SSP_50227-RevC.docx

SSP 50227

Revision C Russian Segment to PDGF/PVGF/ SSRMS Interface Control Document

International Space Station Program

Revision C

November 2015

National Aeronautics and Space Administration International Space Station Program Johnson Space Center Houston, Texas Contract No.: NNJ12GA46C

REVISION AND HISTORY

Incorporate the following PIRNs associated with appropriate SSCNS.

XX-XX-XX

PIRN 50227−NA−0002 IRN N/A SSCN 011497

PIRN 50227−NA−0003 IRN N/A SSCN 011497

PIRN 50227−NA−0004 IRN N/A SSCN 011497

Revision B of this document incorporates both the previous updates included in Revision A as well as new updates agreed upon by NASA and RSA.

Revision A will not be released and the contents are included in Revision B.

Incorporate the following PIRNs associated with appropriate SSCNS 10-21-09

PIRN 50227−NA−0006B IRN N/A SSCN 011497

PIRN 50227−NA−0007 IRN N/A SSCN 011497

Incorporate the following PIRNs associated with appropriate SSCNS 06-17-16

PIRN 50227−NA−0008 IRN N/A SSCN 015120

PIRN 50227−NA−0009 IRN N/A SSCN 015120

PIRN 50227−NA−0010 IRN N/A SSCN 015120

PIRN 50227−NA−0011 IRN N/A SSCN 015120

PIRN 50227−NA−0012 IRN N/A SSCN 015120

PREFACE

russian segment to PDGF/pvgf/ssrms interface control document The SSP 50227, Russian Segment to PDGF/PVGF/SSRMS Interface Control Document (ICD) shall be implemented on all new Program contractual and internal activity and shall be included in any existing contracts through contract changes. This document is under the control of the Space Station Control Board (SSCB) with the concurrence of the respective International Partners, any changes or revisions will be approved by the SSCB and the respective International Partners.

INTERNATIONAL SPACE STATION PROGRAM

russian segment to PDGF/pvgf/ssrms interface control document

CONCURRENCE

november 2015 russian segment to pdgf/pvgf/ssrms interface control document technical CONCURRENCE November 2015 see directive or PIRNs for approvals

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TABLE OF CONTENTS

APPENDIX

a Acronyms and abbreviations a-1

TABLE

FIGURE

SSP 50227

Revision C vii

INTRODUCTION

PURPOSE and SCOPE The purpose of this document is to capture interface requirements between elements of the Russian Segment and US provided grapple fixtures to enable the Russian Segment to interface with the Space Station Remote Manipulator System (SSRMS).

The scope of this document is limited to interfaces requirements between the Functional Cargo Block (FGB) and the Power and Data Grapple Fixture (PDGF), the FGB and the Video Signal Converter (VSC), and the Mini Research Module 1 (MRM1) and the Power and Video Grapple Fixture (PVGF).

PRECEDENCE

In the event of conflict between SSP 41163, Russian Segment (RS) Specification and the Russian module requirements in this Interface Control Document, the requirements of the RS shall take precedence.

In the event of conflict between SSP 41162, Segment Specification for the United States On-Orbit Segment and the U.S. Hardware requirements in this ICD, the requirements of the USOS shall take precedence.

icd DESCRIPTION General FGB and MRM1 interface representation is given by Figure 1.3-1, FGB to PDGF Interfaces Configuration Diagram, Figure 1.3-2, MRM1 to PVGF Interface Configuration Diagram, and Table 1.3-1, FGB/MRM1 Interface Documentation Location Matrix that provides the location of interface documentation referring to other documents other than this ICD. Requirements in this ICD have been developed based on SSP 42004, Mobile Servicing System (MSS) to User (Generic) Interface Control Document, Part 1.

Note: The Diagram and Matrix are included for information only and does not infer responsibility or requirements on any signatory of this ICD.

FIGURE 1.3-1 FGB TO PDGF INTERFACES CONFIGURATION DIAGRAM

TABLE 1.3-1 FGB/MRM 1 Interface Documentation Location Matrix

(2 PAGES)

SSP 50227 (both sides of interface)

Fiber Optic Video Cable layouts & pathways mounted on US (PMA 1, Node 1, Z1)

SSP 50227 (Both sides of interface)

FGB PDGF Mounting Ring to PDGF Stand.

- Structural, Mechanical

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VSC Baseplate to VSC Adapter Plate

– Thermal

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FIGURE 1.3-2 MRM1 TO PVGF INTERFACE CONFIGURATION DIAGRAM

INTERFACE RESPONSIBILITIES

U.S. and canadian Hardware RESPONSIBILITIES Unless otherwise specified herein, NASA has the responsibility for developing the interface requirements in this document.

russian module RESPONSIBILITIES Unless otherwise specified herein, Russian Space Agency (RSA) has the responsibility for developing the Russian module interface requirements in this document.

UNITS

ENGINEERING UNITS

Unless otherwise specified, all dimensions in this section are defined in the English System of inch pound units with the International System of Units (SI) metric equivalent shown in parentheses. For the purpose of verification either system of units can be used.

