SSP42137_P2_RB_CD_012231.pdf

SSP 42137, Part 2, Revision B

National Aeronautics and Space Administration International Space Station Program Johnson Space Center Houston, T exas Contract No. NNJ09GA18B PIC−SI−01

International Space Station Program

Revision B

TYPE 1 NASA APPROVED

30 December 2009

SPACE STATION PROGRAM

Integrated T russ Segment S0 to Node 3 Interface Control Document, Part 2 esa european space agency

SSP 42137, Part 2, Revision B 30 December 2009

REVISION AND HISTORY PAGE

REV. DESCRIPTION PUB.

DATE

− Initial release 08−05−95

A Revision A released per SSCN 006744, EFF. 03−24−03 07−23−03 Revision A is the first release on the ISS Program.

Note: IRN 42137−P2−0001, 42137−P2−0002, and 42137−P2−0003 have been administratively cancelled.

42137−P2−0001 (IRN 0001) (Administrative Cancel) 42137−P2−0002 (IRN 0002) (Administrative Cancel) 42137−P2−0003 (IRN 0003) (Administrative Cancel) 42137−P2−0004

42137−NA−2001D

42137−NA−2003

B Revision B released per SSCN 012231, EFF. 05−13−10 06−11−10

42137−NA−2004 SSCN 008215

42137−NA−2005 SSCN 012231

42137−NA−2006C SSCN 010560

i

PREFACE

The Space Station Program Integrated Truss Segment S0 to Node 3 Interface Control Document

(ICD), Part 1 defines the physical, functional, and environmental interfaces between the

Integrated Truss Segment (ITS) S0 and the Node 3 modules for the on-orbit interfaces.

The contents of this document are intended to be consistent with the task and products to be prepared by the International Space Station (ISS) Program Partners as defined in SSP 41000, International Space Station System Specification. This ICD shall be implemented on all new

ISS Program activities and shall be included in any existing contracts through contract changes.

This document is under the control of the Interface Control Working Group (ICWG) as described in SSP 30459, International Space Station Interface Control Plan.

ii

INTERNATIONAL SPACE STATION PROGRAM

INTEGRATED TRUSS SEGMENT S0 TO NODE 3

INTERFACE CONTROL DOCUMENT, PART 2

CONCURRENCE

Cristina Duplan Clark ARES/PI&C

PREPARED BY: PRINT NAME ORGN

/s/Cristina Duplan Clark 12/30/09

SIGNATURE DATE

CHECKED BY ARES: Anh Tang ARES/PI&C

PRINT NAME ORGN

/s/Anh Tang 12/30/09

SIGNATURE DATE

DQA: Victoria C. Rodriguez ARES/PI&C

PRINT NAME ORGN

/s/Victoria C. Rodriguez 12/30/09

SIGNATURE DATE

APPROVED BY (NASA): Tyson E. Richmond NASA/OM

PRINT NAME ORGN

/s/Tyson E. Richmond 4/20/10

SIGNATURE DATE

iii

INTERNATIONAL SPACE STATION PROGRAM

INTEGRATED TRUSS SEGMENT S0 TO NODE 3

INTERFACE CONTROL DOCUMENT, PART 2

LIST OF CHANGES

All changes to paragraphs, tables, and figures in this document are shown below:

APPROVAL

AUTHORITY NO. ENTRY DATE CHANGE

PARAGRAPH(S)/

TABLE(S)/FIGURE(S)

006744 42137−NA−2001D Cover Page, Concurrence Page, Preface Page, P: 1.1, 1.2, 1.3, 2.1, 3.1.1, 3.1.1.1, 3.1.1.2, 3.1.1.3, 3.1.2, 3.1.4, 3.2.1.1, 3.2.2;

Figures: 3.1.1−1 sht 0, 3.1.1−1 sht 1, 3.1.1−1 sht 2, 3.1.1−1 sht 3, 3.1.1−1 sht 4, 3.1.1−1 sht 5, 3.1.1−1 sht 6, 3.1.1−1 sht 7, 3.1.1−1 sht 8, 3.1.1−1 sht 9;Tables:

3.2.2−1, 3.2.2−2, 3.2.2−3, 3.2.2−4, 3.2.2−5, 3.2.2−6, 3.2.2−7, 3.2.2−8, 3.2.2−9, 3.2.2−10, 3.2.2−11, 3.2.2−12, 3.2.2−13, 3.2.2−14

