SSP_50128-C3.doc

SSP-50128C3

SSP 50128 Revision C3 May 31, 2000

SPECIFICATION

OF TECHNICAL REQUIREMENTS

FOR

FGB FUNCTIONAL CARGO BLOCK

September 4, 1997 plus

Approved Changes:

FGB 30, 125A, 126B, 127, 128A, 129, 132C, 134B, 135A, 136B, 137, 138A, 140A, 141, 145, 147, 148, 149A, 150, 153, 139E, 142A, 143C, 144C, 151A, 152, 154B, 155, 156A, 157B, 158, 160, 161, 162, 163, 165, 166, 167A, 168, 169E, 170A, 171F, 172, & 173A

May 31, 2000

FOR

THE M. V. KHRUNICHEV

STATE RESEARCH AND PRODUCTION SPACE CENTER

RUSSIA

121309 MOSCOW NOVOZAVODSKAJA STREET, 18

REVISION AND HISTORY PAGE

A

B

C

C1

Initial release (SSCBD 000038 R1, EFF. 7-18-95)

Revision A (SSCD 000038, EFF. 08-26-95)

SCN 001 incorporates ECP 219 (Release to File)

(Released for Tracking purposes only. Overcome by Revision B.)

Revision B incorporates ECP 102, ECP 162, ECP 239, ECP 241, ECP 245, ECP 257, ECP 271, ECP 300, and ECP 285.

The FGB Specification changes of ECP 162 and ECP 300 are processed as part of ECP 285.

(FGB Change Form Numbers 1, 2, 3, 4, 5, 6A, 7, 8, 9A, 10, 11, 12, 13, 15, 19, 20, 21, 22, 23A, 24B, 25, 26A, 28A, 29, 32, 36, 37, 38, 39, 40, 41, 42, 45, 46, 48A, 49A, 50A, 51, 52, 53A, 54, 55, 56, 57, 59, 60, 61C, 62, 64, 65, 66, 67, 68A, 69B, and 71)

The following SCN numbers have been cancelled. The SCNs were never created and will never be released. The reason for these cancellations is because the content of the SSCNs have been incorporated into Revision C.

SCN 003 (SSCN 303)

SCN 004 (SSCN 407)

SCN 005 (SSCN 420)

SCN 006 (SSCN 512)

Revision C, Final Document (SSCD 000832, EFF. xx/xx/xx) incorporates the following changes. SSCNs 303, 407, 420, 512, and 832.

(FGB Change Form Numbers 33L, 70D, 72, 73B, 76, 77A, 78B, 80, 81, 85, 86D, 89A, 90, 91, 94B, 95, 96, 97, 98, 99B, 100A, 101A, 102B, 103, 104, 105A, 107A, 108, 109A, 110B, 112, 113, 114, 115B, 116B, 117, 118, 119, 120B, 121, 122C, 123, 124A.

The following SCN number has been cancelled. The SCN was never created and will never be released. The reason for this cancellation is because the content of the SSCN has been incorporated into July 31, 1998 Revision C1 update.

SCN 007 (SSCN 000253)

Due to International agreement the following revision supersedes the previous Revision C.

July 31, 1998 Revision C1 update, Final Document (SSCD 001402, EFF. xx/xx/xx) incorporates the following changes:

SCN 007 (SSCN 000253)

(FGB Change Form Numbers FGB 30, 125A, 126B, 127, 128A, 129, 132C, 134B, 135A, 136B, 137, 138A, 140A, 141, 145, 147, 148, 149A, 150, and 153.

10-19-95

10-19-95

12-11-96

02-20-97

07-20-98

11-11-99

REVISION AND HISTORY PAGE

C2

C3

The following SCN numbers have been cancelled. The SCNs were never created and will never be released. The reason for this cancellation is because the content of the SSCN has been incorporated into the October 15, 1998 Revision C2 update.

SCN 008 (SSCN 000929)

SCN 009 (SSCN 001293)

SCN 010 (SSCN 001342)

SCN 011 (SSCN 001579)

SCN 012 (SSCN 001403)

SCN 013 (SSCN 001465)

SCN 014 (SSCN 001555)

SCN 015 (SSCN 001746)

SCN 016 (SSCN 001787)

The following SCN was cancelled prior to Revision B. The SCN was never created and will never be used. The reason for these cancellations is because the content of the SSCN was incorporated into August 8, 1996 Revision B. Due to the fact that the SSCN was incorporated at that time in Revision B but never documented on the Revision and History page in Revision B this information is being noted with Revision C2.

SCN 002 (SSCN 000316)

Due to International agreement the following revision supersedes the previous Revision C1.

October 15, 1998 Revision C2 update, Final Document (SSCD 001717, EFF. 10-15-98) incorporates the following changes: SSCNs 000929, 001293, 001342, 001579, 001403, 001465, 001555, 001746, 001787, and 001717.

The following SCN numbers have been cancelled. The SCNs were never created and will never be released. The reason for this cancellation is because the content of the SSCN has been incorporated into the May 31, 2000 Revision C3 update.

SCN 017 (SSCN 001821)

SCN 018 (SSCN 002321)

SCN 019 (SSCN 002830)

Due to International agreement the following revision supersedes the previous C2.

May 31, 2000 Revision C3 update, Final Document (SSCD 004510, EFF. 12-03-01) incorporates the following changes:

SSCNs 001821, 002321, 002830 and 004510.

(FGB Change Form Numbers FGB 167A, 168, 169E, 170A, 171F, 172 & 173A.)

SCN 020 (SSCN 003828, EFF. 08/20/01)

04-12-02

04-12-02

NASA ERU Release: 03/16/09

ERU: /s/ M. Hehn 04-12-02

PREFACE

SSP 50128 (Specification of Technical Requirements for the FGB) equally applies to NASA, Boeing, Khrunichev, and RSC-Energia. This document is under the control of the Space Station Control Board (SSCB). Any changes or revisions must be approved by the SSCB and Khrunichev.

Program Manager Date

International Space Station Alpha

INTERNATIONAL SPACE STATION ALPHA PROGRAM

SPECIFICATION OF TECHNICAL REQUIREMENTS FOR THE FGB

4 September 1997

APPROVALS

_\s\ Sergei Shaevich__________ ______11.09.97_ Program Director, Khrunichev Center

DATE

Program Manager, Boeing

DATE

Sergei Shaevich______________________ __Doug Stone___________________

PRINT NAME

SPECIFICATION OF TECHNICAL REQUIREMENTS FOR THE FGB

4 September 1997

TECHNICAL CONCURRENCE

\s\ Leonid Gorshkov______ 3.10.97

LP/S RIPT Manager, NASA

DATE

Head of Department, Space Station Design

RSC-Energia

Mark Geyer________________ Leonid Gorshkov____________

\s\_Doug Drewry_______________9-11-97____ \ s\_Eduard Radchenko_ _________11.9.97

FGB IPT Manager, NASA

DATE

FGB, Design Bureau Salyut

DATE

Doug Drewry_______________

Eduard Radchenko___________

PRINT NAME

PRINT NAME

\s\_Michael Wood 9.11.97________

\s\__Sergei Pougachenko______ 9.11.97 FGB Manager, Boeing

DATE

FGB Project Director DATE

Michael Wood______________

Sergei Pougachenko

SPECIFICATION OF TECHNICAL REQUIREMENTS FOR THE FGB

4 September 1997

CONCURRENCE

PREPARED BY:

_________Roy Norris______ _2-6910__

ORGN

__\s\ Roy Norris_______________________ 9/5/97___

SIGNATURE

PREPARED BY:

_________Andrei Tarasov_____ _Khrunichev___

__\s\ Andrei Tarasov________________________ __ 11/9/97____

CHECKED BY:

_________A. Bishop___________

___\s\ Al Bishop________________________ 9-10-97___

CHECKED BY (NASA):

_________ _Chau Hong___

_______OB___

____\s\ Chau Hong______________________ 9/12/97__

SUPERVISED BY (BOEING)

________Greg Deiter______ ______2-6600__

DQA:

_________Adam Burkey_________ _______2-6910__

__/s/ Adam Burkey__________________ _____07-10-01

INTERNATIONAL SPACE STATION ALPHA PROGRAM

SPECIFICATION OF TECHNICAL REQUIREMENTS FOR THE FGB

LIST OF CHANGES

4 September 1997

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

SSCBD

ENTRY DATE

PARAGRAPH

TITLE

All.