UNITS OF CONVERSION

The units of conversion are in accordance with American Society of Testing Materials (ASTM) E380-91, Standard Practice for Use of the SI (The Modernized Metric System).

Coordinate Systems The space station coordinate system is defined in SSP 30219.

RESPONSIBILITY AND CHANGE AUTHORITY

This document is prepared and maintained in accordance with SSP 50135, International Space Station Interface Control Plan NASA/RSA. NASA has prime responsibility for preparation and maintenance of this ICD.

SSP 50227

Revision C

1-5

DOCUMENTS

APPLICABLE DOCUMENTS

The following documents of the date and issue shown include specifications, models, standards, guidelines, handbooks, and other special publications. Current Issue is shown in parentheses in place of the specific date and issue when the document is under Space Station Control Board control. The status of documents identified by Current Issue may be determined from the International Space Station Program Baseline Activity Index and Status Report.

The documents in this paragraph are applicable to the extent specified in each section. 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.

The following applicable documents of the exact issue shown form a part of this document to the extent specified in each section.

Paragraphs: C3.1.3, C3.1.4, C3.2.1.5, C3.2.1.5.1, C3.2.1.5.2, C3.2.1.5.2.1, C3.2.1.5.2.2, C3.2.1.5.2.3.1.1.1, C3.2.1.5.2.3.1.1.2, C3.2.1.5.3, C3.2.1.7.4, C3.2.2.4.1, C3.2.2.4.1.1, C3.2.2.4.1.2, C4.3.2.1.5.2, C4.3.2.2.4.1.1, H3.2.1.6, H3.2.1.6.1, H3.2.1.6.1.1, H3.2.1.6.1.2, H3.2.1.6.1.3, H3.2.2.6, H5.3.3, Tables: 1.3-1, C4.0-1, H4.0-1, Figures: C3.2.1.5.2-2, H3.2.1.6.1.1-1

SSP 30237

Rev. B Space Station Electromangetic Emissions and Susceptibility Requirements H3.2.2.5.1.2, H3.2.2.5.1.6.1-1

Paragraphs: C3.2.2.6.2, D3.2.2.5.2, H3.2.2.9.2

Paragraphs: C3.2.2.6.4, D3.2.2.5.4, H3.2.2.9.4

Paragraphs: C3.2.2.6.1, C3.2.2.6.5, C3.2.2.6.6, D3.2.2.5.1, D3.2.2.5.5, D3.2.2.5.6, H3.2.2.9.1, H3.2.2.9.5, H3.2.2.9.6, Table: C4.0-1

Paragraph: C5.2.2.6.3, D3.2.2.5.3, Table: H4.0-1

Paragraphs: C3.2.1.3.5, C3.2.2.2.1, D3.2.2.2.2, Table: C4.0-1

Paragraphs: 1.2, C3.2.1.3.5, C3.2.2.2.1, C3.2.2.6.10, D3.2.2.2.2, Table: C4.0-1

Paragraphs: 1.2, C3.2.1.8.1, D3.2.1.6

Paragraph:H5.3.3.1

Paragraph 1.3

Paragraphs: C3.2.1.3.2, C3.2.1.4.2.1, Tables: 1.3-1, C4.0-1, H4.0-1, Figures: 1.3-1, C3.2.1.5.2-1

Paragraphs: C3.2.1.3.5, C3.2.1.5.2.1.2, C3.2.1.5.2.3.1.1.2, C3.2.1.7.1, C3.2.1.7.2, C3.2.1.7.3, C3.2.1.7.4, C3.2.1.7.5, C3.2.1.7.6, D3.2.1.5.1, D3.2.1.5.2, D3.2.1.5.3, D3.2.1.5.5, D3.2.1.5.6, H3.2.1.4.1, H3.2.1.9.1, H3.2.1.9.2, H3.2.1.9.3, H3.2.1.9.4, H3.2.1.9.5, H3.2.1.9.6, Tables: C4.0-1, D4.0-1, H4.0-1

Paragraphs: C3.2.2.4.1.1, , H3.2.1.6.1, H5.3.3, Tables: 1.3-1, C4.0-1, H4.0-1

Paragraphs: C4.0, C4.1, C4.2, D4.0, D4.1, D4.2, H4.0, H4.1, H4.2

Table: 1.3-1

Paragraph: 1.6

Paragraph: C3.2.1.3.5 reference documents The following Reference Documents of the exact issue shown form a part of this document to the extent specified herein.

Paragraphs: 1.5.3, Table: H3.2.1.2-1

Paragraphs: 1.5.2

2-3

HEADING ONE

Section A3: Deleted Section A4: Deleted Section A5: Deleted

SSP 50227

Revision C

A3-1

Section B3: Deleted Section B4: Deleted

B3-1

SECTION C3: FUNCTIONAL CARGO BLOCK TO POWER AND DATA GRAPPLE FIXTURE ASSEMBLY INTERFACE

C3.0 REQUIREMENTS

C3.1 GENERAL

C3.1.1 iNTERFACE DESCRIPTION The FGB Module to PDGF Assembly interface consist of structural, mechanical, thermal, environmental, and power interfaces.

