SSP_42003-RevJ.docx

United States On-orbit Segment (USOS) to Mobile Servicing System (MSS) Interface Control Document Part I

International Space Station Program

Revision J

March 2016

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

SSP 42003

Revision J

REVISION AND HISTORY

REVISION AND HISTORY - Continued

REVISION AND HISTORY - Continued

REVISION AND HISTORY - Continued

Revision J will be the first release of this document after conversion from the Interleaf Technical Publication Software format to Microsoft Word format. Formatting variances are a result of this conversion.

Revision J includes the following approved SSCN: 013573.

SSP 42003

Revision J

PREFACE

United States On-orbit Segment (USOS) to Mobile Servicing System (MSS) Interface Control Document Part I

MARCH 2016

SSP 42003, United States On-orbit Segment (USOS) to Mobile Servicing System (MSS) Interface Control Document (ICD) Part I shall be implemented on all new Program contractual and internal activities 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 Canadian Space Agency (CSA), and any changes or revisions will be approved by the SSCB and CSA.

INTERNATIONAL SPACE STATION PROGRAM

United States On-orbit Segment (USOS) to Mobile Servicing System (MSS) Interface Control Document Part I

CONCURRENCE

March 2016 v

TABLE OF CONTENTS

APPENDIX

TABLE

FIGURE

INTRODUCTIOn The Space Station provides a Mobile Servicing System (MSS) to assist in the assembly and external maintenance of the Space Station. The MSS is used to transport hardware and payloads about the Space Station and support Extravehicular Activity (EVA) operations.

The flight segments of the MSS consist of the Mobile Remote Servicer Base System (MBS), the Space Station Remote Manipulator System (SSRMS), the Special Purpose Dexterous Manipulator (SPDM), and the Artificial Vision Unit (AVU). The Space Station Manned Base (SSMB) Mobile Transporter (MT) provides the mobility function for the Mobile Remote Servicer (MRS) which comprises the MBS and the SSRMS. The SSRMS and SPDM provide the capabilities to support Space Station assembly, maintenance, servicing, and EVA. The MSS Control Equipment consists of hardware and software to control the MSS.

PURPOSE AND SCOPE

This Interface Control Document (ICD) defines and controls the interfaces between the Space Station and the Mobile Servicing System. Chapter 3 of this ICD is divided into seven sections (A, C, D, E, F, G, and H ) as shown in Figure 1.1-1.

figure 1.1-1 space station to mobile servicing system icd sections

SECTION A PURPOSE AND SCOPE

Definition and control for the SSMB to MBS is in Section A. This section of the ICD defines and controls the interface requirements between the SSMB and the MBS. The MBS interfaces with the EVA Portable Work Platform (PWP) are defined in Section E of this ICD.

deleted

SECTION C PURPOSE AND SCOPE

The AVU to United States Laboratory (USL) interfaces are in Section C. Section C of the ICD defines and controls the physical, electrical, and functional interface requirements between the AVU and the USL. Note, the AVU Cursor Control Device (CCD) to Robotics Workstation (RWS) interface is defined in Section G.

SECTION D PURPOSE AND SCOPE

Section D defines the interfaces associated with the SSRMS operating from a Power and Data Grapple Fixture (PDGF) attached to International Space Station (ISS) pressurized modules. This section of the ICD defines and controls the physical, electrical, and functional interface requirements between the PDGF, and the PDGF harness with a module to support SSRMS and SPDM stand-alone operations. The specific structural, mechanical, and electrical attachments for the PDGFs, and the PDGF harness on the various modules requiring a PDGF for SSRMS or SPDM operation will be defined in Part II of this ICD. PDGF interfaces with users and payloads are defined in SSP 42004, MSS to User ICD.

SECTION E PURPOSE AND SCOPE

Section E defines the interfaces between the EVA PWP and the MBS. The interface when the PWP is stowed or transported is between the MBS PWP Worksite Interface Fixture (WIF) and the PWP.

SECTION F PURPOSE AND SCOPE

Section F defines the interfaces between SSMB and the SSRMS for launch and relocation. This section of the ICD defines and controls the physical, electrical, and functional interface requirements between the SSMB Launch Support Assembly (LSA) and the SSRMS and associated Flight Support Equipment (FSE).

SECTION G PURPOSE AND SCOPE

Section G defines the AVU CCD to RWS interfaces. The interfaces between the AVU and the USL are defined in Section C of this ICD.

SECTION H PURPOSE AND SCOPE

Section H defines the interfaces associated with the Video Signal Converter (VSC). The VSC is used in conjunction with the PDGF to support relocated SSRMS operations on the modules. The VSC is also used on the S0 segment to convert fiber optic video from the external video switch to copper for the Trailing Umbilical System (TUS). This section of the ICD defines and controls the physical, electrical, and functional interface requirements between the SSMB and the VSC.

PRECEDENCE

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

CHANGE AUTHORITY

The responsibility for assuring the definition, control, and implementation of the interfaces identified in this document is vested with the National Aeronautics and Space Administration (NASA) International Space Station Program Office and with the CSA. This document is formally approved and controlled in accordance with the provisions of SSP 30459, International Space Station Interface Control Plan.

1-3

DOCUMENTS

applicable documents The following documents of the exact date and revision shown form a part of this ICD to the extent specified herein.