006744 42137−NA−2003 P:3.1.1, 3.1.1.1, F:3.1.1−1

006744 42137−P2−0004 Tab: 3.2.2−4, 3.2.2−5, 3.2.2−6, 3.2.2−7, 3.2.2−11, 3.2.2−12

0006744 42137−P2−0003 Tab: 3.2.2−3, 3.2.2−5, 3.2.2−10, 3.2.2−12

BP/96−0324 19 APR 96 42137−P2−0002 Tab. 3.2.2−1, Tab. 3.2.2−2, Tab. 3.2.2−3, Tab. 3.2.2−4, Tab. 3.2.2−5, Tab. 3.2.2−6, Tab. 3.2.2−7, Tab. 3.2.2−8, Tab. 3.2.2−9, Tab. 3.2.2−10, Tab. 3.2.2−11, Tab.3.2.2−12

BP/96−0478 20 JUNE 96 PIRN# 42137−P2−0001 Para. 3.1.1, Para. 3.2.1.1 Fig. 3.1.1−1 (Sheets 0−9) iv

INTERNATIONAL SPACE STATION PROGRAM

INTEGRATED TRUSS SEGMENT S0 TO NODE 3

INTERFACE CONTROL DOCUMENT, PART 2

LIST OF CHANGES − Continued

APPROVAL

AUTHORITY NO. ENTRY DATE CHANGE

PARAGRAPH(S)/

TABLE(S)/FIGURE(S)

008215 11/09 42137−NA−2004 F:3.1.1−1 (Sheet 8 of 10), 3.1.1−1 (Sheet 9 of 10), 3.1.1−1 (Sheet 10 of 10), T3.2.2−2, 3.2.2−4, 3.2.2−6, 3.2.2−7, 3.2.2−9, 3.2.2−11