The PDGF will interface with the FGB via mechanical attachments and electrical (power) connections. The PDGF will be installed IVA to the PDGF mounting ring already installed on the PDGF Stand. The FGB will require a Cable Harness be provided with the PDGF to support electrical connections (power/data/video). For purposes of this section of the ICD, the PDGF mounting structure (PDGF Stand which includes the FGB hull) is considered a single entity as part of the FGB Module when the PDGF stand is installed on the FGB by EVA after being delivered as a separate cargo. The reason for this approach is to assure that the interface between the PDGF stand and the FGB Module meet the SSRMS structural loads and stiffness requirements in Section C.3.2.1.3.1 in this document.

The PDGF Assembly to FGB Module on-orbit configuration is shown in Figure C3.1.1-1, FGB Module to PDGF Assembly On-Orbit Configuration Diagram. The PDGF Assembly to FGB Module functional interface is shown in Figure C3.1.1-2, FGB Module to PDGF Assembly Functional Interface Diagram.

FIGURE C3.1.1-1 FGB module to Pdgf assembly on-orbit configuration diagram

FIGURE C3.1.1-2 FGB module to PDGF assembly FUNCTIONAL Interface DIAGRAM C3.1.1.1 FGB description The FGB Module provides ports for attaching Russian and U.S. modules on-orbit. The FGB Module contains the capability to support power, fluids, air, data, video, and audio utilities.

C3.1.1.2 FGB PDGF assembly description The PDGF Assembly is mounted on the FGB Module to allow manipulation by the SSRMS. The PDGF Assembly consists of a PDGF, Mounting Ring, bolts, and a PDGF Cable Harness.

C3.1.1.3 PDGF ASSEMBLY WEIGHT

The weight of the PDGF Assembly, including PDGF ORU Assembly, PDGF Grapple Shaft ORU, and PDGF Mounting Ring (attached to PAMA) shall not exceed 85 lbs (38.6 kg). Note: This weight excludes the PDGF Mounting Ring attachment hardware and the FGB PDGF External Harness.

C3.1.2 COORDINATE SYSTEMS

The PDGF assembly coordinate system will be as defined in Figure C3.1.2-1, PDGF Assembly Coordinate System. The FGB Module coordinate system will be as defined in Figure C3.1.2-2, FGB Module Coordinate System Diagram.

FIGURE C3.1.2-1 PDGF ASSEMBLY COORDINATE SYSTEM

FGB

Z Z Y Y X X X Y Z - Design Coordinate System X,Y,Z Dynamic and Coordinate System Ballistic Mass Center

FIGURE C3.1.2-2 FGB MODULE COORDINATE SYSTEM DIAGRAM

C3.1.3 fgb INTERFACE FUNCTIONS The FGB Module will:

C3.1.4 PDGF assembly INTERFACE FUNCTIONS The PDGF Assembly will :

C3.2 INTERFACE REQUIREMENTS

C3.2.1 FGB module INTERFACE REQUIREMENTS C3.2.1.1 ENVELOPEs

C3.2.1.1.1 EVA MAINTENANCE ENVELOPE

The FGB Module envelope shall provide the capability to EVA install and release the following:

The EVA maintenance envelope around the PDGF shall be as defined in Figure C3.2.1.1.1-1, EVA Maintenance Envelope.

FIGURE C3.2.1.1.1-1 EVA MAINTENANCE ENVELOPE

C3.2.1.1.2 FGB module SSRMS APPROACH ENVELOPE The FGB Module shall accommodate the SSRMS approach envelope around the PDGF for static mode of operation as defined in Figure C3.2.1.1.2-1, SSRMS LEE Approach Envelope (Static).

Notes:

STAYOUT ZONE

Approach Envelope (Conical) 87.49” (2222 mm) 37.5” (953 mm) 6” (152 mm) 40” (1016 mm)

FIGURE C3.2.1.1.2-1 SSRMS LEE APPROACH ENVELOPE (STATIC)

C3.2.1.2 reserved C3.2.1.3 Structural/mechanical interface

C3.2.1.3.1 FGB STRUCTURAL INTERFACES

The FGB Module and PDGF mounting structure shall meet all performance requirements while being subject to the loads as defined below.

C3.2.1.3.2 FGB module MECHANICAL INTERFACE The FGB Module shall provide accommodations for attachment of the PDGF Mounting Ring at the location specified below in Table C3.2.1.3.2-1, PDGF Mounting Ring Interface Location in conjunction with the figure shown in SSP 42121, U.S. On-Orbit Segment Pressurized Mating Adapter-1 to Russian Segment FGB ICD, Part 1, Appendix C, Figure C 3.1-1, EFGF To FGB On-Orbit Configuration.

TABLE C3.2.1.3.2-1 PDGF Mounting Ring interface location

Orientation shall be as shown in Figure C3.2.1.3.2-1 Sheets 1, 2, and 3.

