SSP_41160-RevH.docx

SSP 41160

Revision H European Space Agency Segment Specification for Columbus

International Space Station Program

Revision H

30 June 2015

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

SSP 41160

REVISION AND HISTORY

REVISION AND HISTORY - Continued

REVISION AND HISTORY - Continued

REVISION AND HISTORY - Continued

REVISION AND HISTORY - Continued

SCN 138 (SSCN 008060)

SCN 135 (SSCN 008719)

SCN 141 (SSCN 008939)

SCN 140 (SSCN 009086)

SCN 137 (SSCN 009312)

Revision G incorporates SSCNs 002664, 006771, 008060, 008719, 008939, 009086, 009312.

The following SCNs have been cancelled. The content of the SSCNs authorizing release of the SCNs has been incorporated into Revision H.

SCN 143 (SSCN 009111)

SCN 150 (SSCN 009415)

SCN 142 (SSCN 009540)

SCN 144 (SSCN 009864)

SCN 145 (SSCN 009993)

SCN 147 (SSCN 010119)

SCN 149 (SSCN 010445)

SCN 146 (SSCN 010782)

SCN 152 (SSCN 011768)

SCN 151 (SSCN 012037)

SCN 155 (SSCN 012597)

SCN 153 (SSCN 012713)

SCN 154 (SSCN 012906)

Revision H incorporates SSCNs 009111, 009415, 009540, 009864, 009993, 010119, 010445, 010782, 011768, 012037, 012597, 012713, 012906, 013515, 013845, and 015127.

SSP 41160

PREFACE

This SSP 41160, Segment Specification establishes the performance and design requirements for the European Space Agency Segment. Any changes to this document will be approved bilaterally by NASA and ESA Program Managers.

INTERNATIONAL SPACE STATION PROGRAM

European Space Agency Segment Specification for Columbus

CONCURRENCE

30 June 2015

SSP 41160

Revision H

TABLE OF CONTENTS

APPENDIX

TABLE

FIGURE

SCOPE

This specification and the Space Station Manned Base (SSMB) to Attached Pressurized Module (APM) Interface Requirements Document (IRD) and the International Standard Payload Rack (ISPR) IRD establish the performance and design requirements for the European APM. This specification has been developed using paragraphs from the Joint Program Definition and Requirements Document (JPDRD), JESA 30000, section 3 and section 6, with an outline from SSP 41171 (MIL-STD-490) as a guide. The paragraph headers in section 3.2.1 are based on the functional decomposition allocations to the APM in the International Space Station System Specification, SSP 41000, section 3.7.3. The requirements in section 3.2.1 of this specification define the performance of the APM. Requirements in section 3.2.2 through 3.6 are constraints with which the APM must comply.

The APM has been officially renamed to Columbus Module. For the sake of keeping the naming in the requirements documentation consistent, this Segment Specification continues to use the name APM.

Identification.

Not applicable.

System overview.

The APM is a facility developed by the European Space Agency (ESA) for the purpose of supporting microgravity research in an earth orbit as a segment of the International Space Station. The APM supports internally and externally mounted user payloads.

applicable DOCUMENTS Government documents.

The following documents of the exact issue shown form a part of this specification to the extent specified herein. In the event of conflict between the text of this specification and references cited herein, the text of this specification takes precedence. Nothing in this specification, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.

Specifications, standards, and handbooks.

The following specifications, standards, and handbooks form a part of this document to the extent specified herein. Unless otherwise specified, the exact issue shown applies to this segment specification.

SPECIFICATIONS

NASA

SSP 30219

Rev. H, DCN 006 June 1, 2005 Space Station Reference Coordinate Systems (Reference Table-IV-A, Table IV-B)

SSP 30233

Rev. H August 21, 2007 Space Station Requirements for Materials and Processes (Reference paragraphs 2.4, 3.3.1.3.2)

SSP 30312

Rev. H, DCN 001, 002, 003 November 22, 1999 EEE and Mechanical Parts Management and Implementation Plan (Reference paragraphs 3.3.6.8.1.2, 3.3.18.1, Figure 3)

SSP 30423

Rev. H January 15, 2000 Space Station Approved Electrical, Electronic, and Electromechanical Parts List (Reference paragraphs 3.3.1.4, 3.3.18.1)

SSP 30425

Rev. B February 8, 1994 Space Station Program Natural Environment Definition for Design (Reference paragraphs 3.2.6.1.2, 3.2.6.1.3, 3.2.6.1.4, 3.2.6.1.6, 3.2.6.1.7, 3.2.6.1.8)

SSP 30426

Rev. D, DCN 001 January 21, 1994 Space Station External Contamination Control Requirements (Reference paragraphs 3.3.10.3, 6.1)

SSP 30482 Volume 1 Rev. C, SCN 003, TBD (2915) July 7, 1997

Electric Power Specifications and Standards Volume 1: EPS Electrical Performance Specifications (Reference paragraphs 2.4, 3.2.1.1.1.29) Note: SCN 003 (1314) and TBD (2915) unilaterally approved by NASA as no impact to SSP 41160.