ANSI Y 14.5M-1982

References Dimensioning and Tolerancing 3.1

ASTM E380

Rev A 1 Jan 93 References Standard Practice for use of the International System of Units (SI)(The Modernized Metric System)

3.1

CSA-SS-ID-0002

Draft 30 Sept 1996 References MSS Robotics Control Station(MRCS) to AVU Interface Control Document

C3.2.1.10, C3.2.2.10

MIL-C-27500

Rev. G, Amend. 1 23 Feb 90 References Cable, Power, Electrical and Cable Special Purpose, Electrical Shielded and Unshielded, General Specifications for C3.2.1.6.1

MIL-C-38999

References Connectors, Electrical, Circular, Miniature, High Density, Quick Disconnect (Bayonet, Threaded and Breech Coupling), Environment Resistant, Removable Crimp and Hermetic Solder Contacts, General Specification for G3.2.1.4

MIL-STD-1553

Rev B, Notice 4 15 January 1996 References Digital Time Division Command/Response Multiplex Data Bus

A3.2.1.5.1, A3.2.1.6.1, A3.2.1.6.2, A3.2.2.6.1, A3.2.2.6.2, C3.2.1.5, C3.2.1.6, C3.2.1.6.2, C3.2.1.6.2.1, C3.2.1.6.2.2, C3.2.1.6.2.4, C3.2.2.6, C3.2.2.6.2, C3.2.2.6.2.1, C3.2.2.6.2.3, D3.2.1.5, D3.2.1.6.1, D3.2.1.6.2, D3.2.2.6.1, D3.2.2.6.2, F3.2.1.5, F3.2.1.6.2, F3.2.2.6.2, H3.1.1

SSP 30219

Revision J 1 May 2008

Space Station Reference Coordinate Systems

A3.1.2, C3.1.2, C3.2.2.9.12.1, D3.1.2, E3.1.2, F3.1.2, G3.1.2, H3.1.2

SSP 30237

Revision T 2 February 2010 References Space Station Electromagnetic Emission and Susceptibility Requirements

C3.2.2.9.18, G3.2.1.9.18

SSP 30238

Rev E 31 July 02

Space Station Electromagnetic Techniques

C3.2.2.9.18, G3.2.1.9.18

SSP 30240

Revision H 15 January 2010

Space Station Program Grounding Requirements

A3.2.1.9.1.2, A3.2.2.9.1.2, C3.2.1.5.2, C3.2.2.5.2, D3.2.1.9.1.2, D3.2.2.9.1.2, F3.2.1.9.1.2, F3.2.2.9.1.2, G3.2.1.5.3, G3.2.2.5.3, H3.2.1.5.4, H3.2.1.9.1.2, H3.2.2.5.3, H3.2.2.9.1.2

SSP 30242

Revision K 10 January 2010 References Space Station Cable/Wire Design and Control Requirements for Electromagnetic Compatibility

A3.2.1.9.1.4, A3.2.2.9.1.4, D3.2.1.9.1.4, D3.2.2.9.1.4, F3.2.1.9.1.4, F3.2.2.9.1.4, H3.2.1.9.1.4, H3.2.2.9.1.4

SSP 30243

Revision N 21 January 2010 References Space Station Requirements for Electromagnetic Compatibility

A3.2.1.9.1.1, A3.2.1.9.1.5, A3.2.1.9.1.6, A3.2.2.9.1.1, A3.2.2.9.1.5, A3.2.2.9.1.6, C3.2.2.9.1.7, D3.2.1.9.1.1, D3.2.2.9.1.5, D3.2.1.9.1.6, D3.2.2.9.1.1, D3.2.2.9.1.5, D3.2.2.9.1.6, F3.2.1.9.1.1, F3.2.2.9.1.1, F3.2.2.9.1.5, F3.2.2.9.1.6, G3.2.1.9.1.7, H3.2.1.9.1.1, H3.2.1.9.1.5, H3.2.1.9.1.6, H3.2.2.9.1.1, H3.2.2.9.1.5, H3.2.2.9.1.6

SSP 30245

Revision P 27 January 2010

Space Station Electrical Bonding Requirements

A3.2.1.9.1.3, A3.2.2.9.1.3, C3.2.1.5.3, C3.2.2.5.3, D3.2.1.9.3, D3.2.2.9.1.3, F3.2.1.9.1.3, F3.2.2.9.1.3, G3.2.1.5.4, G3.2.2.5.4, H3.2.1.9.1.3, H3.2.2.9.1.3

SSP 30256:001

Rev J 17 Oct. 12 References Extravehicular Activity (EVA) Standard Interface Control Document

A3.2.1.1, A3.2.2.1, D3.2.1.2, E3.2.1.2, E3.2.1.3, E3.2.1.4, E3.2.2.2, E3.2.2.3, E3.2.2.3.1, E3.2.2.4, F3.2.1.2, H3.2.1.2

SSP 30258:006

Current Issue References Space Station Program Internal Thermal Control Coldplate Set Standard Interface Control Document C3.2.1.2, C3.2.1.8, C3.2.2.2, C3.2.2.3, C3.2.2.8, C3.2.2.9.5

SSP 30263:001

Current Issue References DC-to-DC Converter Unit External (DDCUE) Standard Interface Control Document A3.2.1.5

SSP 30263:002

Current Issue References Remote Power Controller Module (RPCM) Standard Interface Control Document A3.2.1.5, C3.2.1.5, D3.2.1.5, F3.2.1.5, F3.2.1.5.1.1, H3.2.1.5

SSP 30482, Vol. 1 Rev C, DCN SSCN 2915 7 July 1997 References Electric Power Specifications and Standards Volume 1: EPS Electrical Performance Specifications

A3.2.1.5.1.1, A3.2.2.5.1.1, C3.2.1.5.1.1, D3.2.1.5.1.1, D3.2.2.5.4.1, F3.2.1.5.1.1, F3.2.2.5.1.1, H3.2.1.5.1.1, H3.2.2.5.1.1