FIGURE C3.2.1.3.2-1 PDGF ORIENTATION ON FGB MODULE (SHEET 1 of 3)

FIGURE C3.2.1.3.2-1 PDGF ORIENTATION ON FGB MODULE (SHEET 2 of 3)

FIGURE C3.2.1.3.2-1 PDGF ORIENTATION ON FGB MODULE (SHEET 3 of 3) The FGB Module shall accommodate eight mounting bolts and nut assemblies for attachment of the PDGF Mounting Ring, as specified in Figure C3.2.1.3.2-2, PDGF Mounting Ring Attachment Diagram.

FIGURE C3.2.1.3.2-2 PDGF MOUNTING RING ATTACHMENT DIAGRAM

The FGB to PDGF electrical bonding shall be through the Mounting Ring.

The FGB shall accommodate a ground strap from the PDGF Mounting Ring to the PDGF Stand.

C3.2.1.3.3 LOADS AND STIFFNESS

C3.2.1.3.3.1 FGB module IMPACT LOADS During grappling of the PDGF assembly by the SSRMS the impact load to the FGB Module shall be as defined in Figure C3.2.1.3.3.1-1, PDGF Assembly Impact Loads Diagram.

FIGURE C3.2.1.3.3.1-1 PDGF ASSEMBLY IMPACT LOADS DIAGRAM

C3.2.1.3.3.2 FGB module STIFFNESS REQUIREMENTS The minimum rotational stiffness required from the FGB Module (FGB hull and PDGF stand) at the PDGF to FGB Module interface surface with respect to the interface between the FGB and the Pressurized Mating Adapter (PMA) shall be:

(Coordinate system is defined in Figure C3.1.2-1, PDGF Assembly Coordinate System) C3.2.1.3.3.3 FGB PDGF Load Operations.

The FGB Module shall be capable of having the SSRMS utilized on the FGB PDGF for at least 10 complete operations. An operation is defined as the time from which the SSRMS has walked on and is mounted to the FGB PDGF, through the SSRMS activity, to the time at which the SSRMS has walked off the FGB PDGF back to the USOS.

The number of cycles for one SSRMS operation is specified in Table C3.2.1.3.3.3-1, SSRMS Load Cycles.

TABLE C3.2.1.3.3.3-1 SSRMS LOAD CYCLES

LOAD CYCLES

C3.2.1.3.4 FGB module ELECTRICAL INTERFACE HARDWARE The FGB Module shall provide the capability to tie down the PDGF Cable Harness and be mated with the PDGF Cable Harness connector.

At least 18 in (457 mm) of Cable Harness slack shall be maintained to permit EVA crew release of the PDGF Cable Harness from the FGB Module.

The FGB Module shall assure that Cable Harness restraints within 39 in (1 m) of the PDGF be EVA releasable and re-matable without using tools.

C3.2.1.3.5 fgb module ELECTRICAL CONNECTORS The U.S.-supplied electrical connectors for the FGB Module shall comply with the requirements of SSQ 21635, General Specifications for Connectors and Accessories, Electrical, Circular, Miniature, IVA/EVA Robot Compatible, Space Quality SSP 30256:001, Space Station Electrical Bonding Requirements and SSP 41162.

Only EVA compatible connectors shall be supplied by NASA/CSA and shall consist of the standard type for PDGF to PDGF Cable Harness interfaces. Russian supplied connectors for the PDGF Cable Harness interface shall comply with SSP 50094, NASA/RSA Joint Specification/Standards Document for the ISSA Russian Segment paragraphs 6.4.5.1, 6.4.5.2, and 6.4.5.3.

C3.2.1.4 electrical interface C3.2.1.4.1 fgb module ELECTRICAL interfaces For SSRMS base point operations, the FGB to PDGF Cable Harness electrical interfaces shall be as shown in Figure C3.1.1-2, FGB Module to PDGF Assembly Functional Interface Diagram for the FGB Module.

C3.2.1.4.2 FGB MODULE POWER SUPPLY

The FGB Module shall supply power to the PDGF Cable Harness through the power Circuits specified in Figure C3.1.1-2, FGB Module to PDGF Assembly Functional Interface Diagram, and Figure C3.2.1.4.2-1, FGB to PDGF Power Interface Diagram.

Note:

1. All payload lines must be demated during SSRMS walk-off to/from the FGB PDGF. RACU connections for MSS operations from the FGB PDGF will be defined in the applicable operational products.

FIGURE C3.2.1.4.2-1 fgb to pdgf power interface diagram

C3.2.1.4.2.1 FGB MODULE POWER QUALITY

The FGB Module interface power quality shall be in accordance with SSP 42121, Part 1, Appendix B, paragraph B.3.2.2.1.1.

C3.2.1.4.2.2 FAULT PROTECTION

The FGB Module shall provide protection as follows:

C3.2.1.5 Command and data handling (C&dh) interface There are two functionally identical EVA installed MIL-STD-1553 Data Cables to be installed Intravehicular Activity (IVA): one Node 3 to FGB PDGF 1553 Data Cable (Channel A) and one Node 3 to FGV 1553 Data Cable (Channel B).