012231 12/09 42137−NA−2005 P: 2.0

010560 12/09 42137−NA−2006 P: 3.1.1, 3.1.2, T: 3.2.2−2,

3.2.2−4, 3.2.2−6, 3.2.2−7, 3.2.2−9, 3.2.2−11 (Deleted) v

TABLE OF CONTENTS

PARAGRAPH PAGE

1.0 INTRODUCTION 1−1

1.1 PURPOSE AND SCOPE 1−1

1.2 PRECEDENCE 1−1

1.3 RESPONSIBILITY AND CHANGE AUTHORITY 1−1

2.0 DOCUMENTATION 2−1

2.1 APPLICABLE DOCUMENTS 2−1

2.2 REFERENCE DOCUMENTS 2−1

3.0 INTERFACE DEFINITION 3−1

3.1 GENERAL 3−1

3.1.1 INTERFACE DESCRIPTION 3−1

3.1.1.1 DISPLACEMENT BETWEEN S0 AND NODE 3 INTERFACE 3−12

3.1.1.2 DISPLACEMENT BETWEEN PCBM/NODE 3 INTERFACE AND CLEVIS

MECHANISM/NODE 3 INTERFACE 3−13

3.1.1.3 DISPLACEMENT DUE TO MANUFACTURING TOLERANCES OF

NODE 3 3−14

3.1.2 INTERFACE RESPONSIBILITIES 3−14

3.1.3 ENGINEERING UNITS AND TOLERANCES 3−14

3.1.4 COORDINATE SYSTEMS 3−14

3.2 INTERFACES 3−15

3.2.1 STRUCTURAL/MECHANICAL INTERFACE 3−15

3.2.1.1 INTERFACE DESIGN 3−15

3.2.1.1.1 DESIGN CONSTRAINTS 3−15

3.2.2 CONNECTOR CHARACTERISTICS 3−15

APPENDIX

A ABBREVIATIONS AND ACRONYMS A − 1

vi

TABLE OF CONTENTS − Continued

TABLES

TABLES PAGE

3.1.3−1 LINEAR TOLERANCES 3−14

3.1.3−2 ANGULAR TOLERANCES 3−14

3.2.2−1 CONNECTOR CHARACTERISTICS, MBSU 4A POWER 3−16

3.2.2−2 DELETED 3−16

3.2.2−3 CONNECTOR CHARACTERISTICS, HEAT EXCHANGER LOOP

A/CAMERA & CAMERA LT 3−17

3.2.2−4 DELETED 3−17

3.2.2−5 CONNECTOR CHARACTERISTICS, HEAT EXCHANGER LOOP A 3−18

3.2.2−6 DELETED 3−18

3.2.2−7 CONNECTOR CHARACTERISTICS, PDGF VIDEO 3/CAMERA

VIDEO & SYNC 3−19

3.2.2−8 CONNECTOR CHARACTERISTICS, MBSU 2A POWER 3−19

3.2.2−9 DELETED 3−19

3.2.2−10 CONNECTOR CHARACTERISTICS, HEAT EXCHANGER LOOP

B/CAMERA HEATER & CAMERA LIGHT HEATER 3−20

3.2.2−11 DELETED 3−21

3.2.2−12 CONNECTOR CHARACTERISTICS, HEAT EXCHANGER LOOP B 3−21

3.2.2−13 CONNECTOR CHARACTERISTICS, MBSU 1B POWER 3−22

3.2.2−14 CONNECTOR CHARACTERISTICS, MBSU 2B POWER 3−22

vii

TABLE OF CONTENTS − Continued

FIGURES

FIGURES PAGE

3.1.1−1 INTERFACE DESIGN (SHEET 1 OF 10) 3−2

3.1.1−1 INTERFACE DESIGN (SHEET 2 OF 10) 3−3

3.1.1−1 INTERFACE DESIGN (SHEET 3 OF 10) 3−4

3.1.1−1 INTERFACE DESIGN (SHEET 4 OF 10) 3−5

3.1.1−1 INTERFACE DESIGN (SHEET 5 OF 10) 3−6

3.1.1−1 INTERFACE DESIGN (SHEET 6 OF 10) 3−7

3.1.1−1 INTERFACE DESIGN (SHEET 7 OF 10) 3−8

3.1.1−1 INTERFACE DESIGN (SHEET 8 OF 10) 3−9

3.1.1−1 INTERFACE DESIGN (SHEET 9 OF 10) 3−10

3.1.1−1 INTERFACE DESIGN (SHEET 10 OF 10) 3−11

1−1

1.0 INTRODUCTION

1.1 PURPOSE AND SCOPE

This Interface Control Document (ICD) defines and controls the implementation of the physical and functional interfaces between the International Space Station (ISS) Integrated Truss Segment S0 and Node 3 elements. Part 1 to this ICD contains the design requirements for this interface;

this Part 2 contains the design solution for these requirements.

1.2 PRECEDENCE

In the event of conflict between SSP 41000, System Specification for Space Station, and the contents of this ICD, the requirements of the System Specification shall take precedence.

1.3 RESPONSIBILITY AND CHANGE AUTHORITY

This document is prepared and maintained in accordance with SSP 30459, International Space Station Interface Control Plan.

2−1

2.0 DOCUMENTATION

The following documents of the exact issue shown, or if no issue is specified, the issue in effect at the effective date of this document, form a part of this document to the extent specified herein.

In the event of conflict between documents referenced here and the contents of Section 3, the order of precedence shall be as stated in paragraph 1.3 of this document.

2.1 APPLICABLE DOCUMENTS

2.2 REFERENCE DOCUMENTS

The following documents of the date and issue shown including specifications, models, standards, guidelines, handbooks, and other special publications are applicable to the extent specified herein. Inclusion of applicable documents herein does not in any way supersede the order of precedence identified in paragraph 1.2.

The references show where each applicable document is cited in this document.

DOCUMENT NO. TITLE

SSP 30219 Space Station Reference Coordinate Systems References 3.1.4

SSP 41000 Space Station Systems Specification References 1.2

ANSI/ASME B46.1 Surface texture (Surface Roughness, Waviness, and Lay) References 3.2.1.1.1

ANSI Y14.5M Dimensioning and Tolerancing References 3.1.3

MIL−B−5087 Bonding, Electrical, and Lightning Protection, for References 3.2.1.1.1

SSP 30459 International Space Station Interface Control Plan References 1.3

SSQ 21635 Connectors and Accessories, Electrical, Circular Miniature, IVA/EVA Compatible, Space Quality, General Specification for

References 3.2.2

3−1

3.0 INTERFACE DEFINITION

3.1 GENERAL

3.1.1 INTERFACE DESCRIPTION

The S0 to Node 3 interface consists of the interface for the on–orbit, Extravehicular Activity (EVA) installed utility tray and the on–orbit, EVA connected avionic connectors. The utility tray is taken to orbit stowed on S0. Because of the relocation of Node 3 from the Nadir side of Node 1 to the port side of Node 1, the tray will remain in its stowed location. Node 3 provides a scarred clevis fitting complete with latch pin to accept the latch on the end of the tray. The tray is no longer used. The utilities will be connected using external cables.

