
22ga
P303
P304
Fo
Fo
Fo
Fo
Fo
FSEGF
J1
J2
S0/Lab/LDAConnector Panel
J303
LabHarness &Connectors
Tsp
Tsp
J304
Tsp
Tsp
*1 Fo
J305
* Unused in this Configuration
Note: Backup Drive not wired to SSMB
BusCoupler &Terminator
BusCoupler &Terminator
FIG
UR
E F
3.4–2 FS
EG
F TO
US
L ELE
CT
RIC
AL S
YS
TE
M D
IAG
RA
M
SSP 42003, Part 2, Revision A SSMB to MSS ICDMay 22, 1997
F3 – 14
TABLE F3.4.2–1 DETAILED ELECTRICAL DESCRIPTION OF FSEGF TO USLCONNECTOR J300 (PRIME POWER)
FOÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁNote: MIL–STD–1553 wire is 22 AWG
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TABLE F3.4.4–3 DELETED
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SECTION G3 AVU CCD TO RWS INTERFACE
G3.0 INTERFACE DEFINITION
G3.1 GENERAL
G3.1.1 INTERFACE DESCRIPTION
The Artificial Vision Unit (AVU) Cursor Control Device (CCD) to Robotic Workstation (RWS)mated on–orbit configuration for both primary (LAS 5) and secondary (LAP 5) configurationsare shown in Figure G3.1.1–1. The structural and mechanical interface plane is at the mountingsurface between the AVU CCD and the RWS bracket. Utility interface planes exist at theconnectors between the AVU CCD and the RWS harness.
G3.1.2 INTERFACE RESPONSIBILITIES
CSA is responsible for AVU CCD delivery to NASA as Government Furnished Equipment(GFE). NASA is responsible for development of the RWS. Interface responsibilities for theAVU CCD to RWS interface are as defined in SSP 42003 Part I, Section G and as described inSSP 42003 Part II, Section G herein.
G3.1.3 ENGINEERING UNITS AND TOLERANCES
Unless otherwise noted herein, all dimensions in this document are shown in English system ofinch pound (IP) units. Implied tolerances on linear dimensions are defined in Table G3.1.3–1.
TABLE G3.1.3–1 LINEAR TOLERANCES
English Dimensions Implied Tolerances (inches)
x.xx +/– 0.030
x.xxx +/– 0.010
G3.2 STRUCTURAL/MECHANICAL INTERFACES
G3.2.1 GENERAL
AVU CCD structurally attaches to the RWS mounting bracket as shown in Figure G3.2.1–1 andG3.2.1–2.
G3.2.2 ELECTRICAL CONNECTOR LOCATION
AVU CCD electrical connector location and configuration are as defined in Figure G3.2.1–1.
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G3.3 FLUID INTERFACE(S)
N/A
G3.4 ELECTRICAL INTERFACES
G3.4.1 ELECTRICAL CONNECTIVITY
The electrical interface(s) (including power and data interfaces) between the AVU CCD andRWS consists of an electrical connector with associated cabling. The power and data systeminterfaces are reflected in Figure G3.4.1–1.
G3.4.1.1 DETAILED ELECTRICAL INTERFACE(S)
Control of the detailed electrical interface between the AVU CCD and the RWS harness consistsof identifying the particular jack/plug pair, configuration, location, part number andfunctionality. Table G3.4.1.1–1 defines these controlling parameters for the power and data. ForTable G3.4.1.1–1 the following definitions apply:
Not Used – Pin location not used by ORU or wire harnessReserved – Pin used by ORU only.Spare – Pin used by wire harness only.
G3.4.2 ELECTRICAL BONDING
The electrical bonding interface for the AVU CCD is at the dedicated Class H–bond pin (22gauge) of the AVU J1 CCD Connector as identified in Table G3.4.1.1–1 (contact number one).This bonding interface shall comply with the electrical bonding requirements defined in SSP30245.