TABLES(S)

FIGURE(S)S

APPENDIX(ES)

ADDENDA

Not applicable.

Table of Contents 11.0

SCOPE

1.1 FGB Overview 1.2 Notations Used in This Document 1.3 Notes Concerning FGB Configuration 2.0

APPLICABLE

2.1 Reference Documents 2.2 Precedence 3.0

REQUIREMENTS

3.1 FGB Definition (RSS 3.7.1.2) 3.1.1 Interface Definition 3.1.1.1 FGB Diagrams 3.1.1.2 Physical Interface 3.1.2 FGB Constraints (Derived from RSS 3.3.12.8)

j. Mass Constraints

3.1.3 Major Component List 3.2 Characteristics 3.2.1 Performance Characteristics (RSS 3.7.1.2) 3.2.1.1 Control Total Atmosphere 3.2.1.1.1 Monitor Total Pressure (RSS 3.7.1.3.1.1) 3.2.1.1.2 Monitor Oxygen Partial Pressure (RSS 3.7.1.3.2.1) 3.2.1.1.3 Monitor Carbon Dioxide (RSS 3.7.1.3.25.1) 3.2.1.1.4 Remove Airborne Particulate Contaminants (RSS 3.7.1.3.26.1) 3.2.1.1.5 Equalize Pressure (RSS 3.7.1.3.4)

3.2.1.1.6 FGB to PMA1 Leak Seal Monitoring and repressurization (RSS 3.7.1.3.3) 3.2.1.2 Condition Atmosphere 3.2.1.2.1 Monitor Atmosphere Temperature (RSS 3.7.1.3.4.1.1) 3.2.1.2.2 Remove Atmosphere Heat (RSS 3.7.1.3.4.1.2) 3.2.1.2.3 Monitor Humidity (RSS 3.7.1.3.4.2.1) 3.2.1.2.4 Circulate Atmosphere Intramodule (RSS 3.7.1.3.5.1) 3.2.1.2.5 Circulate Atmosphere Inter-module (RSS 3.7.1.3.5.2) 3.2.1.3 Maintain Thermal Conditioning 3.2.1.3.1 Collect Thermal Energy (RSS 3.7.1.3.22.1) 3.2.1.3.2 Transmit Thermal Energy (RSS 3.7.1.3.22.2) 3.2.1.3.3 Dispose of Thermal Energy (RSS 3.7.1.3.22.3) 3.2.1.3.4 Passive Thermal Energy (RSS 3.7.1.3.22.4) 3.2.1.4 Provide Electrical Power 3.2.1.4.1 Generate Power (Derived from RSS 3.7.1.3.20.1) 3.2.1.4.2 Distribute Power (Derived from RSS 3.7.1.3.20.2) 3.2.1.4.3 Store Energy (RSS 3.7.1.3.20.3) 3.2.1.5 Lighting of Interior Areas 3.2.1.5.1 Control Internal Lighting (RSS 3.7.1.3.40.1) 3.2.1.5.2 Illuminate Internal Areas (RSS 3.7.1.3.40.2) 3.2.1.6 Monitor System Status 3.2.1.6.1 Collect Function Status Data (RSS 3.7.1.3.13.1) 3.2.1.6.2 Assess Function Status Data (RSS 3.7.1.3.14) 3.2.1.6.3 Provide Docking Status (RSS 3.7.1.3.45) 3.2.1.7 FGB Functions 3.2.1.7.1 FGB Function Activation 3.2.1.8 Distribute Time (RSS 3.7.1.3.11) 3.2.1.9 Provide Voice Communications 3.2.1.9.1 Transmit Hardwire (RSS 3.7.1.3.28.1) 3.2.1.9.2 Receive Hardwire (RSS 3.7.1.3.29.1) 3.2.1.10 Provide Visual Access 3.2.1.10.1 Transmit Video Signal (RSS 3.7.1.3.27.1) 3.2.1.10.2 Receive Video Signal (RSS 3.7.1.3.27.2) 3.2.1.10.3 FGB Video Transmission (RSS 3.7.1.3.47) 3.2.1.11 Provide Link With Ground Stations 3.2.1.11.1.1 Receive Uplinked Data (RSS 3.7.1.3.30.1) 3.2.1.11.1.2 Prepare Uplinked Data for On-board Distribution (RSS 3.7.1.3.30.2) 3.2.1.11.1.3 Distribute Uplinked Data (RSS 3.7.1.3.30.3) 3.2.1.11.2.1 Prepare Data for Downlink (RSS 3.7.1.3.31.1) 3.2.1.11.2.2 Transmit Data for Downlink (RSS 3.7.1.3.31.2) 3.2.1.12 Respond to Loss of Function 3.2.1.12.1 Isolate to Recovery Level (RSS 3.7.1.3.6) 3.2.1.12.2 Recover Lost Function (RSS 3.7.1.3.7) 3.2.1.12.3 Safe (RSS 3.7.1.3.8) 3.2.1.13 Respond to Emergency Conditions 3.2.1.13.1 Respond to Fire (RSS 3.7.1.3.17) 3.2.1.13.1.1 Reserved 3.2.1.13.2 Detect Fire Event (RSS 3.7.1.3.17.1) 3.2.1.13.3 Isolate Fire Control Zone (RSS 3.7.1.3.17.2) 3.2.1.13.4 Extinguish Fire (RSS 3.7.1.3.17.3) 3.2.1.13.5 Recover from Fire (RSS 3.7.1.3.17.4) 3.2.1.13.6 Respond to Hazardous Atmosphere (RSS 3.7.1.3.19) 3.2.1.14 Execute Translation Maneuvers 3.2.1.14.1 Execute Maneuver Guidance (RSS 3.7.1.3.36) 3.2.1.14.2 Execute Translational Thrust (RSS 3.7.1.3.37) 3.2.1.14.3 Control Attitude - Propulsive (RSS 3.7.1.3.38)

3.2.1.14.3.1. Control Attitude Propulsively in the Configurations indicated in Table 3-VIII

(RSS 3.7.1.3.38.1)

3.2.1.14.3.2.