For reference only, the total uncertainty due to the build up of assumed tolerances at the utility tray to Node 3 interface is +6.590 inches to –6.538 inches in the XA direction, +5.851 inches to –5.947 inches in the YA direction and +4.156 inches to –4.290 inches in the ZA direction.

Figure 3.1.1–1, sheet 1 of 10, shows this as a tolerance box built around Point 0, the nominal Node 3 attach point, which is dimensioned back to the S0 datum. The tolerance box may be assumed to enclose all possible locations of the Node 3 attach point with respect to S0 datum for tray installation.

For reference only, the total displacement, including rotations, between S0 and Node 3 clevis mechanism attachment point, due to modules pressurization, manufacturing and assembly tolerances, thermal effects and on−orbit transient loads are reported in paragraph 3.1.1.1. These displacements are being assumed as controlled by NASA/Prime. They are not requirements on individual modules or segments. Changes to these parameters could affect the Node 3 Umbilical design.

For reference only, the tolerances for the displacement between Passive Common Berthing Mechanism (PCBM)/Node3 interface and clevis mechanism/Node 3 interface are reported in paragraph 3.1.1.2 and are regarded to form part of (and not in addition to) paragraph 3.1.1.1 parameters. Paragraph 3.1.1.2 is provided by the Node 3 supplier to describe “actual” calculated displacements between the PCBM/Node3 interface and the Node 3 clevis pin (point 0).

For reference only, the tolerances for the displacement of the Node 3 clevis due to Node 3 manufacturing tolerances are reported in paragraph 3.1.1.3.

For reference only, the Node 3 supplier responsibility shall be limited to meet the deflections included in paragraphs 3.1.1.2 and 3.1.1.3 only.

3−2

(1

.9

(1

.4

FIGURE 3.1.1−1 INTERFACE DESIGN (SHEET 1 OF 10)

3−3

FIGURE 3.1.1−1 INTERFACE DESIGN (SHEET 2 OF 10)

3−4

FIGURE 3.1.1−1 INTERFACE DESIGN (SHEET 3 OF 10)

3−5

FIGURE 3.1.1−1 INTERFACE DESIGN (SHEET 4 OF 10)

3−6

FIGURE 3.1.1−1 INTERFACE DESIGN (SHEET 5 OF 10)

3−7

FIGURE 3.1.1−1 INTERFACE DESIGN (SHEET 6 OF 10)

3−8

FIGURE 3.1.1−1 INTERFACE DESIGN (SHEET 7 OF 10)

3−9

FIGURE 3.1.1−1 INTERFACE DESIGN (SHEET 8 OF 10)

3−10

FIGURE 3.1.1−1 INTERFACE DESIGN (SHEET 9 OF 10)

o

3x o o 0’

3−11

FIGURE 3.1.1−1 INTERFACE DESIGN (SHEET 10 OF 10)

3−12

3.1.1.1 DISPLACEMENT BETWEEN S0 AND NODE 3 INTERF ACE

a. Displacements due to module pressurization between the Module to Truss Structure (MTS) and the Node 3 attach point (includes displacements of Lab, Node 1 and Node 3) will not exceed:

0.785 in. Aft (−XA).

0.12 in. Stbd (+YA).

0.55 in. Nadir (+ZA).

Plus a rotation about Y’A axis of Node 3 about displaced Node 1−Node 3 interface of −0 degrees 6 minutes.

b. Rotation due to interface tolerances between the S0 truss and the Lab Module through the Lab Cradle Assembly (LCA) will not exceed+/− 0 degrees 45 minutes about the X’A, Y’ A and Z’A axes at the center of the LCA. For Node 3 tray tolerance analysis only, rotation about the X’A axis is reduced to +/− 0 degrees 34.8 minutes because of the way the passive LCA platform was used as a datum to locate the S0 Node 3 tray latches, reducing S0 to LCA interface rotation about X’A from 15 minutes (0.25°) to 4.8 minutes (0.08°)

c. Rotation due to MTS thermal deformation will not exceed +/−0 degrees 5 minutes about X’, +/− 0 degrees 7 minutes about Y’ and +/−0 degrees 10.4 minutes about Z’ at the displaced midpoint of the 4 MTS strut−to−Lab attach points.

d. Rotation due to interface tolerances and Common Berthing Mechanism (CBM) pressure and thermal deformations will not exceed +/− 0 degrees 21 minutes about X’, +/−0 degrees 21.8 minutes about Y’ and +/−0 degrees 21.8 minutes about Z’ at the displaced Lab−Node 1 interface.