The Channel A cable is designated as the primary cable; the Channel B cable is designated as the secondary cable. Each cable is externally routed from the appropriate jumper connector located on Node 3 to the FGB PDGF where each cable is mated to the corresponding FGB PDGF harness connector. The data interface with EVA connectors is shown in Figure C3.2.1.5*1, FGB PDGF To NODE 3 PVGF Data Connector Diagram. Connector parameters are shown in Table C3.2.1.5-1, Data Bus Connectors.

The FGB will support the following functions at the interface to the MIL-STD-1553 drag-through cables: a) structural/mechanical attachment, and b) data signal transfer. The drag-through cable connectors will support the following functions at the interface to the FGB MIL-STD-1553 cable connectors: a) structural / mechanical attachment, and b) data signal transfer.

FIGURE C3.2.1.5-1 FGB PDGF TO NODE 3 PVGF DATA CONNECTOR DIAGRAM

TABLE C3.2.1.5-1 DATA BUSS CONNECTORS

33У.5534.017

33У.5534.016

33У.5534.016

33У.5534.016

C3.2.1.5.1 Deleted C3.2.1.5.2 Deleted C3.2.1.5.2.1 Deleted C3.2.1.5.2.1.1 Deleted C3.2.1.5.2.1.2 Deleted C3.2.1.5.2.2 Deleted C3.2.1.5.2.3 Deleted C3.2.1.6 Thermal C3.2.1.6.1 FGB MODULE Passive Thermal Control Interface Requirements The temperature of the FGB Module (PDGF Stand) shall be maintained between – 94 degrees F to +145.4 degrees F (–70 degrees C to +63 degrees C).

For design purposes the FGB shall assume the contact conductance at the FGB to PDGF interface to be a maximum of 3.0 Watts/C.

C3.2.1.7 ENVIRONMENTS

C3.2.1.7.1 fgb module ELECTROMAGNETIC COMPATIBILITY The FGB Module side of the interface shall meet the requirements of SSP 50094, paragraph 3.4.

C3.2.1.7.2 FGB MODULE GROUNDING

The FGB Module side of the interface shall meet the requirements of SSP 50094, paragraphs 3.4.7.3, 3.4.7.4, 3.4.8, and 6.5.1.1.

C3.2.1.7.3 fgb module electrical BONDING The FGB Module side of the interface shall meet the requirements of SSP 50094, paragraphs 3.4.8.1 and 6.5.1.2.

The electrical bond path shall be continuous from the FGB to PDGF mounting ring interface plane.

C3.2.1.7.4 FGB MODULE CABLE AND WIRE DESIGN

The FGB Module side of the interface shall meet the requirements of SSP 50094, paragraph 4.3.4.6.3.

Termination length shall be as short as possible and shall not exceed 15.75 inches (400 mm).

C3.2.1.7.5 fgb module ELECTROSTATIC DISCHARGE The FGB Module side of the interface shall meet the requirements of SSP 50094, paragraphs 3.4.7.4, 6.5.1.2, and 6.5.1.9.

C3.2.1.7.6 fgb module CORONA The FGB Module side of the interface shall meet the requirements of SSP 50094, paragraph 3.4.9.

C3.2.1.8 eva interface

C3-17

C3.2.1.8.1 FGB module EVA INTERFACES The EVA requirements for FGB Module shall be in accordance with SSP 41163, as well as, Sections A3.2.1 (PDGF interface requirements), A3.2.2.7 (unique EVA constraints) and D3.2.1.5 (VSC interface requirements) of this document for supplements to the specific requirements listed below.

C3.2.1.8.2 Translation Paths For FGB/PDGF assembly EVA tasks, several translation paths shall be selectable. The crew may be carried by the U.S. segment’s robotic arm between the joint airlock and the FGB Module worksite. As a alternative path, handrails on the joint Airlock, Node 1, PMA 1 and the FGB Module may also be used. If the Russian docking compartment airlock is used, translation along the Russian cargo crane is also a possibility.

Translation along the length of the U.S. segment’s arm shall only be used as a backup path if no other method is possible. The handrail translation path between PMA- 1 and the FGB Module is shown in Figure C3.2.1.8.2-1, EVA Translation Path Diagram.

FIGURE C3.2.1.8.2-1 EVA TRANSLATION PATH DIAGRAM

C3.2.1.8.3 Worksite Clearance The FGB Module and PDGF assembly mechanical and electrical EVA interfaces are shown in Figures C3.2.1.8.3-1, FGB Module PDGF Interface Diagram, C3.2.1.8.3-2, FGB Module-PDGF Interface Diagram (Continued), C3.2.1.8.3-3, PDGF Mounting Ring EVA Interface Diagram, C3.2.1.8.3-4, PDGF Mounting Ring EVA Interface Diagram (Continued), C3.2.1.8.3-5, PDGF Cable Harness EVA Interface Diagram, C3.2.1.8.3-6 PDGF Grapple Pin Interface Diagram. Clearances for these interfaces shall be maintained to ensure safe crew return to the airlock and successful manual mating of the PDGF assembly components to the FGB Module.