Indicate Status of Motion Control System (RSS 3.7.1.3.38.2) 3.2.1.15 Support Microgravity Operations 3.2.1.15.1 Limit Accelerations (RSS 3.7.1.3.39) 3.2.1.16 Support Flight Crew 3.2.1.16.1 Support Internal Crew Restraint and Mobility (RSS 3.7.1.3.24) 3.2.1.16.2 Support Housekeeping (RSS 3.7.1.3.41) 3.2.1.17 Support Internal Equipment Manipulation and Maintenance 3.2.1.17.1 Support Internal Equipment Translation (RSS 3.7.1.3.32) 3.2.1.17.2 Support Internal Equipment Removal and Replacement (RSS 3.7.1.3.33) 3.2.1.17.3 Support Internal Equipment Identification (RSS 3.7.1.3.34) 3.2.1.17.4 Support Internal Equipment Restraint (RSS 3.7.1.3.35) 3.2.1.17.5 Support Orbital Replacement Unit Repair (RSS 3.7.1.3.43) 3.2.1.17.6 Store Internal Equipment (RSS 3.7.1.3.42) 3.2.1.18 Support Crew Control Interface 3.2.1.18.1 Provide Data to Crew (RSS 3.7.1.3.12) 3.2.1.18.2 Provide Crew Control Interface (RSS 3.7.1.3.15 3.2.1.19 FGB / Service Module Manual Docking (RSA requirement) 3.2.1.21 Automatic Power reduction (RSS 3.7.1.3.48) 3.2.2.1 Mass Properties 3.2.2.1.1 Mass 3.2.2.1.2 Center of Gravity 3.2.2.1.3 Mass Moments of Inertial 3.2.2.2 Dimensions 3.2.2.3 Structural Design Constraint 3.2.2.4 Interfaces 3.2.2.4.1 FGB to RS Interface 3.2.2.4.2 FGB to USOS Interface (RSS 3.1.5.1.1) 3.2.2.4.3 Docking Targets 3.2.2.4.4 FGB to ICM Interface 3.2.2.5 FGB PDGF Support Interfaces (RSA Requirement) 3.2.2.6 Safety 3.2.2.6.1 Reserved 3.2.2.6.2 Reserved 3.2.2.6.3 Reserved 3.2.2.6.4 Support Flight Crew 3.2.2.6.4.1 Tools (derived from RSS 3.2.4.1.2) 3.2.2.7 Approach and Departure Corridor 3.2.2.7.1 NADIR Docking Port (-Y) (RSS 3.2.2.1) 3.2.2.7.2 Forward Docking Port (-X) (RSS 3.2.2.1) 3.2.2.7.3 AFT Docking Port (+X) 3.2.2.8 MDM Interface 3.2.2.9 Distribute commands and data (RSS 3.2.2.7, 3.7.1.3.38b(3) ) 3.2.3 Reliability 3.2.3.1 Failure Tolerance (RSS 3.2.3.1) 3.2.3.2 Failure Propagation (derived from RSS 3.2.3.3) 3.2.3.3 Service Life (derived from RSS 3.2.3.2) 3.2.3.4 FGB MCS Lifetime (derived from RSS 3.2.3.2) 3.2.3.5 Redundancy Status (RSS 3.2.3.4) 3.2.4 Maintainability 3.2.4.1 Qualitative Maintainability Requirements (RSS 3.2.4.1) 3.2.4.1.1 Design for Maintainability (RSS 3.2.4.1) 3.2.4.2 Quantitative Maintainability Requirements (RSS 3.2.4.2) 3.2.4.2.1 Equipment Maintenance Time in Nonpressurized Areas (RSS 3.2.4.2.1) 3.2.4.2.2 Total Mean Maintenance Crew Hours/Year (TMMCH/Y) (RSS 3.2.4.2.2, 3.2.4.2.2.1, 3.2.4.2.2.2, 3.2.4.2.2.2.1, 3.2.4.2.3) 3.2.4.2.3 Reserved 3.2.4.3 Failure Detection, Isolation, and Recovery (FDIR) (RSS 3.2.4.3) 3.2.4.3.1 Manual Control of FDIR (derived from RSS 3.2.4.3.1) 3.2.4.3.2 Testing at Operating Location (RSS 3.2.4.3.2) 3.2.4.3.3 Manual FDIR (RSS 3.2.4.3.3) 3.2.4.3.4 Automatic Functional Recovery Confirmation (RSS 3.2.4.3.4) 3.2.4.3.5 Automatic Safing Confirmation (RSS 3.2.4.3.5) 3.2.4.3.6 False Alarm Mitigation (RSS 3.2.4.3.6) 3.2.4.4 Pressure Integrity (derived from RSS 3.2.4.4) 3.2.4.5 Reserved 3.2.4.6 Equipment Installation/Removal 3.2.4.6.1 Equipment Item Interconnecting Devices 3.2.4.6.2 Incorrect Equipment Installation (RSS 3.2.12.5.2) 3.2.4.6.3 Lock Wiring and Staking (RSS 3.2.4.1) 3.2.5 Flight Attitude Table (RSS 3.2.6.1.11) 3.2.6 Environmental Conditions 3.2.6.1 On-orbit Environments (RSS 3.2.6.1) 3.2.6.1.1 Thermal environment (RSS 3.2.6.1.1) 3.2.6.1.2 Neutral Atmosphere (RSS 3.2.6.1.2) 3.2.6.1.3 External Contamination (RSS 3.2.6.1.3) 3.2.6.1.4 Magnetic Fields

3.2.6.1.4.1 Electromagnetic Fields

(Derived from RSS 3.2.6.1.4) 3.2.6.1.4.2 Geomagnetic Fields (Derived from RSS 3.2.6.1.4) 3.2.6.1.5 Plasma (Derived from RSS 3.2.6.1.5) 3.2.6.1.6 Ionizing Radiation (RSS 3.2.6.1.6) 3.2.6.1.7 Reserved 3.2.6.1.8 Meteoroids and Orbital Debris (M/OD) (RSS 3.2.6.1.8) 3.2.6.1.9 Reserved 3.2.6.1.10 Plume Impingement Pressures (Derived from RSS 3.2.6.1.10) 3.2.6.2 Ground Environments 3.2.6.2.1 Transportation Environments 3.2.6.2.2 Storage Environments 3.3 Design and Construction 3.3.1 Materials, Processes, and Parts (RSS 3.3.1) 3.3.1.1 Reserved 3.3.1.2 Reserved 3.3.1.3 Materials and Processes (RSS 3.3.1.3) 3.3.1.4 Electrical, Electronic, and Electromechanical (EEE) Parts Selection 3.3.1.4.1 EEE Part Selection (Derived from RSS 3.3.1.4) 3.3.1.5 Seal Life (RSS 3.3.1.5) 3.3.1.6 Fluid Standards (RSS 3.3.1.6) 3.3.1.8 Reserved 3.3.1.9 Design Requirements 3.3.1.9.1 Structural Design Requirements (RSS 3.3.12.1) 3.3.1.9.2 Structure Penetration (Derived from RSS 3.3.12.1.1.1) 3.3.1.9.3 Reserved 3.3.1.9.4 Fracture Control (Derived from RSS 3.3.12.3) 3.3.1.9.5 Atmosphere Leakage (Derived from RSS 3.3.12.7) 3.3.2 Electromagnetic Compatibility (EMC) (RSS 3.3.2.1) 3.3.3 Nameplates and Product Markings (RSS 3.3.3) 3.3.3.1 Labeling (RSS 3.3.3.1) 3.3.3.1.1 Vendor Labels (RSS 3.3.3.1.1) 3.3.3.2 On-orbit Labels (RSS 3.3.3.2) 3.3.4 Workmanship (RSS 3.3.4) 3.3.4.1 Cleanliness (RSS 3.3.4.1) 3.3.4.2 Cleanliness of Surfaces in Contact with Fluids (RSS 3.3.4.2) 3.3.5 Preclude Condensation (RSS 3.3.12.9) 3.3.6 Safety 3.3.6.1 General 3.3.6.1.1 Catastrophic Hazards (RSS 3.3.6.1.1) 3.3.6.1.2 Critical Hazards (Derived from RSS 3.3.6.1.2) 3.3.6.1.3 Design for Minimum Risk (RSS 3.3.6.1.3) 3.3.6.1.4 Control of Functions Resulting in Critical Hazards 3.3.6.1.4.2 Loss of a Function Resulting in a Critical Hazard (RSS 3.3.6.1.4.2) 3.3.6.1.5 Control of Functions Resulting in Catastrophic Hazards 3.3.6.1.5.1 Inadvertent Operation Resulting in a Catastrophic Hazard (RSS 3.3.6.1.5.1) 3.3.6.1.5.2 Loss of Function Resulting in a Catastrophic Hazard (RSS 3.3.6.1.5.2) 3.3.6.1.5.3 Material Fire Safety (RSS 3.3.1.3) 3.3.6.1.5.5 Non Ionizing Radiation (RSS 3.3.6.6.2) 3.3.6.1.5.5.1 Reserved 3.3.6.1.6 Subsequent Induced Loads (RSS 3.3.6.1.6) 3.3.6.1.7 Safety Interlocks (RSS 3.3.6.1.7) 3.3.6.1.8 Environmental Compatibility (Derived from RSS 3.3.6.1.8) 3.3.6.1.9 Redundant Functions (RSS 3.3.6.1.9) 3.3.6.1.10 Hazard Detection and Safing

3.3.6.1.10.1 Safing Prior to Return, Resupply/Refurbishment

(RSS 3.3.6.2.1)