SSP 30482, Vol. 2 Rev A, DCN 001, 002, 003, 004, 005, 006, SSCNs 2191, 2130, 2135, 2915 1 Jan 1994 References Electrical Power Specifications and Standards Volume 2: Consumer Constraints

A3.2.1.5.1.1, A3.2.2.5.1.1, C3.2.2.5.1.1, D3.2.1.5.1.1, D3.2.2.5.4.1, F3.2.1.5.1.1, F3.2.2.5.1.1, H3.2.1.5.1.1, H3.2.2.5.1.1

SSP 30512

Rev C 3 Jun 94

Space Station Ionizing Radiation Design Environment

C3.2.2.9.2.0, G3.2.1.9.2.0

SSP 30513

Rev B 3 Jun 94 References Space Station Ionizing Radiation Environment Effects Test and Analysis Techniques

C3.2.2.9.2.0, G3.2.1.9.2.0

SSP 30559

Revision D July 27, 2007

Structural Design and Verification Requirements

C3.2.2.9.12.1, C3.2.2.9.12.2

SSP 42004

Current Issue References Mobile Servicing System (MSS) to User (Generic) Interface Control Document Part 1 1.1.4, D3.1.2, D3.2.1.1.1, D3.2.1.1.2, D3.2.1.2, D3.2.1.3, D3.2.1.3.1, D3.2.1.3.3, D3.2.1.5, D3.2.1.5.2, D3.2.1.6, D3.2.2.1, D3.2.2.2, D3.2.2.3, D3.2.2.3.1, D3.2.2.5, D3.2.2.5.1, E3.1.1

SSP 50002

Rev A, DCN 002

SSCN 4967

20 Oct 00

International Space Station Video Standard

A3.2.1.7.1, A3.2.2.7.1, C3.2.1.7.1, C3.2.2.7.1, C3.2.2.7.2, D3.2.1.7.1, D3.2.2.7.1, F3.2.1.7.1, F3.2.2.7.1, H3.2.1.7.1.1, H3.2.1.7.1.3, H3.2.1.7.2, H3.2.2.7.1.1, H3.2.2.7.1.3, H3.2.2.7.2

SSP 50005

Revision F 15 January 2015 References International Space Station Flight Crew Integration Standard

(NASA-STD-3000/T)

A3.2.1.1, A3.2.2.1, C3.2.1.1, C3.2.2.4, D3.2.1.2, D3.2.2.2, E3.2.2.1, F3.2.1.1, F3.2.2.1, H3.2.1.2, H3.2.2.2

SSP 52051

Revision B January 31, 2013 References User Electric Power Specifications and Standards Volume 1: 120 Volt DC Loads

A3.2.1.5.1.1, A3.2.2.5.1.1

SSQ 21635

Revision N October 22, 2002 References Connectors and Accessories, Electrical, Circular, Miniature, IVA/EVA/Robot Compatible, Space Quality, General Specifications for A3.2.1.4.1, A3.2.2.4, C3.2.1.3, C3.2.2.4, D3.2.1.4.1, D3.2.2.4.1, F3.2.1.4.1, F3.2.2.4.1, H3.2.1.4, H3.2.2.4

SSQ 21653

References Cable, Coaxial, Twinaxial, and Triaxial, Flexible and Semirigid, General Specifications for H3.2.1.7.2

SSQ 21654

References Cable, Single Fiber, Multimode, Space Quality, General Specification for D3.2.1.7, D3.2.2.7, F3.2.1.7, F3.2.2.7, H3.2.1.7, H3.2.2.7

SSQ 21655

Revision H 30 October 2014 References Cable Electrical, MIL-STD-1553, Data Bus, Space Quality, General Specification for

C3.2.1.6.1, F3.2.1.6, F3.2.2.6, G3.2.2.6

TIA/EIA-422

Rev B 13 April 1994 References Electrical Characteristics of Balanced Voltage Digital Interface Circuits

C3.2.1.6.1, C3.2.2.6.1, G3.2.1.6, G3.2.2.6 reference documents The following documents are cited as reference to guide the user in the application of this standard.

SSP 30459

Reference International Space Station Interface Control Plan 1.3

SSP 41000

Reference International Space Station System Specification 1.2

SSP 50098

Reference Robotic Workstation to Space Station Manned Base (SSMB) Interface Control Document, Part 1 C3.2.1.6

REFERENCE DRAWINGS

683-10041 Reference Thermal Control Subsystem Coldplate - Pressurized Modules C3.2.2.9.5

2-5 general

ENGINEERING UNITS AND TOLERANCES

When identified, dimensions in this document are shown first in the English Inch Pound system, and then in the metric equivalent Systems International units (SI) shown in parenthesis. Conversion of units shall be in accordance with ASTM E380, Standard Practice for use of the International System of Units. Unless otherwise specified, all dimensions are in accordance with ANSI-Y-14.5, Dimensioning and tolerancing.

3-1

SECTION A3 SSMB TO MRS BASE SYSTEM (MBS) INTERFACE

A3.0 REQUIREMENTS

A3.1 GENERAL

The MT will interface with the MBS. The MT provides the mobility function for the MBS. Space Station resources are transferred by the MT from the Integrated Truss Assembly (ITA) to the MBS to enable it to perform assembly, servicing, transportation, and deployment functions.

The MBS provides the mechanical and electrical interface with the MT. Mechanical attachments provide a stiff base to transmit loads from the MBS through the MT to the truss. The electrical connections transfer power, data, and video across the MT and MBS interface. The MBS is also equipped with EVA power outlets to interface with EVA tools and lights.

A3.1.1 INTERFACE DESCRIPTION

The SSMB to MBS interfaces consist of structural, mechanical, thermal, environmental, power, data, and video interfaces.