FIGURE C3.2.1.8.3-1 FGB MODULE PDGF INTERFACE DIAGRAM

FIGURE C3.2.1.8.3-2 FGB MODULE - PDGF INTERFACE DIAGRAM (CONTINUED)

FIGURE C3.2.1.8.3-3 PDGF MOUNTING RING EVA INTERFACE DIAGRAM

FIGURE C3.2.1.8.3-4 PDGF MOUNTING RING EVA INTERFACE DIAGRAM (CONTINUED)

FIGURE C3.2.1.8.3-5 PDGF CABLE HARNESS EVA INTERFACE DIAGRAM

FIGURE C3.2.1.8.3-6 PDGF GRAPPLE PIN INTERFACE DIAGRAM

C3.2.1.8.4 TOOL RESPONSIBILITIES

Jointly approved U.S. and Russian EVA support equipment shall be used for functional assurance.

NASA shall provide its own tools and support equipment as Government Furnished Equipment (GFE) to perform the identified task responsibilities.

Russia shall maintain clearances to operate these tools. Since NASA tools shall always be tethered to the U.S. EVA crewmembers, there is no need for special tool restraint provisions at any FGB worksite.

Tool use shall be minimized for nominal on-orbit assembly, disassembly and maintenance. To aid RSC-E design and assure NASA tool access, the following significant tools are identified for possible U.S. task in Table C3.2.1.8.4-1, Tool Usage. Each item is further described in Figure C3.2.1.8.4-1, FGB PDGF EVA Tools.

FIGURE C3.2.1.8.4-1 FGB PDGF EVA TOOLS

TABLE C3.2.1.8.4-1 Tool Usage

C3.2.1.8.5 RESERVED

C3.2.1.8.6 EVA HANDLING CONSTRAINTS FOR THE PDGF STAND ASSEMBLY AND THE COMBINED PDGF/STAND

C3.2.1.8.7 EVA loads for the PDGF stand

C3.2.1.8.8 RESERVED

C3.2.1.8.9 EVA features of electrical connectors and cables The following requirements shall apply:

C3.2.2 PDGF Assembly INTERFACE REQUIREMENTS The PDGF Assembly is standard ISS provided hardware that is verified by existing ISS specifications and ICDs. Therefore, PDGF design requirements will not be shown herein, with the following exceptions that will be documented:

C3.2.2.1 RESERVED

C3.2.2.1.1 rESERVED C3.2.2.2 PDGF Structural/mechanical interface

C3.2.2.2.1 PDGF ASSEMBLY MECHANICAL INTERFACE

The mechanical interface between the PDGF Assembly and the FGB shall be provided by the PDGF Mounting Ring and mounting bolts.

The PDGF Mounting Ring shall accommodate holes for eight (8) FGB mounting bolts as specified in Figure C3.2.2.2.1-1, PDGF Mounting Ring Attachment.

FIGURE C3.2.2.2.1-1 PDGF MOUNTING RING ATTACHMENT

The PDGF Assembly electrical bonding shall be through the PDGF mounting ring to the FGB.

The PDGF ORU-to-PDGF mounting ring bolts shall comply with the EVA requirements documented in SSP 41162 and SSP 30256:001.

C3.2.2.2.2 RESERVED

C3.2.2.2.3 RESERVED

C3.2.2.2.4 RESERVED

C3.2.2.2.5 PDGF CABLE HARNESS RESTRAINTS

The PDGF Cable Harness shall provide the capability to be tied down on the FGB and be mated with the FGB connectors.

Up to 18 in (457 mm) of Cable Harness slack shall be maintained to permit EVA crew release of the PDGF Cable Harness from the FGB.

In addition, the Cable Harness restraints within 39 in (1 m) of the PDGF shall be EVA releasable and re-matable without using tools.

C3.2.2.3 ELECTRICAL INTERFACE

The PDGF shall receive two (2) power output circuits and two (2) fault current circuits at the FGB interface in accordance with Figure C 3.1.1-2, FGB Module to PDGF Assembly Functional Interface Diagram. The power outputs will be identified as FGB-A Power (SSRMS Power) and FGB-B Power, each with a positive and return. The fault current returns will be identified as FGB-A cable fault return and FGB-B cable fault return.

C3.2.2.3.1 PDGF assembly electrical interfaces The electrical interfaces between the PDGF and the PDGF Cable Harness shall be as shown in Figure C3.2.2.3.1-1, PDGF To PDGF Cable Harness Electrical Interfaces/Wiring Diagram.

PAYLOAD POWER

(REDUNDANT)

PAYLOAD POWER

(PRIME)

FIGURE C3.2.2.3.1-1 PDGF to PDGF CABLE HARNESS ELECTRICAL INTERFACES/WIRING DIAGRAM

C3.2.2.3.2 INTERFACE POWER QUALITY

C3.2.2.3.2.1 INRUSH CURRENT

The inrush current of each power input shall not exceed 20 amperes and be less than or equal to the operating current within 50 ms.