3.3.6.1.11 Monitors 3.3.6.1.11.1 Status Information (RSS 3.3.6.2.2.1) 3.3.6.1.11.2 Hazardous Function Operation Prevention (RSS 3.3.6.2.2.2) 3.3.6.1.11.3 Loss of Input or Failure (RSS 3.3.6.2.2.3) 3.3.6.1.11.4 Flight Crew Availability (RSS 3.3.6.2.2.5) 3.3.6.1.12 Near-Real-time Monitoring (RSS 3.3.6.2.3) 3.3.6.1.13 Real-time Monitoring 3.3.6.1.13.1 Maintain Status of Hazard Controls (RSS 3.3.6.2.4.1) 3.3.6.1.13.2 Crew Response Time and Safing Procedures (RSS 3.3.6.2.4.2) 3.3.6.1.14 Command and Computer Control of Hazardous Functions 3.3.6.1.14.2 Detection and Recovery (RSS 3.3.6.3.1.1) 3.3.6.1.14.3 Independent Safing Action (RSS 3.3.6.3.1.2) 3.3.6.1.15 Hazardous Materials 3.3.6.1.15.1 Hazardous Fluid Containment (RSS 3.3.6.4.1) 3.3.6.1.15.2 Reserved 3.3.6.1.16 Pyrotechnics for FGB Applications (RSS 3.3.6.5) 3.3.6.1.17 Electrical Safety 3.3.6.1.17.1 Electrical Power Circuit Overloads 3.3.6.1.17.1.1 Circuit Overload Protection (RSS 3.3.6.8.1.1) 3.3.6.1.17.1.2 Protective Device Sizing (RSS 3.3.6.8.1.2) 3.3.6.1.17.1.3 Bent Pin or Conductive Contamination(RSS 3.3.6.8.1.3) 3.3.6.1.17.2 Crew Protection for Electrical Shock (RSS 3.3.6.8.2) 3.3.6.1.17.3 Reapplication of Power (RSS 3.3.6.8.3) 3.3.6.1.17.4 Batteries (RSS 3.3.6.8.4) 3.3.6.1.18 Reserved 3.3.6.1.19 Fire Protection 3.3.6.1.19.1 Isolation (RSS 3.3.6.10.2) 3.3.6.1.19.2 Reserved 3.3.6.1.19.3 Manual Activation (RSS 3.3.6.10.1) 3.3.6.1.19.4 Suppressant 3.3.6.1.19.4.1 Suppression (RSS 3.3.6.10.3) 3.3.6.1.19.4.2 Suppressant Material (RSS 3.3.6.10.4.1) 3.3.6.1.19.5 Toxicity Level (RSS 3.3.6.10.4.2) 3.3.6.1.19.6 Contamination (RSS 3.3.6.10.5) 3.3.6.1.19.7 Portable Equipment 3.3.6.1.19.7.1 Proximity to Entrance (RSS 3.3.6.10.6.1) 3.3.6.1.19.7.2 Location Within Element (RSS 3.3.6.10.6.2) 3.3.6.1.19.7.3 Set Co-Location (RSS 3.3.6.10.6.3) 3.3.6.1.20 Constraints 3.3.6.1.20.1 Depressurization 3.3.6.1.20.1.1 Pressurized Volume Depressurization and Repressurization

3.3.6.1.20.1.1.1 Hazards During Depressurization

(RSS 3.3.6.11.1)

3.3.6.1.20.1.1.2 Depressurized and Repressurization Failure Propagation

3.3.6.1.20.1.2 Operation During Pressure Change

(RSS 3.3.6.11.1)

3.3.6.1.20.1.3 Operation While Autonomous

(RSS 3.3.6.11.1)

3.3.6.1.20.2 Emergency Egress (Derived from RSS 3.3.6.11.2) 3.3.6.1.20.3 Translation Entry/Exit Paths (RSS 3.3.6.11.3) 3.3.6.1.20.4 Component Hazardous Energy Provision (RSS 3.3.6.11.4) 3.3.6.1.20.5 Reserved 3.3.6.1.20.6 Hatch Operations (RSS 3.3.6.11.6) 3.3.6.1.20.7 Pins or Detachable Parts (RSS 3.3.6.11.7) 3.3.6.1.20.8 Single Crew Member Entry/Exit (RSS 3.3.6.11.8) 3.3.6.1.20.9 Reserved 3.3.6.1.20.10 Equipment Clearance for Entrapment Hazard (RSS 3.3.6.11.10) 3.3.6.1.20.11 Light Fixture (RSS 3.3.6.11.11) 3.3.6.1.21 Liquid Propellant Propulsion Systems (RSS 3.3.6.9) 3.3.6.1.21.1 Inadvertent Engine Firings (RSS 3.3.6.9.1) 3.3.6.1.21.2 Propellant Flow Control Devices (RSS 3.3.6.9.1.1) 3.3.6.1.21.3 Thruster Valves (RSS 3.3.6.9.1.1.1) 3.3.6.1.21.4 Operations (RSS 3.3.6.9.1.1.2) 3.3.6.1.21.5 Electrical Inhibits (RSS 3.3.6.9.1.2) 3.3.6.1.21.6 Monitoring of Electrical Inhibits to Prevent Catastrophic 3.3.6.1.21.7 Propellant Overheating (RSS 3.3.6.9.2) 3.3.6.1.21.8 Propellant Leakage (RSS 3.3.6.9.3) 3.3.6.1.21.9 Plume Impingement (Derived from RSS 3.3.6.9.5) 3.3.6.1.21.10 Hazardous Venting (RSS 3.3.6.9.6) 3.3.6.1.21.11 Monitoring Propulsion System Status (RSS 3.3.6.9.7) 3.3.6.1.21.12 The FGB Motion Control System (RSS 3.3.6.9.8) 3.3.6.2 Ground Safety 3.3.6.2.1 Operation Procedures (RSS 3.3.6.15) 3.3.6.2.2 Reserved 3.3.6.2.3 Reserved 3.3.6.2.5 Ground Operations Equipment (RSS 3.3.6.15) 3.3.6.2.6 Reserved 3.3.6.2.7 Electrical Grounding (RSS 3.3.1.3, 3.3.6.15) 3.3.6.3 Reserved 3.3.6.4 Personnel Safety 3.3.6.4.1 Personnel Protection Equipment 3.3.6.4.2 Out-gassing of Materials (RSS 3.3.1.3, 3.3.10.2) 3.3.7 Human Factors 3.3.7.1 Internal Volume Touch Temperature 3.3.7.1.1 Continuous Contact – High Temperature (RSS 3.3.6.12.1.1) 3.3.7.1.2 Incidental or Momentary Contact – High Temperature 3.3.7.1.3 Internal Volume Low Touch Temperature (RSS 3.3.6.12.1.3) 3.3.7.2 IVA Internal Corner and Edge Protection (RSS 3.3.6.12.4) 3.3.7.3 Reserved 3.3.7.4 Latches 3.3.7.4.1 Design (RSS 3.3.6.12.6.1) 3.3.7.4.2 Protective covers or guards (RSS 3.3.6.12.6.2) 3.3.7.5 Screws and Bolts (RSS 3.3.6.12.7) 3.3.7.6 Safety Critical Fasteners (RSS 3.3.6.12.8) 3.3.7.7 Levers, Cranks, Hooks, and Controls (RSS 3.3.6.12.9) 3.3.7.8 Burrs (RSS 3.3.6.12.10) 3.3.7.9 Reserved 3.3.7.10 Reserved 3.3.7.11 Reserved 3.3.7.12 Flex Hoses, Lines, and Cables (RSS 3.3.6.12.15) 3.3.8 Human Engineering 3.3.8.1 Anthropometric Requirements (Derived from RSS 3.3.7.1) 3.3.8.2 Normal Operations (RSS 3.3.7.3.1) 3.3.8.3 Maintenance (RSS 3.3.7.3.2) 3.3.8.4 Emergency Controls (RSS 3.3.7.3.3) 3.3.8.5 Alphanumeric Coding (RSS 3.3.7.5.1) 3.3.8.6 Accommodate Changes (Derived from RSS 3.3.7.5.2) 3.3.8.7 Housekeeping (RSS 3.3.7.6) 3.3.8.8 Acoustic Emission Limits (RSS 3.3.10.1) 3.3.9 EVA Capabilities 3.3.9.1 Reserved 3.3.9.2 Establish Translation Paths (RSS 3.2.2.2, 3.2.2.6) 3.3.9.3 Establish Worksites (RSS 3.2.2.3)