A3.1.2 COORDINATE SYSTEMS

The Space Station integrated stage configurations and elements will be in accordance with the coordinate systems defined in SSP 30219, Space Station Reference Coordinate Systems.

A3.1.3 SSMB INTERFACE FUNCTIONS

The SSMB shall:

The MT shall:

A3.1.4 MBS INTERFACE FUNCTIONS

The MBS shall:

A3.1.5 INTERFACE RESPONSIBILITIES

The interface hardware responsibilities will be as defined in Table A3.1.5-1.

TABLE A3.1.5-1 MT TO MBS INTERFACE HARDWARE RESPONSIBILITIES

- MBS EVA BOLTS (4)

X

- MBS COARSE ALIGNMENT V-GUIDES

X

- MBS FINE ALIGNMENT FEATURES

X

- MBS DATA, VIDEO HARNESSES

X

- MBS MT CAPTURE LATCH

X

- MBS POWER OUTLETS

X

A3.2 INTERFACE REQUIREMENTS

A3.2.1 SSMB INTERFACE REQUIREMENTS

A3.2.1.1 MT HARDWARE ENVELOPES

a) The MT shall provide an EVA and installation envelope for mating the MBS, in accordance with SSP 50005, International Space Station Flight Crew Integration Standard (NASA-STD-3000/T).

b) The MT shall provide attachment mechanisms in accordance with SSP 50005.

c) The MT shall provide EVA translation aids to enable EVA MBS integration in accordance with SSP 30256:001, Extravehicular Activity (EVA) Standard Interface Control Document.

A3.2.1.2 MT MECHANICAL INTERFACES

a) The MT shall provide 4 bolt holes for the MBS.

b) The MT shall provide a capture bar and alignment features to mate the MBS.

c) The MT nuts shall be capable of being engaged/disengaged via EVA using standard EVA tools.

d) The torque required to engage and disengage the attachments bolts shall not exceed 25 ft-lbs (33.89 N-m).

e) The MT shall support a minimum preload of 2000 lbs applied to each of the attachment bolts.

f) The MT shall provide 4 nuts each equipped with a contingency release mechanism for the on orbit removal of the primary MBS/MT interface nut/bolt sets via EVA in the event of a bolt jam.

g) The torque required to remove these nuts by contingency shall not exceed 25 ft-lbs (33.89 N-m).

h) The MT shall provide visual cues for MT/MBS berthing.

A3.2.1.2.1 MT ALIGNMENT TOLERANCE

The MT error (while stationary) from its nominal position with respect to the SS truss reference coordinate axis, at the MBS/MT interface including errors due to MT latching to the SS truss, thermal distortions, and Orbital Replacement Unit (ORU) changeout shall not exceed the values defined in Table A3.2.1.2.1-1.

TABLE A3.2.1.2.1-1 MT STATIONARY ALIGNMENT TOLERANCE

Note: The manufacturing and assembly error of the MT and the interface hardware will be measured on the ground prior to launch. This error will be recorded in the MT and the MRS data base as a fixed error that will be compensated for in positioning the SSRMS or the SPDM.

A3.2.1.3 MT STRUCTURAL INTERFACES

A3.2.1.3.1 MT STIFFNESS REQUIREMENTS

A3.2.1.3.1.1 MT STATIONARY STIFFNESS REQUIREMENTS

The minimum stiffness requirement of the MT during stationary operations at the MBS interface shall be as defined in Table A3.2.1.3.1.1-1.

TABLE A3.2.1.3.1.1-1 MT/MBS (INCLUDING CONTRIBUTION FROM MT AND TRUSS) INTERFACE STIFFNESS FOR STATIONARY MT

Axial X, Y and Z axis 2000 lbs/in (350,400 N/m)

Rotational X, Y and Z axis 26,000,000 in–lbs/rad (2,940,000 Nm/rad)

NOTES: The above stiffness values represent stiffness after free play is overcome.

A3.2.1.3.1.2 MT STIFFNESS REQUIREMENTS DURING TRANSLATION

The minimum stiffness requirement of the MT during translation shall be as defined in Table A3.2.1.3.1.2-1. The stiffness requirements should be satisfied for the following forces and moments: -180 < Fx < +625 lbf, -26 < Fy < +26 lbf, -65 < Fz < +75 lbf; -2,250 < Mx < +2,100 in-lbf, -6,100 < My < +7,000 in-lbf, -3,300 in-lbf < Mz < +2,600 in-lbf; when each component is applied individually to the MT at geometric center of MT/MBS interface.

TABLE A3.2.1.3.1.2-1 MT/MBS (DOES NOT INCLUDE CONTRIBUTION FROM TRUSS) TRANSLATION STIFFNESS REQUIREMENTS

Axial X, and Z 1,000 lbs/in (175,126 N/m)

Translational Y axis 450 lbs/in (78,806 N/m)

Rotational X 15,000,000 in–lbs/rad (1,695,000 Nm/rad)

Rotational Y and Z 17,500,000 in–lbs/rad (1,980,000 Nm/rad)

NOTES: The above stiffness values represent stiffness after free play is overcome.

A3.2.1.3.2 MT LOADS REQUIREMENTS

a) Stationary Loads:

The MT structure when latched at a worksite shall withstand the worst of the following three independent load cases:

b) The MT/MBS interface load spectrum for 15 years life when secured at a worksite shall be as defined below:

There should be no gapping for moments up to 67,250 in-lbf applied in any direction to MT/MBS interface.

c) MT/MBS guide pins and guide pin receptacles shall be designed for local MT to MBS berthing limit loads of + 1065 lbf shear and 1650 lbf axial force per guide pin/receptacle.

d) MT/MBS capture bar and capture latch shall be designed for local MT to MBS berthing limit loads of + 233 lbf shear in Y direction and + 526 lbf shear in Z direction and 539 lbf axial force.

e) MT/MBS corner berthing features shall be designed for local MT to MBS berthing limit loads of 3773 lbf axial force per corner bolt/receptacle.

f) Translational Loads:

During MT translation, MT structure shall withstand the limit loads defined by interaction equations A3.2.1.3.2-1 through 4. The uni-directional limit loads, which are referenced by the below interaction equations, are defined in Table A3.2.1.3.2-1 and represent the maximum loads generated by on-orbit loading environments excluding MT events (loads are applied to the MT at the geometric center of MT/MBS interface).