C3.2.2.3.2.2 MAXIMUM LOAD CHANGE

The maximum load change for each power input shall not exceed 500 watts with a slew rate of not more than 175 A/ms.

C3.2.2.3.3 FAULT CURRENT RETURN

The fault current return shall be connected to chassis on the PDGF side of the interface.

C3.2.2.3.4 RETURN GROUNDING

Each power output return shall be referenced to chassis at a single point.

C3.2.2.4 Reserved

C3.2.2.5 THERMAL INTERFACES

C3.2.2.5.1 PDGF PASSIVE THERMAL CONTROL INTERFACE REQUIREMENTS

C3.2.2.5.1.1 Maximum PDGF TOUCH TEMPERATURE LIMITS The PDGF design shall accommodate a touch temperature range as follows:

C3.2.2.5.1.2 PDGF Temperature Limits The PDGF operational temperature limits are –94 degrees F to +194 degrees F (–70 degrees C to +90 degrees C). The PDGF non-operational temperature limits are –251 degrees F to +250 degrees F (–157 degrees C to +121 degrees C). The PDGF temperature limits for grappling operations are –94 degrees F to +194 degrees F (–70 degrees C to +90 degrees C) according to PDGF Specification SPSR-SS-SG-0800, Table 3.2.1.2-1.

C3.2.2.5.2 Maximum PDGF To FGB Thermal Conductance The PDGF shall accommodate a maximum thermal conductance to the FGB of 3.0W/degrees C.

C3.2.2.6 ENVIRONMENTS

C3.2.2.6.1 pdgf assembly ELECTROMAGNETIC COMPATIBILITY The PDGF assembly side of the interface shall meet the requirements of SSP 30243, Space Station Requirements for Electromagnetic Compatibility.

C3.2.2.6.2 pdgf assembly GROUNDING The PDGF assembly side of the interface shall meet the requirements of SSP 30240, Space Station Grounding Requirements.

C3.2.2.6.3 pdgf assembly ELECTRICAL BONDING The PDGF assembly side of the interface shall meet the requirements of SSP 30245, Space Station Electrical Bonding Requirements.

Bonding provisions at the interface shall satisfy a Class H and R bond in accordance with the above reference document.

C3.2.2.6.4 pdgf assembly CABLE AND WIRE DESIGN The PDGF assembly side of the interface shall meet the requirements of SSP 30242, Space Station Cable/Wire Design and Control Requirements for Electromagnetic Compatibility.

At the interface the U.S. shields shall be terminated to structure.

C3.2.2.6.5 pdgf assembly ELECTROSTATIC DISCHARGE The PDGF assembly side of the interface shall meet the requirements of SSP 30243.

C3.2.2.6.6 pdgf assembly CORONA The PDGF assembly side of the interface shall meet the requirements of SSP 30243.

C3.2.2.6.7 RS REQUIREMENTS ON PDGF MOUNTING RING FOR LAUNCH ON PROGRESS VEHICLE

C3.2.2.6.7.1 PDGF MOUNTING RING QUASI-STATIC LOADS

The PDGF Mounting Ring shall meet all performance requirements while being subject to the quasi-static pre-processing and launch loads as defined in Table C3.2.2.6.7.1-1.

TABLE C3.2.2.6.7.1-1 Quasi-static Ground and Launch Loads

C3.2.2.6.7.2 PDGF MOUNTING RING HARMONIC LOADS

The PDGF Mounting Ring shall meet all performance requirements while being subject to the harmonic launch loads as defined in Table C3.2.2.6.7.2-1, Sine Wave Launch Vibration.

TABLE C3.2.2.6.7.2-1 Sine Wave Launch Vibration

C3.2.2.6.7.3 PDGF MOUNTING RING RANDOM VIBRATIONS LOADS

The PDGF Mounting Ring shall meet all performance requirements while being subject to the random vibrations as defined in Table C3.2.2.6.7.3-1, Random Vibration Loads.

TABLE C3.2.2.6.7.3-1 Random Vibration Loads

C3.2.2.6.7.4 PDGF MOUNTING RING LAUNCH SHOCK LOADS

The PDGF Mounting Ring shall meet all performance requirements while being subject to the launch shock loads as specified below:

C3.2.2.6.8 PDGF MOUNTING RING THERMAL CONDITIONS

The PDGF Mounting Ring shall meet all performance requirements while being subject to thermal conditions as specified below:

C3.2.2.6.9 PDGF MOUNTING RING ENVIRONMENTAL CONDITIONS

The PDGF Mounting Ring shall meet all performance requirements while being subject to environmental conditions as specified below:

Humidity, Percent

On-orbit Flight/pressurized Compartment

C3.2.2.6.10 PDGF MOUNTING RING RADIATION REQUIREMENTS

The PDGF Mounting Ring shall meet all performance requirements while being subject to the radiation requirements per SSP 41162.