G3.4.3 SOFTWARE INTERFACES
N/A
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RWS Mounting Bracket
AVU CCD
FIGURE G3.1.1–1 AVU CCD TO RWS ON–ORBIT CONFIGURATION
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1.375” +0.005
2.750” ±0.005
1.375” +0.005
2.750” +0.005
2.81”
2.380”
1.350”
1.640”
3.280”
0.172(4 Holes)
∅
∅
FIGURE G3.2.1–2 AVU CCD BOLT PATTERN AND PANEL CUTOUT
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11
3
9
1
6
12
13
NC
Power +5 VDC
Power Return
Structure
Data Norm Hi (+) (T Ball 1+)
Data Norm Lo (–) (T Ball 1–)
Spare (T–Ball 2+)
Spare (T–Ball 2–)
Spare (T–Ball 3+)
Spare (T–Ball 3–)
Spare (T–Ball 4+)
Spare (T–Ball 4–)
AVU
CCD
J1
11
3
9
1
6
12
13
5
7
2
10
4
8
NC
NC
NC
NC
NC
NC: No Connect
Indicates Twisted Shielded Pair
CCP01W07
Notes:
FIGURE G3.4.1–1 RWS TO AVU CCD ELECTRICAL INTERFACES
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TABLE G3.4.1.1–1 DETAILED ELECTRICAL DESCRIPTION OF AVU CCD CONNECTOR J1(CURSOR CONTROL DEVICE)
CSANASA
AVUInterface Plane
J01P01
AVU
CONNECTOR
Insert ArrangementSeries III Insert 11–35 Per
MIL–C–38999
+Y
+X
–Y
–X
CCD
1
2
3
4
5
67
8
9
10
11
1213
CONNECTOR LOCATION
CONNECTOR ID – AVU (CURSOR CONTROL DEVICE)
Ref. Des J01 Part Number D38999/20FB35PN Wire HarnessNumber
NA
Ref. Des P01 Part Number D38999/26FB35SN Wire HarnessNumber
W07CC
PIN FUNCTION TABLEContID
Signal Function EMCClass
AWG SignalDestination
SignalSource
Notes
1 STRUCTURE ML 22 AVU CCD DCP
2 SPARE HO 22 AVU AVU CCD T Ball 3+
3 POWER +5 VDC ML 22 AVU CCD DCP
4 SPARE HO 22 AVU AVU CCD T Ball 4+
5 SPARE RF 22 AVU AVU CCD T Ball 2+
6 RESERVED Lamp supply
7 SPARE RF 22 AVU AVU CCD T Ball 2–
8 SPARE HO 22 AVU AVU CCD T Ball 4–
9 POWER RETURN ML 22 AVU CCD DCP
10 SPARE HO 22 AVU AVU CCD T Ball 3–
11 NOT USED
12 DATA NORM LO (–) RF 22 AVU AVU CCD T Ball 1–
13 DATA NORM HI (+) RF 22 AVU AVU CCD T Ball 1+
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SECTION H3 SSMB TO VSC INTERFACE
H3 REQUIRMENTS
H3.1 GENERAL
A VSC is an ORU that converts PFM fiber optic video to PFM copper video and converts PFMcopper video to PFM fiber optic video. VSC’s are mounted on the USL, Hab, and JEM–PMmodules near the PDGF’s in order to convert video signals for use by the PDGF and SSRMS.VSC’s are also mounted on the TUS reel assemblies on S0 to convert video signals for the TUScable.
H3.1.1 INTERFACE DESCRIPTION
For the VSC mounted on the module, the physical interface plane is at the VSC bracket tomodule mounting bracket. For the VSCs mounted on Truss Segment S0 the physical interfaceplane is at the VSC ORU assembly to truss mounting bracket. The electrical interface plane isbetween the VSC connectors and the harness connectors.
H3.1.2 INTERFACE RESPONSIBILITIES
CSA is responsible for development of the VSC. NASA is responsible for the procurement ofthe VSC bracket for the USL and the Hab. NASA is responsible for the procurement of the VSCMounting Hardware Kit for Truss Segment S0. NASDA is responsible for the development ofthe JEM–PM and procurement of the VSC and VSC bracket for the JEM–PM.
H3.1.3 ENGINEERING UNITS AND TOLERANCES
Unless otherwise noted herein, all dimensions in this document are shown in English system ofinch pound (IP) units.
H3.2 STRUCTURAL/MECHANICAL INTERFACES
For a VSC mounted on a module, the VSC bracket will be a standard configuration as shown inFigure H3.2–1 (TBD). The VSC bracket bolt pattern available to the module will be the samefor each application.
For the VSCs mounted on the Truss Segment S0, the interface will be as shown in Figure H3.2–2and H3.2–3. For the VSCs mounted on Truss Segment S0, the VSC Mounting Hardware Kitwill be utilized.
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H3.3 THERMAL INTERFACES
Depending on the thermal environment, the VSC ORU can be passively controlled through theuse of thermal blankets and thermal conduction to the mating element. Conversely the VSCORU provides heaters and RTDs that can be utilized to actively control temperature of the VSCORU.
H3.3.1 PASSIVE THERMAL INTERFACES
The VSC ORU provides Cotherm strips to increase thermal conduction to the VSC bracket asshown in Figure H3.2–2.
H3.3.2 ACTIVE THERMAL INTERFACES
The VSC ORU provides two thermostatically controlled resistive heaters for active thermalcontrol.
H3.4 ELECTRICL INTERFACES
The modules will provide power and PFM video interfaces to the VSC as shown in FigureD3.4.1–1.