e. Rotation due to interface tolerances and CBM pressure and thermal deformations will not exceed +/− 0 degrees 18.8 minutes about X’, +/− 0 degrees 21.8 minutes about Y’ and +/− 0 degrees 21 minutes about Z’ at the displaced Node 1−Node 3 interface.

f. Assembly tolerances between the MTS and Node 3 (includes tolerances of LCA, Lab, Node 1 and Node 3) will not exceed :

+/− 0.203 in. Forward/Aft (+/−XA)

+/− 0.19 in. Stbd/Port (+/−YA)

+/− 0.203 in. Nadir/Zenith (+/−ZA)

g. Displacement due to CBM pressure deformations between the Lab, Node 1, and Node 3 will not exceed 0.125 inch. XA (assumed +/−) and 0.125 inch. ZA (assumed +/−).

h. Thermal displacements from the S0 attach point (center of Node 3 Tray clevis/handhold) to the Node 3 attach point (center of clevis pin−point O) will not exceed:

+/− 0.16 in. XA

+/− 0.13 in. YA

+/− 0.13 in. ZA

3−13

These displacements do not include the linear thermal expansion of the Node 3 tray of approximately +0.51 in. to −0.340 in. This expansion will be accommodated by the ”swing arm” design of the tray−to Node 3 strut.

i. Deflections due to on−orbit transient loads were assumed zero. Unigraphics analysis, using the above parameters, was performed to confirm that at the worst case tolerance extremes:

The Node 3 tray can be latched to the Node 3 clevis;

There is clearance between the outfitted Node 3 tray and adjacent structure, including the nearest MTS strut, Lab trunnion pin or plate, Airlock debris shield, Airlock trunnion plate, and the high pressure gas tank mounted in the forward−nadir position on the Airlock − provide the dummy connector panels are removed from the Node 3 end of the tray first.

Pairs of node points were added to the integrated on−orbit finite element model corresponding to these tray−to−structure clearance gaps. Design Analysis Cycle #6 (Periodic Loads cycle analysis) output displacements were compared with these gaps to verify no tray−to−structure contact due to on−orbit transient loads.

3.1.1.2 DISPLACEMENT BETWEEN PCBM/NODE 3 INTERF ACE AND CLEVIS

MECHANISM/NODE 3 INTERFACE

Node 3 design has been assessed for displacements of Point 0, the nominal Node 3 attach point for the clevis mechanism with respect to the PCBM/Node 3 interface, (reference Point “Y” in figure 3.1.1−1). These displacements include pressurization, thermal distortion, and on−orbit transient loads.

a. Displacement due to Node 3 pressurization will not exceed

• X = 0.200 inch (5.08 mm) towards Aft

• Y = 0.200 inch (5.08 mm) towards Port

• Z = 0.200 inch (5.08 mm) towards Nadir

b. Displacement due to Node 3 thermal distortion

• X = ± 0.055 inch (1.40 mm)

• Y = ± 0.055 inch (1.40 mm)

• Z = ± 0.055 inch (1.40 mm)

c. Displacement due to application of on−orbit transient loads to Node 3

• X = ± 0.031 inch (0.8 mm)

• Y = ± 0.031 inch (0.8 mm)

• Z = ± 0.031 inch (0.8 mm)

3−14

3.1.1.3 DISPLACEMENT DUE TO MANUFACTURING TOLERANCES OF NODE 3

Manufacturing tolerances resulting from the clevis mechanism attachment to Node 3 secondary structure shall be applied with respect to the datums D, E, & F ensuring that the position of datum “Point 0” (the Node 3 attach point) is maintained within positional tolerance specified in Figure 3.1.1−1, sheet 6 of 9.

3.1.2 INTERFACE RESPONSIBILITIES

Boeing is responsible for development of the ITS S0 interface and ESA is responsible for development of the Node 3 interface. The Integrated Truss Segment (ITS) S0 element provides the avionic harnesses complete with connector halves. The Node 3 element provides connector halves to accept those provided by the S0.

3.1.3 ENGINEERING UNITS AND TOLERANCES

Interpret dimensioning and tolerancing per ANSI Y14.5M−1982. Unless otherwise noted herein, dimensions are in inches. tolerances on linear dimensions are defined in Table 3.1.3−1.

Tolerances on angular dimensions are defined in Table 3.1.3−2. Orthographic projections constructed using third angle projection system.