3.3.9.3.1 Procedures and Tools (RSS 3.2.4.1.2)

3.3.9.4 External Touch Temperature for EVA (RSS 3.3.6.12.2) 3.3.9.5 External Edge, Corner, and Protrusion Radii (RSS 3.3.6.12.3) 3.3.9.7 Reserved 3.3.9.8 Protrusions (RSS 3.3.6.12.12) 3.3.9.9 Pinch Points (RSS 3.3.6.12.13) 3.3.9.10 External Hardware Placards and Controls 3.3.9.11 Moving or Rotating Equipment (RSS 3.3.6.12.17) 3.3.9.13 External Task Location Requirements (RSS 3.3.7.2) 3.3.9.14 Reserved 3.3.9.15 Gloved Operation (Derived from RSS 3.3.7.4) 3.3.9.16 EVA Primary Translation Path (RSS 3.3.7.5.4) 3.3.9.17 Extravehicular Activity (EVA) On-orbit Induced Loads (RSS 3.3.12.1.2) 3.3.9.18 Knobs and Fasteners (RSS 3.3.12.6) 3.3.9.19 EVA Equipment Handling Capabilities (RSS 3.3.13) 3.3.10 MIL-STD-1553 data bus addresses (RSS 3.3.14) 3.3.11 MIL-STD-1553 data bus constraints (RSS 3.3.15) 3.3.11.1 Use of SSQ components (RSS 3.3.15.1) 3.3.11.1.1 Bus coupler type (RSS 3.3.15.1.1) 3.3.11.2 Bus stub length (RSS 3.3.15.2) 3.3.11.3 Bus coupling (RSS 3.3.15.3) 3.3.11.4 MIL-STD-1553 Bus Terminations 3.3.12 Terminal Interface Units (RSS 3.3.16) 3.3.12.1 TIU Multiple Bus Isolation (RSS 3.3.16.1) 3.3.13 FGB not-to-exceed bus length (RSS 3.3.17) 3.4 Computer resource requirements 3.4.1 Computer hardware design considerations (RSS 3.4.1, 3.4.2) 3.4.2 Flexibility and expansion 3.4.2.1 Programming language (RSS 3.4.2) 3.4.2.2 Development (RSS 3.4.2) 3.4.2.3 Modification (RSS 3.4.2) 3.4.2.4 Partitioning (RSS 3.4.2) 3.4.2.5 Processing resource allocations 3.4.2.5.1 Throughput utilization (RSS 3.4.2) 3.4.2.5.2 Processor utilization (RSS 3.4.2) 3.4.2.5.3 RAM utilization (RSS 3.4.2) 3.4.2.5.4 Non-volatile memory utilization (RSS 3.4.2) 3.4.2.5.5 Mass Storage Utilization 3.4.3 Software portability 3.4.4 Computer software design constraints (RSS 3.4.2) 3.5 Logistics (RSS 3.5) 3.5.1 Maintenance 3.5.1.1 General Maintenance Requirements 3.5.1.1.1 FGB On-orbit Maintenance (Derived from RSS 3.5.1.1.1) 3.5.1.1.2 Reserved 3.5.1.2 Perform On-orbit Maintenance 3.5.1.2.1 ORU Removal and Replacement (RSS 3.5.1.2.1) 3.5.1.2.2 In-situ Maintenance (RSS 3.5.1.2.2) 3.5.1.2.3 Maintenance Coordination (RSS 3.5.1.2.3) 3.5.1.2.4 Reserved 3.5.2 Supply (RSS 3.5.2) 3.5.2.1 General Supply Requirements 3.5.2.1.1 Sustaining Fleet Resources (RSS 3.5.2.1.1) 3.5.2.1.2 On-orbit Propellant Reserves (Derived from RSS 3.5.2.1.4) 3.5.2.1.3 Maintenance Resources (RSS 3.5.2.1.3) 3.5.2.2 Provide Inventory Management Capability 3.5.2.2.1 Item Storage (RSS 3.5.2.2.1) 3.5.3 Reserved 3.6 Reserved 3.7 Major FGB Functional Characteristics 3.7.1 Structures (S) 3.7.1.1 Primary Structures (derived 3.2.1.15.1) 3.7.1.1.1 Factors and Margins of Safety (derived 3.3.1.9.1) 3.7.1.1.2 Docking/Berthing Interface Structural Provisions 3.7.1.1.3 On-orbit Loads 3.7.1.1.4 Launch Vehicle Interface Structural Provisions 3.7.1.2 Secondary Structures and Appendages (derived 3.2.1.17.4) 3.7.1.3 Micrometeoroid and Orbital Debris Protection Provisions 3.7.1.4 Exterior Dimensional Constraints 3.7.1.5 Internal Volume Provisions 3.7.1.6 Visual Access (derived from 3.2.1.10.1 & 3.2.1.10.2) 3.7.2 Mechanisms (M) 3.7.2.1 Torque/Force Margins 3.7.2.2 Servo/Dynamic Margins 3.7.2.3 Docking and Undocking Provisions 3.7.2.3.1 Docking Provisions 3.7.2.3.2 Undocking Provisions 3.7.2.3.3 Docking Contact Rates and Alignment (SM NOT ORBITER ASSISTED) 3.7.2.3.3.1 Docking Contact Rates and Alignment for Orbiter Assisted Docking with ICM and SM.

3.7.2.3.4 Airtight Docking Seal 3.7.2.3.5 Docking Loads (Derived from RSS 3.2.5) 3.7.2.3.6 Reserved 3.7.2.4 Berthing and Unberthing Provisions 3.7.2.4.1 Berthing Provisions 3.7.2.4.2 Unberthing Provisions 3.7.2.4.3 Compatibility with Orbiter RMS (Derived from RSS 3.3.11) 3.7.2.4.4 Airtight Berthing Seal 3.7.2.4.5 Berthing Loads 3.7.2.4.6 FGB Control Inhibit 3.7.2.4.7 Unberthing Separation Rates and Clearances 3.7.2.5 Solar Array Mechanisms 3.7.2.5.1 Solar Array Deployment/Retraction Provisions 3.7.2.5.1.1 Deployment/Retraction 3.7.2.5.1.2 Deployment/Retraction Loads 3.7.2.5.1.3 Deployment/Retraction Indication 3.7.2.5.1.4 Reserved 3.7.2.5.1.5 Solar Array EVA Removal 3.7.2.5.2 Solar Array Pointing Provisions 3.7.2.6 Antenna Mechanisms 3.7.2.6.1.1 Autonomous Antenna Deployment 3.7.2.6.1.2 Antenna Deployment Loads 3.7.2.6.1.3 Antenna Deployment Indication 3.7.2.6.1.4 Antenna Removal 3.7.2.6.2 Reserved 3.7.2.7 Intermodule Fluidic and Electrical Connect / Disconnect Provisions 3.7.2.7.1 Fluidic and Electrical Connect - Docking 3.7.2.7.2 Fluidic and Electrical Disconnect - Undocking 3.7.2.7.3 Reserved 3.7.2.7.4 EVA Activity 3.7.2.7.5 Electrical Connect - Berthing 3.7.2.7.6 Electrical Disconnect - Unberthing 3.7.2.7.7 Berthing/Unberthing Operations 3.7.2.8.

FGB/Launch Vehicle Separation Provisions 3.7.2.8.1 Separation Margin 3.7.2.8.2 Separation Rates and Clearances 3.7.3 Thermal Control System (TCS) 3.7.3.1 Active Thermal Control (derived 3.2.1.3.1) 3.7.3.1.1 Internal Thermal Control Loops (derived 3.2.1.3.2) 3.7.3.1.2 External Thermal Control Loops (derived 3.2.1.3.3) 3.7.3.2 Passive Thermal Control (derived 3.2.1.3.4) 3.7.3.2.1 Multilayer Insulation Applications (derived 3.2.1.3.4) 3.7.3.2.2 Surface Infrared Properties (derived 3.2.1.3.4) 3.7.3.2.3 Thermal Resistance Attachments (derived 3.2.1.3.4) 3.7.4 Life Support System (LSS 3.7.4.1 Gas Composition System (derived 3.2.1.1.1, 3.2.1.1.2, 3.2.1.1.5) 3.7.4.2 Reserved 3.7.4.3 Atmosphere Conditioning and Circulation Subsystem 3.7.4.3.1 Monitor Humidity (derived 3.2.1.2.3) 3.7.4.3.2 Monitor Atmosphere Temperature (derived 3.2.1.2.1, 3.2.1.2.2) 3.7.4.3.3 Circulate Atmosphere (derived 3.2.1.2.4, 3.2.1.2.5) 3.7.4.3.4 Filter Particulates (derived 3.2.1.1.4) 3.7.4.3.5 FGB to PMA1 Leak Seal Monitoring and Repressurization.