The Truss Segment S0 will provide power, RTD data and PFM video interfaces to the VSCs asshown in Figure H3.4–1.
The VSC does not support 1553 data bus interface.
H3.4.1 POWER RETURN AND GROUNDING INTERFACES
The modules will provide power return and grounding interfaces to the VSC as shown in FigureD3.4.1–1. The Truss Segment S0 will provide power return and grounding interfaces to the VSCas shown in Figure H3.4–1.
H3.4.2 POWER CONNECTORS AND PIN ASSIGNMENTS
The VSC ORU power connectors and pin assignments are defined in Tables H3.4.2–1 andH3.4.2–2.
H3.4.3 PFM SYNC AND CONTROL AND VIDEO INTERFACES
The modules will support PFM Fiber Optic video interfaces to the VSC ORU via the PDGFharness. The PDGF harness will provide both PFM Fiber Optic and PFM copper lines to the
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module mounted VSC ORU. The Truss Segment S0 will provide one RTD data interface, PFMFiber Optic (FO) and PFM copper interfaces to the VSC ORU.
H3.4.4 DATA AND VIDEO CONNECTORS AND PIN ASSIGNMENTS
The VSC ORU FO video connectors and pin assigments are defined in Table H3.4.4–1. TheVSC ORU copper video connector and pin assignments are defined in Table H3.4.4–2.
H3.5 ENVIRONMENTS
The VSC ORU to module electromagnetic, grounding, and bonding interface implementationwill be as defined in Figure H3.2–1. The VSC ORU to Truss Segment S0 electromagnetic,grounding, and bonding interface implementation will be as defined in Figure H3.2–2.
H3.6 SOFTWARE INTERFACES
There are no software interfaces between the VSC ORU and the module. There are no softwareinterfaces between the VSC ORU and the SSMB Truss.
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TBD
FIGURE H3.2–1 VSC MODULE MOUNTING BRACKET
SSMB to MSS ICDSSP 42003, Part 2
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(Reference SPAR Drawing 51618–1126, Sheet 1 of 2)
FIGURE H3.2–2 VSC TRUSS MOUNTING BRACKET
SSMB to MSS ICDSSP 42003, Part 2
May 22, 1997
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(Reference SPAR Drawing 51618–1126, Sheet 2 of 2)
FIGURE H3.2–3 VSC TRUSS MOUNTING BRACKET
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TUS VSC 1 Video 1 CoaxTUS VSC 1 Video 2 Coax
TUS VSC 1 Video 3 CoaxTUS VSC 1 Sync 1 Coax
TUS VSC 1 Sync 2 Coax
TUS VSC 2 Video 1 CoaxTUS VSC 2 Video 2 Coax
TUS VSC 2 Video 3 CoaxTUS VSC 2 Sync 1 Coax
TUS VSC 2 Sync 2 Coax
VSC 1
J4J1
J3J2
MDM
S0–1
VSW 1
VSW 2
VSW 3
TUS 1
VSC 2
J4 J1
J3 J2
MDM
S0–2
TUS 2
SPDA
S0–4B
SPDA
S0–3A
TUS VSC 1 Power 20 gaTUS VSC 1 Return 20 ga
TUS VSC 1 RTD HiTUS VSC 1 RTD Lo
TUS VSC 1 Heater 1 Power 20 gaTUS VSC 1 Heater 1 Return 20 ga
TUS VSC 1 Power 20 gaTUS VSC 1 Return 20 gaTUS VSC 1 Heater 2 Power 20 gaTUS VSC 1 Heater 2 Return 20 ga
RPCM
S0 4B–E
RPCM
S0 4B–F
RPCM
SO 3A–E
RPCM
S0 3A–F
TUS VSC 2 Power 20 gaTUS VSC 2 Return 20 gaTUS VSC 2 Heater 1 Power 20 gaTUS VSC 2 Heater 1 Return 20 ga
TUS VSC 2 RTD HiTUS VSC 2 RTD Lo
TUS VSC 2 Power 20 gaTUS VSC 2 Return 20 gaTUS VSC 2 Heater 2 Power 20 gaTUS VSC 2 Heater 2 Return 20 ga
TUS VSC 2 Video 1 FOTUS VSC 2 Video 2 FO
TUS VSC 2 Video 3 FOTUS VSC 2 Sync 1 FO
TUS VSC 2 Sync 2 FO
TUS VSC 1 Video 1 FOTUS VSC 1 Video 2 FO
TUS VSC 1 Video 3 FOTUS VSC 1 Sync 1 FO
TUS VSC 1 Sync 2 FO
FIGURE H3.4–1 TUS VSC ELECTRICAL DIAGRAM
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TABLE H3.4.2–1 DETAILED ELECTRICAL DESCRIPTION OF VSC ORU TO SSMBCONNECTOR J2 (PRIME POWER)