Equation A3.2.1.3.2-1 Equation A3.2.1.3.2-2

-1 - SINE(F) + SINE(M) 1

Equation A3.2.1.3.2-3

-1 - SINE(F) - SINE(M) + 1

Equation A3.2.1.3.2-4 -1 + 1 Where,

g) The MT/MBS interface load spectrum during translation due to on-orbit loading environments excluding MT events shall be as defined below at the loading conditions calculated in item f.

h) MT structure shall withstand loads generated by MT events which include segment to segment gap crossing, Solar Array Rotary Joint (SARJ) gap crossing, braking, and impact to the End Stop Unit (ESU). MT/MBS loads due to MT events are enveloped by the following two cases:

i) A maximum 37 lbf force vector in XZ plane, or

ii) The resulting load due to instantaneous application of a 150 lbf braking force along Y direction at MT to ITA interface applied at x= -30.33, y= 6.13, and z= -32.70 inch relative to the geometric center of MT to MBS interface. The maximum kinetic energy in this case will be 717 in-lbf which corresponds to 3.1 in/sec velocity for MT with its maximum design payload.

Table A3.2.1.3.2-1 MT/MBS on-orbit uni-directional structural Limit Loads during translation

A3.2.1.3.3 deleted

A3.2.1.4 MT ELECTRICAL INTERFACE HARDWARE

The MT shall provide fixed connectors for the MBS umbilicals to be mated by EVA.

A3.2.1.4.1 ELECTRICAL CONNECTORS

The MT electrical connectors at the interface shall comply with the requirements of SSQ 21635, Connectors and Accessories, Electrical, Circular, Miniature, Intravehicular Activity (IVA)/EVA/Robot Compatible, Space Quality, General Specifications for.

A3.2.1.5 SSMB MT TO MBS ELECTRICAL INTERFACES

a) The SSMB MT to MBS electrical interfaces shall be as shown in Figure A3.2.1.5–1.

b) MT RPCM supplied power shall be available to the MBS when the MT is not in motion and the MSCUTILITY connectors are demated.

c) MT supplied data resources shall be made available to the MBS when powered by either the MSCUTILITY or MT RPCM A3.2.1.5.1 supply power

a) The SSMB MT shall supply power to the MBS through the MSCUTILITYA and MSCUTILITYB power circuits when MT is located at an MSC utility port.

b) The SSMB MT shall supply power to the MBS through the MT RPCM KA A and MT RPCM KA B power circuits when the MT is not in motion and the MSCUTILITY connectors are demated.

A3-3 figure A3.2.1.5-1 MT to MBS Electrical Interfaces A3.2.1.5.1.1 Power Quality

a) The interface power quality for the MSCUTILITYA/B Power circuits, shall be in accordance with SSP 30482, Electrical Power Specifications and Standards, Volume 1: EPS Electrical Performance Specifications; and SSP 30482, Electrical Power Specifications and Standards, Volume 2: Consumer Constraints, Interface B, with a steady state voltage range defined in Table A3.2.1.5-1.

b) The interface power quality for the MT RPCM KA A/B Power Circuits, shall be in accordance with SSP 52051, Volume 1: User Electric Power Specifications and Standards 120 Volt DC Loads, Section 3.1.3.1.3.2, Interface C, (excluding Interface C Source Impedance requirement) with a steady state voltage range defined in Table A3.2.1.5-1 and transient voltage range within the envelope shown in Figure A3.2.1.5.1.1-1 of this document.

Table A3.2.1.5-1 Electrical Interface Parameters

Vrange (volts) Current (amps) Overcurrent Protection

Notes 1,2

MSCUTILITYB

(Final)

Notes 1,2

(Note 5) Note 6

(Note 5) Note 6

Notes:

1. Protection is equivalent with SSP30263:002, Type IV RPCM Standard ICD.

2. Current limiting is equivalent with SSP30263:001, DDCUE Standard ICD.

3. DDCU is current limited to provide 52 amps on a continuous basis; exceeding 52 amps may result in temperature exceedance which would cause DDCU shutdown.

4. Circuits will receive this interface operating current when MT is located on the truss segments inboard of the Solar Alpha Rotary Joint (SARJ) (i.e. S0, S1, S3, P1, P3).

5. Current is shared between MT and MSS.

6. Protection and current limiting is equivalent with SSP30263:002, Type V (12A) RPCM Standard ICD.

FIGURE A3.2.1.5.1.1-1 transient voltage envelope A3.2.1.5.1.2 Fault Protection The SSMB shall provide protection as shown in Table A3.2.1.5-1.

A3.2.1.5.2 deleted A3.2.1.5.3 deleted

A3.2.1.5.4 ELECTRICAL CONNECTOR DEADFACING

The SSMB shall comply with the electrical connector deadfacing requirements as defined in Figure A3.2.1.5.4-1.

FIGURE A3.2.1.5.4-1 CONNECTOR DEADFACING requirements

A3.2.1.5.5 SHIELDING

The MT shields shall be terminated to structure or chassis at each end.