C4.0 interface quality assurance provisions Section C4 of this ICD defines and documents the interface verification process criteria between NASA and RSA for verifying the interface between the PDGF and the FGB. This criteria is documented in Table C4.0-1, PDGF To FGB Interface Verification Table, which consists of the interface requirements defined in Section C3.2.1, FGB Module Interface Requirements, the general NASA/RSA methods for Joint Verification performance, the RSA verification requirements for individual verification performance, and the assignment of individual verification performance responsibility between NASA and RSA.

The interface verification approach between NASA and RSA shall be accomplished in accordance with SSP 50101, NASA-RSA Phase 2-3 Bi-lateral Integration Verification Plan.

Unless otherwise specified, RSA and NASA will be responsible for the performance of all FGB to PDGF Joint Verification activities in this ICD.

C4.1 Verification methods Definitions of the methods used for verifying PDGF to FGB joint interface requirements are documented in SSP 50101, Section 4.3.

C4.2 Interface verification process Joint Verification Requirements between the FGB and PDGF shall be as defined and documented in this ICD, Paragraph C4.3.2, Verification of Interface Requirements. To obtain further explanation of the Joint Verification Process between NASA and RSA, see SSP 50101, Section 4.1.3.

NASA non-joint Interface Verification requirements are documented in hardware specifications and are crossed referenced in the Interface Verification Visibility Report between the interface requirements documented in Section C3.2 and the applicable NASA Specifications. The interface verification requirements will be identified in paragraph C4.3.2.1, Verification of FGB Module Interface Requirements as Non-Joint Verification.

RSA non-Joint Verification requirements are documented in Table C4.0-1, PDGF to FGB Interface Verification, and will be referenced in Section C4.3.2.2, Verification of PDGF Assemby Interface Requirements as Non-Joint Verification.

C4.2.1 verification responsibility Unless otherwise specified, RSA and NASA will be responsible for the performance of all FGB to PDGF Joint Verification activities in this ICD.

C4.3 INTERFACE QUALITY CONFORMANCE VERIFICATIONS

C4.3.1 INTERFACE VERIFICATION CHARACTERISTICS

Joint interface verification requirements between the FGB and PDGF will consist of a verification method, a verification objective and verification success criteria.

C4.3.2 verification of interface requirements C4.3.2.1 verification of fgb module interface requirements C4.3.2.1.1 verification of envelopes C4.3.2.1.1.1 verification of fgb module eva envelope See Table C4.0-1, PDGF To FGB Interface Verification Table.

C4.3.2.1.1.2 Verification of fgb module ssrms approach envelope See Table C4.0-1, PDGF To FGB Interface Verification Table.

C4.3.2.1.2 reserved C4.3.2.1.3 verification of structural/mechanical interface C4.3.2.1.3.1 verification of fgb structural interfaces See Table C4.0-1, PDGF To FGB Interface Verification Table.

C4.3.2.1.3.2 verification of fgb module mechanical interface See Table C4.0-1, PDGF To FGB Interface Verification Table.

C4.3.2.1.3.3 VERIFICATION OF LOADS AND STIFFNESS

C4.3.2.1.3.3.1 verification of FGB MODULE IMPACT loads See Table C4.0-1, PDGF To FGB Interface Verification Table.

C4.3.2.1.3.3.2 verification of fgb module stiffness requirements See Table C4.0-1, PDGF To FGB Interface Verification Table.

C4.3.2.1.3.3.3 verification of fgb pdgf load OPERATIONS Non Joint Verification; See Table C4.0-1,, PDGF To FGB Interface Verification Table.

C4.3.2.1.3.4 VERIFICATION OF FGB MODULE ELECTRICAL INTERFACE HARDWARE

Joint Verification: See Table C4.0-1, PDGF To FGB Interface Verification Table.

C4.3.2.1.3.5 VERIFICATION OF FGB MODULE ELECTRICAL CONNECTORS

Joint Verification: See Table C4.0-1, PDGF To FGB Interface Verification Table.

C4.3.2.1.4 verification of electrical interface C4.3.2.1.4.1 verification of fgb module electrical interfaces See Table C4.0-1, PDGF To FGB Interface Verification Table.

C4.3.2.1.4.2 verification of fgb module power supply Joint Verification: See Table C4.0-1, PDGF To FGB Interface Verification Table.

C4.3.2.1.4.2.1 verification of fgb module power quality Joint Verification: See Table C4.0-1, PDGF To FGB Interface Verification Table.

C4.3.2.1.4.2.2 VERIFICATION OF FAULT PROTECTION

Non Joint Verification: See Table Table C4.0-1, PDGF To FGB Interface Verification Table.

C4.3.2.1.5 Reserved C4.3.2.1.6 verification of thermal interfaces C4.3.2.1.6.1 verification of fgb passive thermal control interface requirements Non-Joint Verification: See Table C4.0-1, PDGF To FGB Interface Verification Table.

C4.3.2.1.7 verification of environments C4.3.2.1.7.1 verification of fgb module electromagnetic compatibility Non-Joint Verification: See Table C4.0-1, PDGF To FGB…