TABLE 3.1.3−1 Linear T olerances

Dimension Tolerance

.XX +/− .03

.XXX +/−.010

TABLE 3.1.3−2 Angular T olerances

Dimension Tolerance

X ° +/− 1° X °X’ +/− 0° 30’

3.1.4 COORDINATE SYSTEMS

The coordinate system used in defining this interface is the Space Station Analysis Coordinate System as defined in SSP 30219, Space Station Reference Coordinate Systems.

3−15

3.2 INTERFACES

3.2.1 STRUCTURAL/MECHANICAL INTERF ACE

3.2.1.1 INTERFACE DESIGN

Figure 3.1.1−1 (10 sheets) shows the detail design of the S0 to Node 3 interface. Sheets 0 through 6 describe the utility tray interface and sheets 7 through 9 describe the connector interface. Sheets 0 and 1 establish the datums from which the interfaces are located. Sheet 0 also shows the tolerance box relative to S0 in which the clevis pin that accepts the utility tray latch must be located. Sheets 2 and 3 define the clevis pin location relative to Node 3. Sheets 4, 5 and 6 describe the envelope required for the utility tray latch and pip pin.

Sheets 7 through 9 define the connector interface. Sheet 7 shows the connectors, orientation of the connector handles and the required gap between the Node 3 end ring and debris shield ring.

Sheet 8 defines the connector circumferential locations and the connector reference designations.

Sheet 9 defines the radial location of the connectors and the distance between the connector centers and the Node 3 end ring.

3.2.1.1.1 DESIGN CONSTRAINTS

The interface design is in accordance with the requirements of Part 1 to this document. The utility tray latch is made of anodized aluminum and the clevis and pin are compatible in accordance with Part 1 of this document. Interfacing surface roughness shall be 125 micro inches per ANSI/ASME B46.1, Surface Texture (Surface Roughness, Waviness, and Lay).

Bonding at the interface is not required since a bonding jumper between the tray and S0 provides a Class S bond per MIL−B−5087, Bonding, Electrical, and Lightning Protection, for Aerospace Systems.

3.2.2 CONNECTOR CHARACTERISTICS

Tables 3.2.2−1 through 3.2.2−14 provide the characteristics of the connectors at the interface.

Each table describes the characteristics of an individual connector with a reference designation that corresponds to that shown in sheet 8 of Figure 3.1.1−1. Electrical connectors are in accordance with SSQ 21635, General specification for Connectors and Accessories, Electrical, Circular, Miniature, IVA/EVA/Robot Compatible, Space Quality.

3−16

ÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁTABLE 3.2.2−1 CONNECTOR CHARACTERISTICS, MBSU 4A POWER

CONNECTOR ID

Ref. Des S0

P101 Part Number NZGL06G2525LN3SN

Ref. Des

NODE 3

J101 Part Number NZGL07T2525LN3PN

PIN FUNCTION TABLE

Contact

ID

Signal

Function Wire

Gauge

EMC

Class

System Remarks

A NODE34A PRI PWR 4 EO EPS FROM MBSU−4A

C NODE34A RTN 4 EO EPS

B 4A FAULT RTN 8 EO EPS

TABLE 3.2.2−2 DELETED

3−17

ÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁTABLE 3.2.2−3 CONNECTOR CHARACTERISTICS, HEAT EXCHANGER LOOP

A/CAMERA & CAMERA L T

CONNECTOR ID

Ref. Des S0

P103 Part Number NZGL06G1717N26SN

Ref. Des

NODE 3

J103 Part Number NZGL07T1717N26PN

PIN FUNCTION TABLE

Contact

ID

Signal Function

Cable Type

Wire Gauge

EMC

Class.

System Remarks

*B ECPNODE3(CAMERA) SEC

PWR

20 EO EPS FROM SPDA

S0−1A

T ECPNODE3(CAMERA) RTN 20 EO EPS

S FAULT RTN 20 EO EPS

*A ECPLTNODE3(LIGHT) SEC

PWR

20 EO EPS

N ECPLTNODE3(LIGHT) RTN 20 EO EPS

P FAULT RTN 20 EO EPS

Z MT−A HX BYP VLV NORMAL

FLOW CMD SEC PWR

TQ 20 EO ATCS SDO PWR 1A

(MDM S0−1)