A3.2.1.5.6 REDUNDANCY

a) The MT shall provide a prime and redundant power feed to the MBS when the MT is latched down and the active-to-passive Umbilical Mechanism Assembly (UMA) are mated at an Mobile Servicing Center (MSC) utility port.

b) The MT shall provide a prime and redundant power feed to the MBS when the active-to-passive UMA are de-mated and the MT is not in motion.

c) Each of the power feeds shall have the capability to supply power to the MBS as defined in Table A3.2.1.5–1.

d) The SSMB shall provide the capability to simultaneously provide power on both prime and redundant feeds.

A3.2.1.6 Command and data handling (C&dh) interfaces

a) The MT shall provide the A channel of the MSS local bus (MSS LB) stub and the B channel of the MSS local bus (MSS LB) stub through separate connectors.

b) The SSMB shall provide an extension of the MSS LB to the MT as shown in Figure A3.2.1.6-1.

FIGURE A3.2.1.6-1 MSS LB configuration

A3.2.1.6.1 provide output amplitude SSMB shall provide a signal amplitude of at least 17 volts, peak-to-peak, line-to-line, at the MBS interfaces for messages transmitted on the MIL-STD-1553, (Digital Time Division Command/Response Multiplex Data Bus) bus.

A3.2.1.6.2 MIL-STD-1553 DATA BUS ADDRESSES

The MIL-STD-1553 Bus Addresses for the SSMB Remote Terminals (RTs) on the MSS Local Bus (MSS LB) shall be as defined in Table A3.2.1.6.2-1.

table a3.2.1.6.2-1 Mss lb addresses (2 Pages)

Notes:

1) MBS is located on the MSS local bus after installation.

2) MCAS payloads must use address 21. All other payloads can use any of the payload RT addresses including 21 if an MCAS payload is not present.

A3.2.1.7 SSMB SYNC, CONTROL, AND VIDEO INTERFACES

a) The SSMB shall provide sync, control, and video interfaces to the MBS as shown in Figure A3.2.1.5-1.

b) The MT shall provide two sets of interfaces, each containing three video and two sync copper lines to distribute Pulse Frequency Modulated (PFM) sync and control and to receive PFM video from the MBS.

c) The SSMB shall route one video channel from each set of interfaces to each external video switch (VSW(E)).

d) The MT shall be a pass-through for video.

e) One sync and control signal and two simultaneous video views shall be available after the first video system failure.

f) The sync and control signal transmitted across the interface shall include the camera commands multiplexed on the signal.

A3.2.1.7.1 SSMB VIDEO, SYNC, AND CONTROL TRANSMISSION AND SIGNAL CHARACTERISTICS

a) The SSMB shall transmit PFM sync and control signals and receive PFM video signals from the MBS in accordance with SSP 50002, International Space Station Video Standard, Section 4.2.1.5.4.

b) The SSMB PFM video and PFM sync signal power levels at the MBS/MT interface shall be as defined in Table A3.2.1.7.1-1.

table a.3.2.1.7.1-1 SSMB sync and video power levels

A3.2.1.7.2 deleted

A3.2.1.8 MT THERMAL INTERFACES

The MT shall provide compliance at the interface to ensure that the 4 nuts can align with the four 1/2” (fixed) bolts when the MT and MBS have a temperature difference of not greater than 27.7 degrees Celsius (50 degrees Fahrenheit).

A3.2.1.9 ENVIRONMENTS

A3.2.1.9.1 ELECTROMAGNETIC EFFECTS

A3.2.1.9.1.1 ELECTROMAGNETIC COMPATIBILITY

The SSMB interface with the MBS shall meet the requirements of SSP 30243, Space Station Requirements for Electromagnetic Compatibility.

A3.2.1.9.1.2 GROUNDING

The MT interface shall meet the requirements of SSP 30240, Space Station Grounding Requirements.

A3.2.1.9.1.3 BONDING

a) The MT structural/mechanical interface shall meet the requirements of SSP 30245, Space Station Electrical Bonding Requirements.

b) The MT shall provide a Class H and R bond in accordance with the above referenced document.

A3.2.1.9.1.4 CABLE AND WIRE DESIGN

The MT cable and wire interface shall meet the requirements of SSP 30242, Space Station Cable/Wire Design and Control Requirements for Electromagnetic Compatibility.

A3.2.1.9.1.5 ELECTROSTATIC DISCHARGE

The MT interface shall meet the requirements of SSP 30243.

A3.2.1.9.1.6 CORONA

The MT interface shall meet the requirements of SSP 30243.

A3.2.2 MBS INTERFACE REQUIREMENTS

A3.2.2.1 MBS HARDWARE ENVELOPE

a) The MBS shall provide an EVA and installation envelope for mating to the MT.

b) The MBS shall provide attachment mechanisms in accordance with SSP 50005 for accessibility by EVA crew members.

c) The MBS shall provide EVA translation aids in accordance with SSP 30256:001 to enable EVA MBS integration and translation between elements.

A3.2.2.2 MBS MECHANICAL INTERFACES

a) The MBS shall provide four 1/2” EVA compatible bolts to mate with the MT.

b) The MBS shall provide alignment guides and a capture latch to interface with the MT guide pins and capture bar.

c) The MBS attachment bolts shall be capable of being engaged/disengaged via EVA using standard EVA tools.

d) The torque required to engage and disengage the attachments bolts shall not exceed 25 ft-lbs (33.89 N-m).

e) The MBS shall support a minimum preload of 2000 lbs applied to each of the attachment bolts.

f) The MT Capture Latch on the MBS shall support a preload (with latch closed) between 800 lbs and 1850 lbs.

g) The MBS shall provide the MT/MBS interface umbilicals and the MBS ORU connectors to mate the electrical utilities to the MT.

h) The MBS shall provide visual cues for MT/MBS berthing.