3.7.4.3.6 Monitor CO2 Partial Pressure (derived 3.2.1.1.3) 3.7.4.4 Fire Detection and Suppression System 3.7.4.4.1 Detect Fire (derived 3.2.1.13.2) 3.7.4.4.2 Activate Alarm (derived 3.2.1.13.2) 3.7.4.4.3 Shut Off Power and Airflow (derived 3.2.1.13.3) 3.7.4.4.4 Shut Off Intermodule Airflow (derived 3.2.1.13.3) 3.7.4.4.5 Portable Breathing Apparatuses (derived 3.2.1.13.1, 3.2.1.13.6) 3.7.4.4.6 Fire Extinguisher (derived 3.2.1.13.1, 3.2.1.13.4) 3.7.4.4.7 Restoring Habitable Environment (derived 3.2.1.13.5) 3.7.5 Crew Systems 3.7.5.1 Handholds and Supports (derived 3.2.1.16.1, 3.2.1.17.1) 3.7.5.2 Reserved 3.7.5.3 Lighting (derived 3.2.1.5.1, & 3.2.1.5.2) 3.7.5.4 Support Housekeeping (derived 3.2.1.16.2) 3.7.6 Command and Data Handling (C&DH) 3.7.6.1 Command and Control 3.7.6.1.1 Control On-board Systems (derived 3.2.1.7.1) 3.7.6.1.2 Station Modes (derived 3.2.1.7.1) 3.7.6.1.3 FGB Space Operations 3.7.6.1.4 Software Control 3.7.6.2 Data Handling 3.7.6.2.1 Function Status Data (derived 3.2.1.6.1, 3.2.1.6.2) 3.7.6.2.2 Data Exchanges (derived 3.2.1.6.1) 3.7.6.2.3 Command and Data Transfers (derived 3.2.1.18.1) 3.7.6.2.4 Out-of-tolerance Conditions (derived 3.2.1.6.2) 3.7.6.2.5 Hazardous Conditions (derived 3.2.1.6.2) 3.7.6.3 Time Distribution (derived 3.2.1.8) 3.7.6.4 Failure Detection, Isolation and Recovery (FDIR) 3.7.6.4.1 Failure Isolation and Recovery (derived 3.2.1.12.1, 3.2.1.12.2) 3.7.6.4.2 Safing Operations (derived 3.2.1.12.3) 3.7.7 Motion Control 3.7.7.1 Motion Control Operations 3.7.7.1.1.

MCS Operation in the presence of the ICM 3.7.7.2 Attitude Control 3.7.7.2.1.

Attitude Control During Translation Maneuvers on Flights 1A/R and 2A (3.2.1.14.3) 3.7.7.2.2.

Dynamic Stability in the FGB (Flight 1A/R) and FGB + NODE 1 (Flight 2A) Configurations (3.2.1.14.3) 3.7.7.2.3.

LVLH Attitude Control in the FGB (Flight 1A/R) and FGB + NODE 1(Flight 2A) Configurations (3.2.1.14.3) 3.7.7.2.4.

Attitude Control During Soft Docking with the Orbiter on Flight 2A (3.2.1.14.3)

3.7.7.2.4.1. Attitude Control During direct Docking of the Orbiter Delivering the ICM or SM on Flight 2A.1 and 7A.1 3.7.7.2.5 Inhibit Attitude Control 3.7.7.2.5.1 Inhibit Attitude Control after Grappling (derived 3.2.1.14.3) 3.7.7.2.5.2 Inhibit Attitude Control after Docking with the SM in the FGB+ Node 1 configuration (2A). (3.2.1.14.3) 3.7.7.2.5.2.1.

Inhibit control after Orbiter docking on flights 2a.1 and 7a.1 3.7.7.2.5.3 Indication of Attitude Control Inhibit on Flight 2A. (derived 3.2.1.14.3a(9),(15)) 3.7.7.2.5.3.1.

Indicate inhibit of attitude control on flights 2a.1 and 7a.1 3.7.7.2.5.4 Inhibit Attitude Control from RGS (derived 3.2.1.14.3) 3.7.7.2.6 Activate Thruster Operations after Separation of the Orbiter on Flight 2A, 2A.1, and 7A. (derived 3.2.1.14.3) 3.7.7.2.6.1 Activate Thruster Operations after Separation on flight 2A.

3.7.7.2.6.2. Activate thruster operation after separation of the Orbiter on flight 2A.1

3.7.7.2.6.3. Activate thruster operation after separation of the ICM on flight 7A.

3.7.7.2.7 Attitude Control in an Orbital Environment 3.7.7.2.7.1 Attitude Command Data (derived 3.2.1.14.3) 3.7.7.2.7.2 Execution of Command (derived 3.2.1.14.3) 3.7.7.2.8 Indicate Status of motion control system 3.7.7.2.9 Attitude Control of the ISS in configurations indicated in Table3-VIII in the presence of the ICM:

3.7.7.3.

Translation Control in the FGB and FGB + Mode 1 Configurations (1A/R, 2A).

3.7.7.3.1.

Guidance During Maneuvers in the FGB and FGB + Node 1 Configurations (1A/R, 2A).

3.7.7.3.1.1. Reboost Maneuver in the FGB + Node 1 configurations (1A/R, 2A)(3.2.1.14.1)

3.7.7.3.1.2. Orbit Control in the FGB and FGB + NODE 1 Configurations (1A/R, 2A) (3.2.1.14.1) 3.7.7.3.1.3.

Docking Control in the FGB + NODE 1 configuration (2A) (3.2.1.14.1) 3.7.7.3.1.4.

Provide Automated Collision Avoidance Maneuvers in the FGB + NODE 1 Configuration (2A) (3.2.1.14.1) 3.7.7.3.2.

Maneuver Commands in the FGB and FGB + Node 1 Configurations (1A/R, 2A)

3.7.7.3.2.1. Maneuver Execution in the FGB and FGB + Node 1 Configurations (1 A/R, 2A) (3.2.1.14.2) 3.7.7.3.2.2.

Maneuver Termination in the FGB and FGB + Node 1 Configurations (1A/R, 2A) (derived 3.2.1.14.2)

3.7.7.3.2.3. Maneuver Initiation and Termination in the FGB and FGB + Node 1 Configurations (1A/R, 2A) (derived 3.2.1.14.2)

3.7.7.3.2.4. Maneuvering Commands Received from Ground Services in the FGB and FGB + Node1 Configurations (1A/R, 2A) (3.2.1.14.2) 3.7.8 Communication and Tracking (C&T) 3.7.8.1 Link with Ground Stations 3.7.8.2 Sensor Data Collection (derived 3.2.1.11.2.1) 3.7.8.3 Telemetry data Transmission (derived 3.2.1.11.2.2) 3.7.8.4 Data Display 3.7.8.5 Rendezvous and Docking Support 3.7.8.6 Trajectory Measurement 3.7.8.7 Audio Communications Links (derived 3.2.1.9.1, 3.2.1.9.2) 3.7.8.8 Emergency Warnings (derived 3.2.1.13.2) 3.7.8.9 Video for Rendezvous and Docking (derived 3.2.1.10.2) 3.7.8.10 Signal Transmittal 3.7.8.11 Video Signal Creation and Display (derived 3.2.1.10.1) 3.7.9 FGB Power Supply (PS) 3.7.9.1 FGB Generate Power 3.7.9.2 FGB Distribute Power (derived from 3.2.1.4.2) 3.7.9.2.1 Distribute Power at USOS Interface (derived from 3.2.1.4.2) 3.7.9.2.2 Distribute Power at UDM Interface (derived from 3.2.1.4.2) 3.7.9.2.3 Distribute Power at SM Interface (derived from 3.2.1.4.2) 3.7.9.2.4 Distribute Power at DSM/Soyuz Vehicle Interface (derived from 3.2.1.4.2) 3.7.9.2.5 Distribute Power at Progress Vehicle Interface (derived from 3.2.1.4.2) 3.7.9.3 Grounding Restrictions 3.7.9.4 Energy Storage (derived 3.2.1.4.3) 3.7.10 Propulsion Unit (PU) 3.7.10.1 Pressurized Systems Design 3.7.10.1.1 Welded Connections 3.7.10.1.2 Propellant Mass Status (derived 3.2.1.14.2 & 3.2.1.14.3) 3.7.10.1.3 System Health and Status (derived 3.2.1.14.2) 3.7.10.1.4 Command Interfacing 3.7.10.1.7 Propellant Resupply 3.7.10.2 Propellant Supply and Storage 3.7.10.2.1 Tankage Capacity (derived 3.2.1.14.2) 3.7.10.2.2 Tank Pressure 3.7.10.2.3 Material Compatibility 3.7.10.2.4 Propellant Temperatures 3.7.10.2.5 Propellant Resupply 3.7.10.4 Reboost Thruster Shutdown 4.0