Y MT−A HX BYP VLV NORMAL

FLOW CMD RTN

20 EO ATCS

X MT−A HX BYP VLV BYP

FLOW CMD SEC PWR

20 EO ATCS

*C MT−A HX BYP VLV BYP

FLOW CMD RTN

20 EO ATCS

C MT−A HX ISLN/RLF VLV

OPEN CMD SEC PWR

TQ 20 EO ATCS

U MT−A HX ISLN/RLF VLV

OPEN CMD RTN

20 EO ATCS

V MT−A HX ISLN/RLF VLV CL

CMD SEC PWR

20 EO ATCS

W MT−A HX ISLN/RLF VLV CL

CMD RTN

20 EO ATCS

NOTES: lower case letter TQ− Twisted quad

ÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁTABLE 3.2.2−4 DELETED

3−18

TABLE 3.2.2−5 CONNECTOR CHARACTERISTICS, HEAT EXCHANGER LOOP A

Connector ID

Ref. Des S0

P105 Part Number NZGL06G1513N35PH−1

Ref. Des

NODE 3

J105 Part Number NZGL07T1513N35SH

PIN FUNCTION TABLE

Contact

ID

Signal Function

Wire Gauge

EMC

Class

System Remarks

15 MT−A HX BYP VLV

NORMAL FLOW POS HI

22 HO ATCS

1 MT−A HX BYP VLV

NORMAL FLOW POS LO

22 HO ATCS

14 MT−A HX BYP VLV BYP

FLOW POS HI

22 HO ATCS

21 MT−A HX BYP VLV BYP

FLOW POS LO

22 HO ATCS

20 MT−A HX ISLN/RLF VLV

OPEN POS HI

22 HO ATCS

19 MT−A HX ISLN/RLF VLV

OPEN POS LO

22 HO ATCS

18 MT−A HX ISLN/RLF VLV

CL POS HI

22 HO ATCS

22 MT−A HX ISLN/RLF VLV

CL POS LO

22 HO ATCS

16 MT−A HX OUTLET RTD

SIG

22 HO ATCS

17 MT−A HX OUTLET RTD

RTN

22 HO ATCS

TABLE 3.2.2−6 DELETED

3−19

TABLE 3.2.2−7 CONNECTOR CHARACTERISTICS, PDGF VIDEO 3/CAMERA

VIDEO & SYNC

CONNECTOR ID

Ref. Des S0

P107(1) Part Number NZGL06G1513N4PC−1

Ref. Des

NODE 3

J107(1) Part Number NZGL07T1513N4SC

PIN FUNCTION TABLE

Contact

ID

Signal Function

Wire Gauge

EMC

Class

System Remarks

C (2) PDGF VIDEO−3 16FO NA C & T FROM EVS−3

B VCSA PORT 14 VIDEO 16FO NA C & T

D VCSA PORT 14 SYNC 16FO NA C & T

NOTES:

(1) These connectors are on both S0 and Node 3 with no connectivity between them.

(2) Not implemented in Node 3.

TABLE 3.2.2−8 CONNECTOR CHARACTERISTICS, MBSU 2A POWER

CONNECTOR ID

Ref. Des S0

P108 Part Number NZGL06G2525LN3SD

Ref. Des

NODE 3

J108 Part Number NZGL07T2525LN3PD

PIN FUNCTION TABLE

Contact

ID

Signal Function

Wire Gauge

EMC

Class

System Remarks

A NODE32A PRI PWR 4 EO EPS FROM MBSU 2A

C NODE32A RTN 4 EO EPS

B 2A FAULT RETURN 8 EO EPS

TABLE 3.2.2−9 DELETED

3−20

TABLE 3.2.2−10 CONNECTOR CHARACTERISTICS, HEAT EXCHANGER LOOP

B/CAMERA HEA TER & CAMERA LIGHT HEA TER

Connector ID Ref. Des S0

P110 Part Number

NZGL06G1717N26SA

Ref. Des

NODE 3

J110 Part Number

NZGL07T1717N26PA

PIN FUNCTION TABLE

Contact

ID

Signal Function

Cable Type

Wire Gauge

EMC

Class.

System Remarks

*B ECPHTRNODE3 (CAMERA)

SEC PWR

20 EO EPS FROM SPDA

S0−2B

T ECPHTRNODE3 (CAMERA)

RTN

20 EO EPS

*A ECPLTHTRNODE3 (LIGHT)

SEC PWR

20 EO EPS

S ECPLTHTRNODE3 (LIGHT)

RTN

20 EO EPS

Z LT−B HX BYP VLV NORMAL

FLOW CMD SEC PWR

TQ 20 EO ATCS SDO PWR 2B

(MDM S0−2)