A3.2.2.3 MBS STRUCTURAL INTERFACES

A3.2.2.3.1 deleted

A3.2.2.3.2 MBS LOADS REQUIREMENTS

a) Stationary Loads:

The MBS structure when MT is latched at a worksite shall withstand the worst of the following three independent load cases applied to the MT/MBS interface:

b) The MT/MBS interface load spectrum for 15 years life when secured at a worksite shall be as defined below:

There should be no gapping for moments up to 67,250 in-lbf applied in any direction to MT/MBS interface.

c) MT/MBS guide pins and guide pin receptacles shall be designed for local MT to MBS berthing limit loads of + 1065 lbf shear and 1650 lbf axial force per guide pin/receptacle.

d) MT/MBS capture bar and capture latch shall be designed for local MT to MBS berthing limit loads of + 233 lbf shear in Y direction and + 526 lbf shear in Z direction and 539 lbf axial force.

e) MT/MBS corner berthing features shall be designed for local MT to MBS berthing limit loads of 3773 lbf axial force per corner bolt/receptacle.

f) Translational Loads:

During MT translation, MBS structure shall withstand the limit loads defined by interaction equations A3.2.1.3.2-1 through 4. The uni-directional limit loads, which are referenced by the above interaction equations, are defined in Table A3.2.1.3.2-1 and represent the maximum loads generated by on-orbit loading environments excluding MT events (loads are applied to the MT at the geometric center of MT/MBS interface).

g) The MT/MBS interface load spectrum during translation due to on-orbit loading environments excluding MT events shall be as defined below at the loading conditions calculated in item f.

h) MBS structure shall withstand loads generated by MT events which include segment to segment Gap crossing, SARJ gap crossing, braking, and impact to ESU. MT/MBS loads due to MT events are enveloped by the following two cases:

i) A maximum 37 lbf force vector in XZ plane, or

ii) The resulting load due to instantaneous application of a 150 lbf braking force along Y direction at MT to ITA interface applied at x= -30.33, y= 6.13, and z= -32.70 inch relative to the geometric center of MT to MBS interface. The maximum kinetic energy in this case will be 717 in-lbf which corresponds to a 3.1 in/sec velocity for MT with its maximum design payload.

A3.2.2.3.3 deleted

A3.2.2.4 MBS ELECTRICAL INTERFACE HARDWARE

The MBS electrical connectors at the interface shall comply with the requirements of SSQ 21635.

A3.2.2.5 SSMB MT TO MBS ELECTRICAL INTERFACES

a) The SSMB MT to MBS electrical interfaces shall be as shown in Figure A3.2.1.5−1.

b) The MBS shall provide two EVA power outlets.

A3.2.2.5.1 receive power

a) The MBS shall provide the capability to receive power through the MSCUTILITYA and MSCUTILITYB power circuits when the active–to–passive UMA are mated.

b) The MBS shall provide the capability to receive power through the MT RPCM KA A and MT RPCM KA B power circuits when the active–to–passive UMA are de-mated.

A3.2.2.5.1.1 Power Quality

a) The interface power quality at the MSCUTILITYA/B Power circuits, shall be in accordance with SSP 30482, Electrical Power Specifications and Standards, Volume 1: EPS Electrical performance specifications; and SSP 30482, Electrical Power Specifications and Standards, Volume 2: Consumer Constraints, Interface B, with a steady state voltage range defined in Table A3.2.1.5-1.

b) The interface power quality at the MT RPCM KA A/B Power Circuits, shall be in accordance with SSP 52051, Volume 1: User Electric Power Specifications and Standards, 120 Volt DC Loads, Section 3.1.3.1.3.2, Interface C, (excluding Interface C Source Impedance requirement) with a steady state voltage range defined in Table A3.2.1.5-1 and transient voltage range within the envelope shown in Figure A3.2.1.5.1.1-1 of this document.

A3.2.2.5.2 deleted

A3.2.2.5.3 ELECTRICAL CONNECTOR DEADFACING

The MBS shall comply with the electrical connector deadfacing requirements as defined in Figure A3.2.1.5.4-1.

A3.2.2.5.4 SHIELDING

The MBS shields shall be terminated to structure or chassis at each end.

A3.2.2.5.5 REDUNDANCY

a) The MBS shall receive a prime and redundant power feed from the MT when the MT is latched down and the active-to-passive UMA are mated at an MSC utility port.

b) The MBS shall receive a prime and redundant power feed from the MT when the active–to–passive UMA are de-mated and the MT is not in motion.

c) The MBS shall receive power in accordance with Table A3.2.1.5-1.

A3.2.2.6 C&dh interfaces

a) The MBS shall receive the A channel of the MSS local bus (MSS LB) stub and the B channel of the MSS local bus (MSS LB) stub through separate connectors.

b) The MBS shall receive an extension of the MSS LB from the MT as shown in Figure A3.2.1.6-1.

A3.2.2.6.1 provide output amplitude MBS shall provide a signal amplitude of at least 2.35 volts, peak-to-peak, line-to-line, at the SSMB interfaces for messages transmitted on the MIL-STD-1553 bus.

A3.2.2.6.2 Mil-std-1553 data bus addresses The MIL-STD-1553 bus addresses for the MSS RTs on the MSS Local Bus shall be as defined in Table A3.2.1.6.2-1.

A3.2.2.7 MBS SYNC, CONTROL, AND VIDEO INTERFACES

a) The MBS shall provide sync, control, and video interfaces to the MT as shown in Figure A3.2.1.5-1.

b) The MBS shall receive two sets of interfaces, each containing three video and two sync copper lines to distribute PFM sync and control and to provide PFM video to the MT.

c) The MBS video transmitted across the interface shall include the camera telemetry multiplexed on the video signal.

d) One sync and control signal and two simultaneous video views shall be available after the first video system failure.