QUALITY ASSURANCE PROVISIONS

4.1 General 4.1.1 Responsibility for Verification 4.2 Segment Quality Conformance Inspections 4.3 Verification Requirements 5.0 Preparation For Delivery 6.0 Notes 6.1 Abbreviations and Acronyms 6.2 Definitions

1-1 Matrix of Russian to US Subsystem Nomenclatures and Functions

3-2 FGB Subsystem Block Diagram

3-3 FGB System Functional Interface

3-4 FGB Overview

3-5 Fire Protection Selection Guide

3-6 Fire Protection Selection Guide Continued

3-7 Fire Protection Selection Guide Continued

3-8 Allowable Accelerations at the Internal Payloads

3-16 Allowable Translation Accelerations at RS to USOS Interface

3-17 Allowable Rotational Accelerations at RS to USOS Interface

3-20 Multiplication Attenuation Factors

3-9 FGB Coordinate Axis Systems

3-18 Scanning Antenna Field of View

3-21 Design hot thermal environment profile

3-22 Design cold thermal environment profile

3-23 Extreme hot thermal environment profile

3-24 Extreme cold thermal environment profile

3-13 On-Orbit Electromagnetic Field Intensity

3-14 Allowable P/L to Orbiter International Electric Field Strength

3-25 Typical Bus

3-10 Crew Member Work Envelope

3-11 Spacesuit Helmet Field of View

3-12 Crewmember Work Envelope (Gloved Hand)

4-1 Test Harness 1

4-2 Test Harness 2

4-3 Test Harness 3

4-4 TIU Multibus Isolation Test Setup

3-III

Distribution of Power

3-IV

FGB Interior Lighting Intensity Levels

3-V Failure Detection, Isolation, and Recovery Functions

3-VI

FGB Functional System Versus Operational Phase

3-VII

Propulsion Performance Data

3-VIII

ISS Configurations requiring FGB attitude control

3-XXI

FGB MIL-STD-1553 Data Bus Distribution

3-IX

FGB Capability Failure Tolerances

3-XXIII

Flight attitudes

3-XIX

Hot and cold natural thermal environment

3-XX

Extreme hot and cold natural thermal environment

3-XII

Solar and Geomagnetic Parameter Applicable to Space Station Design

3-XIII

Parameters for M/OD Environment Definition

3-XIV

Spacecraft Maximum Allowable Concentrations

3-XV

Designated Extravehicular Activity Interfaces

3-XVI

Edge, Corner, and Protrusion Criteria

3-XVII

External Hardware Placards and Controls

3-XXII

FGB no-to-exceed bus lengths

3-XVIII

Maximum Limits for Transport of Objects by a Single Crewmember

4-I Test Interfaces

1.0

SCOPE

This specification establishes the performance, design, development, and verification requirements for the Energy Block (FGB) element, hereafter referred to as the FGB, of the International Space Station Alpha (ISSA). The FGB is a Russian-designed and manufactured element procured by NASA. The constraints applicable to this Procurement Specification are listed in paragraph 3.1.2.

Figure 1-1 shows the Russian FGB system’s correspondence to the U.S. subsystem nomenclature.

Section 3.1 defines the FGB segment to segment interfaces by block diagrams, a description of the interface functionality, and a description of the physical interface. Requirements in Section 3.2.1 define the performance characteristics of the FGB. Requirements in Sections 3.2.2 through 3.6 are constraints with which the FGB must comply. Requirements in Section 3.7 define the performance of the systems that compose the FGB. Section 4.0 contains the verification requirements for each paragraph from Section 3.2.1 through Section 3.7. The performance requirements are derived from the functional decomposition, a hierarchical breakdown of capabilities and functions the FGB will perform.

Requirements listed in Section 3.1 are based on the interface control documents (ICDs) that control the segment-to-segment interfaces. Requirements in Section 3.7 are based on functions that are subtiered to the parent capabilities defined in Section 3.2.1. The performance requirements herein are applicable during nominal operations, maintenance, or contingency events. Note: As the ISSA segments are assembled, the requirements for the FGB operation change.

1.1

FGB Overview

The FGB will be the first orbiting element of the ISSA. The purpose of the FGB is to provide for the assembly of American and Russian elements of the ISSA; accumulation and distribution of the power supply within the frames of the power system of the station; reception, storage, and delivery of propellants in the combined pneumatic hydraulic system, motion control system (guidance and control), onboard complex control system; partial life support functions; propulsion services, communications, and data links to the ground support facilities. The FGB navigation function is performed by the Ground Stations.

1.2

Notations Used in This Document

A “TBR”, to be resolved, signifies the specified requirement is believed to be correct, but the requirement needs to be analyzed to ensure its correctness.

A “TBD”, to be determined, signifies that the specific details for the requirement are unknown and will have to be researched with the correct data/information added to the specification when it is available.

1.3

Notes Concerning FGB Configuration

After the Node 1 is docked to the FGB, the FGB will transfer FGB status data through the FGB/PMA1 interface.

FGB 142A, 10/9/98

1.4

Interface control approach The approach to interface requirements and interface control is driven by the existing interface responsibilities.

On the United States (US) side, NASA has the responsibility for the interfaces between the FGB and other US element (e.g. PMA-1 and the ICM). The requirements as specified in SSP 42121 PMA-1 to FGB ICD part 1 and SSP 50269 FGB to Control Vehicle (Generic) ICD have been flowed down into the FGB specification.

On the Russian side RSA has the responsibility for the interfaces between the FGB and the elements of the Russian Segment. The ICD is prepared as part of the NASA-RSA contract (NAS 15-10110 Data Requirement DR RVE-23, FGB Interface Control Documentation). The requirements of this document are flowed into the FGB specification.

2.0

APPLICABLE

The following specifications, standards, handbooks, drawings and publications of the exact issue shown form a part of this specification to the extent specified herein. Where a “/T” follows a document number, that document has been tailored for FGB unique utilization. In the event of a conflict between the documents referenced herein and the contents of this specification, the contents of this specification shall be considered a superseding requirement.

NASA:

SSP 50097 SSMB to RS Software ICD Revision B dated: March 1998 plus PIRN 51 and PIRN 70A.

FGB 156A, 10/5/98 and FGB 172, 5/31/00

SSP 50269 FGB to Control Vehicle (Generic) ICD, Interface Control Document, Working Draft, June 20, 1997, w/PIRNs 1 and 2.

FGB 149A. 6/15/98

SSP 50017

Assembly Sequence Manifest.

SSP 42121, dated: 30 June 1995, w/PIRNs 42121-NA-

0020A, (21), (22A), (23), (24), (25B), (26), (27A), (28), (29A), (30), (31), (33), (34),(35),(36), (37), (38), (39B), (40), (41A), (42), (43), (44), (45), (46), (47), (48), (49C), (50), (51), (52), (53), (54), (55), (56), (57), (58), (59), (60), (62), (63), (64), (65B), (66), (67B), (68), (69), (70), (71E), (72C), (73), (75) and (79).

FGB 135A and FGB 138A, 3/6/98

FGB 161, 10/8/98

U.S. On-orbit Segment Pressurized Mating Adapter 1 to

Russian Segment FGB Interface Control Document

(Appendix C of SSP 42121, Part 1 is the sole source of all

Orbiter to FGB interface requirements)

SSP 30261:002, Space Station Multiplexer/Demultiplexer

(SSMDM) Standard ICD, Rev J, 1 April 1998 plus IRN 001.

FGB 162, 10/15/98

SSP 50342, Revision Initial Release, May 1998.

FGB 151A, 10/5/98

RPO – 0754

Russian Microgravity Control Plan

SSP 30423 Rev F, 31 Mar. 95

SSP 30423 Rev. F, 31 Mar 95

MIL-STD-1553 Rev. B, Notice 2, 8 Sep. 86

MIL-HDBK-1553 Rev A, Notice 1, 31 Jan 93

NASA/RSA:

SSP 50094, June 20, 1997 , NASA/RSA Joint

Specifications/Standards Document for the ISSA Russian

Segment plus Joint Standards Team protocol for TIM #21, and

NDCs 004, 005, 006, 007, 008, 009 and 019; except for those items identified in Appendix D of this FGB Specification SSP

50128.

FGB 143C 10/15/98 & FGB 167 11/02/98

Russian:

Specifications / Standards

(Document titles and numbers are TBD)

FGB0041, received Aug 1994

Data for Development of the Technical

Assignment for the Energy Block FGB

KhSC:

RKK Energia

Other:

TBD

2.1

Reference Documents

The following documents form a part of this specification to the extent referenced herein and are considered to be for guidance and information only.