Y LT−B HX BYP VLV NORMAL

FLOW CMD RTN

20 EO ATCS

X LT−B HX BYP VLV BYP

FLOW CMD SEC PWR

20 EO ATCS

*C LT−B HX BYP VLV BYP

FLOW CMD RTN

20 EO ATCS

C LT−B HX ISLN/RLF VLV

OPEN CMD SEC PWR

TQ 20 EO ATCS

U LT−B HX ISLN/RLF VLV

OPEN CMD RTN

20 EO ATCS

V LT−B HX ISLN/RLF VLV CL

CMD SEC PWR

20 EO ATCS

W LT−B HX ISLN/RLF VLV CL

CMD RTN

20 EO ATCS

* Notes lower case letter TQ− Twisted quad

3−21

TABLE 3.2.2−11 DELETED

TABLE 3.2.2−12 CONNECTOR CHARACTERISTICS, HEAT EXCHANGER LOOP B

Connector ID

Ref. Des S0

P112 Part Number NZGL06G1513N35PG−1

Ref. Des

NODE 3

J112 Part Number NZGL07T1513N35SG

PIN FUNCTION TABLE

Contact

ID

Signal Function

Wire Gauge

EMC

Class.

System Remarks

15 LT−B HX BYP VLV NORMAL

FLOW POS HI

22 HO ATCS

1 LT−B HX BYP VLV NORMAL

FLOW POS LO

22 HO ATCS

14 LT−B HX BYP VLV BYP FLOW

POS HI

22 HO ATCS

21 LT−B HX BYP VLV BYP FLOW

POS LO

22 HO ATCS

20 LT−B HX ISLN/RLF VLV OPEN

POS HI

22 HO ATCS

19 LT−B HX ISLN/RLF VLV OPEN

POS LO

22 HO ATCS

18 LT−B HX ISLN/RLF VLV CL

POS HI

22 HO ATCS

22 LT−B HX ISLN/RLF VLV CL

POS LO

22 HO ATCS

16 LT−B HX OUTLET RTD SIG 22 HO ATCS

17 LT−B HX OUTLET RTD RTN 22 HO ATCS

3−22

TABLE 3.2.2−13 CONNECTOR CHARACTERISTICS, MBSU 1B POWER

Connector ID

Ref. Des S0

P113 Part Number NZGL06G2525LN3SB

Ref. Des

NODE 3

J113 Part Number NZGL07T2525LN3PB

PIN FUNCTION TABLE

Contact

ID

Signal Function

Wire Gauge

EMC

Class.

System Remarks

A NODE31B PRI PWR 4 EO EPS FROM MBSU−1B

C NODE31B RTN 4 EO EPS

B 1B FAULT RTN 8 EO EPS

TABLE 3.2.2−14 CONNECTOR CHARACTERISTICS, MBSU 2B POWER

Connector ID Ref. Des S0

P114 Part Number NZGL06G2525LN3SC

Ref. Des

NODE 3

J114 Part Number NZGL07T2525LN3PC

PIN FUNCTION TABLE

Contact

ID

Signal Function

Wire Gauge

EMC

Class.

System Remarks

A NODE32B PRI PWR 4 EO EPS FROM MBSU−2B

C NODE32B RTN 4 EO EPS

B 2B FAULT RTN 8 EO EPS

A−1

APPENDIX A ABBREVIA TIONS AND ACRONYMS

A.1 ABBREVIA TIONS AND ACRONYMS

ASI Agenzia Spaziale Italiana (Italian Space Agency)

ATCS Active Thermal Control System

BYP Bypass

CBM Common Berthing Mechanism

CL Close

Class Classification

CMD Command

EMC Electromagnetic Compatibility

EPS Electrical Power System

EVA Extravehicular Activity

EVS External Video Switch

HX heat exchanger

ICD Interface Control Document

ICWG Interface Control Working Group

ID Identification in inch

ISLN/RLF Isolation Relief

ISS International Space Station

ITS Integrated Truss Segment

IVA Intravehicular Activity

LCA Lab Cradle Assembly

MBSU Main Bus Switching Unit

MDM Modulator/Demodulator

A − 2

ABBREVIATIONS AND ACRONYMS − Continued mm millimeter

MT Mobile Transporter

MTS Module to Truss Structure

PCBM Passive Common Berthing Mechanism

PDGF Power Data Grapple Fixture

POS Position

PRI Primary

PWR Power

PL Payload

Ref Des Reference Designation

RLF Relief

RTD Resistive Temperature Device

RTN Return

S0 Integrated Truss Segment S0

SDO Selenoid Driver Output

SEC Secondary sht Sheet

SIG Signal

SPDA Secondary power distribution assembly

SYNC Syncronization

VLV Valve