A3.2.2.7.1 MBS VIDEO, SYNC, AND CONTROL TRANSMISSION AND SIGNAL CHARACTERISTICS

a) The MBS shall transmit PFM video signals and receive PFM sync and control signals in accordance with SSP 50002, Section 4.2.1.5.4.

b) The MBS PFM video and PFM sync signal power levels at the MBS/MT interface shall be as defined in Table A3.2.2.7.1-1.

table a.3.2.2.7.1-1 mbs sync and video power levels

Note: 1) For the MBS, all measurements are performed at the end of the jumper cable interfacing the MBS to the MT.

A3.2.2.7.2 deleted

A3.2.2.8 MBS THERMAL INTERFACES

The MBS shall support a temperature difference of not greater than 27.7 degrees Celsius (50 degrees Fahrenheit) at the interface to ensure that the 4 nuts can align with the four 1/2” (fixed) bolts.

A3.2.2.9 ENVIRONMENTS

A3.2.2.9.1 ELECTROMAGNETIC EFFECTS

A3.2.2.9.1.1 ELECTROMAGNETIC COMPATIBILITY

The MBS interface with the SSMB shall meet the requirements of SSP 30243.

A3.2.2.9.1.2 GROUNDING

The MBS interface shall meet the requirements of SSP 30240.

A3.2.2.9.1.3 BONDING

a) The MBS structural/mechanical interface shall meet the requirements of SSP 30245.

b) The MBS shall provide a Class H and R bond in accordance with the above referenced document.

A3.2.2.9.1.4 CABLE AND WIRE DESIGN

The MBS cable and wire interface shall meet the requirements of SSP 30242.

A3.2.2.9.1.5 ELECTROSTATIC DISCHARGE

The MBS interface shall meet the requirements of SSP 30243.

A3.2.2.9.1.6 CORONA

The MBS interface shall meet the requirements of SSP 30243.

SECTION B3 DELETED

B3.0 DELETED

B3-1

SECTION C3 USL TO AVU INTERFACE

C3.0 REQUIREMENTS

C3.1 GENERAL

C3.1.1 INTERFACE DESCRIPTION

The USL interface provides structural, mechanical, thermal, environmental, power, data, and video interfaces for the AVU.

C3.1.2 COORDINATE SYSTEMS

The Space Station integrated stage configurations and elements will be in accordance with the coordinate systems defined in SSP 30219.

C3.1.3 USL INTERFACE FUNCTIONS

The USL interface shall:

C3.1.4 AVU INTERFACE FUNCTIONS

The AVU shall:

C3.1.5 INTERFACE RESPONSIBILITIES

The interface hardware responsibilities will be as defined in Table C3.1.5-1.

TABLE C3.1.5-1 AVU TO USL INTERFACE PROVISION RESPONSIBILITIES

USL ColdPlates for AVU

X

USL fastener for AVU Attachment to Rack ColdPlate and Shelf

X

USL interconnecting cables to AVU

X

AVU ORU Guide Rails

X

Note:

1) The hardware responsibilities above applies to both CSA AVU interfaces with the USL racks. Both LAS-5 and LAP-5 USL racks will be outfitted with an AVU.

C3.2 INTERFACE REQUIREMENTS

C3.2.1 USL INTERFACE REQUIREMENTS

C3.2.1.1 USL HARDWARE ENVELOPES

The USL shall contain two equipment rack locations for the AVU. The USL shall support the AVU envelopes as defined in Figure C3.2.1.1-1 and C3.2.1.1-2.

figure C3.2.1.1-1 AVU ENVELOPES figure c3.2.1.1-2 Hard drive envelope

C3.2.1.2 USL MECHANICAL INTERFACES

The USL shall provide mechanical interfaces for the AVU as defined in SSP 30258:006, Space Station Program Internal Thermal Control Coldplate Set Standard Interface Control Document, Section 3.4.1, ORU to Coldplate Installation and Section 3.4.3, Surface Finish. The USL shall provide coldplate interfaces to the AVU as defined in SSP 30258:006, Figure B-8 (Boeing Part Number 683-10041-8). The USL Rack fasteners shall interface to AVU threaded inserts as defined in Figure 3.2.2.2-1 (actual fastener usage may be reduced if thermal transfer and structural adequacy is insured).

C3.2.1.3 USL STRUCTURAL INTERFACES

The single point fastener maximum limit load for combined high and low frequency load case are shown below

C3.2.1.4 ELECTRICAL CONNECTORS

The USL electrical connectors at the interface shall comply with the requirements of SSQ 21635.

C3.2.1.5 power INTERFACES The USL to AVU power interfaces shall be as shown in Figure C3.2.1.5-1.

figure c3.2.1.5-1 USL TO AVU ELECTRICAL INTERFACE DIAGRAM C3.2.1.5.1 supply power The USL shall supply power to the primary AVU (LAS5) through the AVU2 power circuits. The USL shall supply power to the secondary AVU (LAP5) through the AVU1 power circuit.

C3.2.1.5.1.1 power quality Power quality shall be in compliance with “interface C” as defined in SSP 30482, Volume I.

C3.2.1.5.1.2 fault protection The USL shall provide protection as shown in Table C3.2.1.5-1.

Table C3.2.1.5-1 USL to AVU Electrical Interface Parameters

Circuit Name

INTERFACE

Vrange (volts) Operating Current (amps)

Overcurrent Protection

C3.2.1.5.2 grounding The USL grounding interface shall meet the requirements…