NASA:

SSP 41163, dated: 27 September 1994

Russian Segment Specification

(FGB applicable paragraphs only)

Russian:

RVE-23, Requirements to Interfaces Connecting the FGB with

Other Articles of Russian Orbital Segment

FGB / SM Interfaces

FGB / DSM Interfaces

FGB / TS Soyuz Interfaces

FGB / UDM Interfaces

FGB/Progress Interfaces 2.2

Precedence

All specifications, standards, exhibits, drawings, or other documents that are referenced as applicable in this specification are hereby incorporated as cited. All documents that are referred to by a reference document are considered to be for guidance and information only.

The order of precedence of the FGB specification is as follows:

1.

SSP 50128, FGB Procurement Specification.

2.

Interface Control Documents and Interface Requirements Documents.

3.

SSP 50094, The Join Specifications and Standards Document for the ISSA Russian Segment.

(see note below)

4.

Other applicable documents listed in the procurement specification.

5.

GOST/OST or other approved Khrunichev or Russian specifications used to manufacture the FGB, and not referenced or listed in the applicable documents list.

In the event of a conflict between the requirements herein and any referenced documents, this order of precedence shall be used to decide the prevailing specification.

NOTE:

The FGB specification invokes the utilization of SSP 50094 during the design, manufacture, assembly and testing of the FGB. This document (SSP 50094) will be utilized as the source of applicable specifications and standards. For those cases when SSP 50094 does not contain an applicable specification or standard, or is missing a section or contains a TBD or a TBR, the Approved Existing Russian Documentation is acceptable until such time as a mutually agreed upon resolution is documented for incorporation into SSP 50094 or the contract requirements regarding those items affected by these cases have been completed. Approved Existing Russian Documentation consists of: Russian specification and standards, RKK Energia specifications and standards, Khrunichev specifications and standards, and Khrunichev design requirements.

3.0

REQUIREMENTS

3.1 FGB Definition

(RSS 3.7.1.2)

The FGB is a vehicle used in the initial stages of the ISSA as the primary method for FGB and FGB NODE 1 reboost and attitude control. The FGB contains propulsion, Command and Data Handling (C&DH), Guidance, Navigation, and Control (GN&C), communications, electrical power, and thermal control systems. At permanent human capability the FGB will provide propellant storage for Service Module propulsion system reboost and attitude control.

3.1.1

Interface Definition

3.1.1.1

FGB Diagrams

Block diagrams of each FGB interface to adjoining ISSA segments are included in this section (see Figures. 3-2 through 3-3). The major functional characteristics of the FGB systems/subsystems are described in Section 3.7 of this specification.

3.1.1.2

Physical Interface

The physical interface between the FGB and the adjoining ISSA segments are described in the following ICDs:

SSP 42121,

U.S. On-orbit Segment Pressurized Mating Adapter-1 to Russian

Segment FGB Interface Control Document.

SSP 50269, FGB to Control Vehicle (Generic) ICD.

RVE-23, Requirements to Interfaces Connecting the FGB with Other Articles of

Russian Orbital Segment, ISSA

FGB / Service Module (SM) Interfaces

FGB / Docking and Storage Module (DSM) Interfaces

FGB / Soyuz Vehicle Interfaces

FGB / Universal Docking Module (UDM) Interfaces

FGB/Progress Interfaces Each FGB system is described in detail in Section 3.7 of this specification.

3.1.2 FGB Constraints (Derived from RSS 3.3.12.8)

a.

Orbital Parameters:

(1) For design analysis and planning purposes, the circular orbital parameters for the FGB vehicle are as follows.

Inclination 51.6°

FGB orbit altitudes

Minimum 220 km 119 nmi

Maximum 500 km 270 nmi

2A/1R Rendezvous 350-385 km 189-208 nmi

The orbit of the FGB shall be no less than 350 km 30 days after launch for rendezvous with assembly flight 2A (US Node 1). The orbit of the FGB + Node 1 shall be no less than 350 km 130 days after assembly flight 2A for rendezvous with assembly flight 1R (Service Module).

(2) Operational Altitudes:

For the assembly phases, the minimum operational altitude for the on-orbit space station shall be the altitude that provides 90 days of orbital decay to 278 km (150 NM).

b.

Launch Vehicle:

The FGB shall be designed to be launched with a Proton launch vehicle.

c.

ISSA Assembly Sequence

The FGB shall be designed to be compatible with the ISSA assembly sequence as defined in accordance with SSP 50017, Assembly Sequence Manifest.

d.

Solar Array Orientation

To ensure energy balance of the FGB during the period it is attached to the Orbiter, the orientation of the FGB must be maintained such that the FGB solar arrays are exposed to the sun a minimum of 45 minutes of each sun period.

e. Plume Impingement:

The FGB is designed to withstand plume impingement (loads, contamination and temperatures) as described below:

(1) Plume impingement pressure tolerance for selected FGB components:

In accordance with Russian requirements.

(2) Plume impingement temperature tolerance for selected FGB components.

In accordance with Russian requirements.

f.

FGB support of Soyuz Vehicle.

The requirements identified in the specification relating to the Soyuz vehicle shall be met by the FGB vehicle when the Service Module is not present. Soyuz crew life support functions are provided by the USOS. It is understood that the support of the Soyuz vehicle when the Service Module is not present requires no change to the current FGB configuration capabilities. The FGB is not required to perform attitude control of ISS when Soyuz is docked to the FGB nadir port.

g. ISS motion control moding with FGB assist

ISS motion control moding with FGB assist is defined by the fuel reserves available on the FGB after insertion to orbit and capabilities of the transport system to deliver fuel to the FGB.

FGB 138A, 3/6/98

h. The FGB aft end combination docking unit launch configuration shall be the active configuration.

When the FGB is launched with the aft docking unit in the active combination docking unit configuration, the FGB shall only be required to provide docking interfaces at the aft end with those modules compatible with the capabilities of the FGB and the active combination docking unit at the FGB aft end as specified herein.

If the FGB is required to support the ICM or SM (Orbiter assisted), the transfer of the combination docking unit into the corresponding passive configuration shall be completed not later than 65 days before launch of the FGB, following a management decision. The decision about the transfer of the docking unit into a single configuration must be made no later than 3 months before launch of the FGB and be reflected as an update to this Specification SSP 50128.

FGB 144C 10/5/98

i. FGB Fuel Insertion into Orbit

The FGB delivers a minimum of 2850 kg (2650 kg operating fuel mass) +/- 50 kg to its assembly orbit with Node 1 (when fulfilling nominal flight program of translation from the injection orbit to the assembly orbit with Node 1).

FGB 154B, 10/5/98, FGB 168, 5/31/00

j. Mass Constraints

1. Mass at flight 2A.1

(a) The mass of the cargo delivered to the FGB in Flight 2A.1 shall not exceed 1600 kg.

(b) Total mass of the cargo delivered to the FGB+Node1 configuration in Flight 2A.1 shall not exceed 2300 kg.

2. Mass at flight 2A.2A

(a) Total mass of the cargo remaining on the FGB+Node1 configuration in Flight 2A.2A shall not exceed 3000 kg (taking into account 2A and 2A.1 cargo).

FGB 169E, 5/31/00 and FGB 171F, 5/31/00

k. FGB Lifetime Extension through end of 2000.

FGB can provide autonomous flight of FGB+Node 1 configuration to the end of year 2000 provided:

(1) Flight 2A.2A occurs and successfully conducts the tasks of replacing FGB ORUs which have limited service life or have failed prior to 2A.2A.

(2) FGB propellant is sufficient for normal operations through December 31, 2000.

(3) The possibility of non-failure FGB hardware performance at the end of stand-alone flight of FGB+Node 1 configuration should be not less than TBD.

(4) By the end of 2000, the FGB will need to be docked to a Service Module.

(5) The possibility of docking a manned transport vehicle in order for a crew to replace FGB ORUs will be provided for in case of an FGB hardware failure which leads to the inability of extending autonomous flight of the stack, or the inability to dock with the SM, to the end of 2000.The FGB ORUs intended for transport to the FGB, in the case of failure noted above, must be certified and prepared for on-orbit delivery.

FGB 171F, 5/31/00

3.1.3 Major Component List

The FGB segment consists of two major components, the Pressurized Adapter (PA) and the Pressurized…