SSP 30482 Volume 2 Rev. A, DCN-001, 002, 003, 004 January 1, 1994 Electric Power Specifications and Standards Volume 2: Consumer Constraints (Reference paragraphs 2.4, 3.2.1.1.1.29)

SSP 30512

Rev. C June 3, 1994 Space Station Ionizing Radiation Design Environment (Reference paragraph 3.2.6.1.5)

SSP 30558

Rev C, DCN TBD (2611) August 24, 2001 Fracture Control Requirements for Space Station (as called up in COL-ESA-RQ-008) (Reference paragraphs 2.4, 3.3.6.4.1, 3.3.12.1)

SSP 30559

Rev. D July 27, 2007 Structural Design and Verification Requirements (as called up in COL-ESA-RQ-001) (Reference paragraph 3.3.12.1)

SSP 30560

Rev. A May 5, 2003 Glass, Window, and Ceramic Structural Design and Verification Requirements (as called up in COL-ESA-RQ-001) (Reference paragraph 3.3.12.1) Note: DCN 003 (3660) unilaterally approved by NASA as no impact to SSP 41160.

SSP 30573

Rev. E December 2, 2009 Space Station Program Fluid Procurement and Use Control Specification (Reference paragraph 3.3.12.2.1)

SSP 30575

April 2007 Space Station Interior and Exterior Operational Location Coding System (Reference paragraphs 3.3.7.5, Table VII-D)

SSP 41002

Current Issue International Standard Payload Rack to NASA/ESA/NASDA Modules Interface Control Document (Reference paragraph 3.1.5.1.7)

SSP 42001

Space Station Manned Base to Columbus Attached Pressurized Module Interface Control Document (Reference paragraph 3.1.5.1.7, Table II)

SSP 50005

June 30, 2006 International Space Station Flight Crew Integration Standard (NASA-STD-3000/T) (Reference paragraphs 2.4, 3.3.6.6.1, 3.3.6.8.2, 3.3.6.12.4.1, 3.3.6.12.5, B.3.3.6.8.2)

SSP 50014

September 3, 1997 International Space Station Utility Coding Specification (Reference paragraph 3.3.3.8)

SSP 50038

November 17, 1995 Computer Based Control System Safety Requirements (Reference paragraphs 2.4, 3.3.6.3)

SSP 50184

May 25, 2001 High Rate Data Link Physical Media, Physical Signaling and Protocol Specification (Reference paragraph 3.2.2.5)

SSP 50251

Rev. B, IRN 0005 May 30, 2003 ARIS to Pressurized Element Interface Control Document, Part I (Reference paragraph 3.2.2.8)

ESA

COL-ESA-RQ-001

Space Segment Volume 1, Issue 4 Rev. A December 10, 2001 Columbus System Requirements Document (CSRD) (Reference paragraphs 2.4, 3.3.1.3, 3.3.1.4, 3.3.6.3, 3.3.12.1, 3.7.1, 4)

COL-ESA-RQ-004

Issue 2 Rev. A March 11, 1996 Columbus Product Assurance Requirements (Reference paragraphs 2.4, 3.3.1.3, 4, Figure 3)

COL-ESA-RQ-013

Issue 3 Rev. G May 8, 2000 Columbus Human Factors Engineering Requirements (Reference paragraphs 2.4, 3.3.3.6, 3.3.6.8.2, Table VII-D, 3.3.7, 3.3.7.1, 3.3.7.2.1, 3.3.7.2.2, 3.3.7.2.3, 3.3.7.4, 3.3.7.6, 3.3.7.7, 3.3.7.8, 3.5.1.2, B.3.3.6.8.2)

COL-ESA-RQ-014

Rev. D May 8, 2000 Columbus EMC and Power Quality Requirements (Reference paragraphs 2.4, 3.2.1.1.1.29, 3.3.2.1, 3.3.14)

MS-ESA-HB-013

Issue 1 Rev. C May 8, 2000 Manned Space Flight Human Factors Engineering Handbook (Reference paragraphs 3.3.6.6.1, 3.3.6.12.3.1, 3.3.6.12.4.1, 3.3.6.12.5)

MS-ESA-RQ-023

Rev. D February 5, 1999 Software and Protocols Standard (Reference paragraphs 2.4, 3.3.6.3, 3.3.7)

STANDARDS

MILITARY

MIL-STD-1246

September 4, 1987 Product Cleanliness Levels and Contamination Control Program (Reference paragraph 3.3.10.3)

MIL-STD-1553

Rev. B, Notice 2 September 8, 1986

Digital Time Division Command/Response Multiplex Data Bus (Reference paragraph 3.3.19)

NASA

SSP 30550

Volume I, Rev. C, DCN 002 September, 1998 Space Station Program Robotics Systems Integration Standards Volume I: Robotic Accommodation Requirements (Reference paragraph 3.3.11)

(Unless otherwise indicated, copies of United States (U.S.) federal and military specifications, standards, and handbooks are available from the Standardization Documents Order Desk, Building 4D, 700 Robbins Avenue, Philadelphia, PA 19111-5094.)

Other Government documents, drawings, and publications.

The following other government documents, drawings, and publications form a part of this document to the extent specified herein. Unless otherwise specified, the exact issue shown applies to this segment specification.

OTHER GOVERNMENT DOCUMENTS

NASA

ICD-A-21396

Orbiter/Columbus Elements Interfaces (Reference paragraph 3.2.7)

ISO/IEC 8802-3:

2000(E), IEEE Std 802.3., 2000 Edition, sections 14/21 Information Technology - Local and Metropolitan Area Networks - Part 3: Carrier Sense Multiple Access with Collision Detection (CSMA/CD) Access Method and Physical Layer Specification (Reference paragraph 3.2.2.5)

KHB 1700.7

September 30, 1992 Space Shuttle Payload Ground Safety (Reference paragraphs 3.3.6.14, 5.1)

NHB 6000.1

Rev. D September 1, 1990 Packaging, Handling and Transportation for Aeronautical and Space Systems Equipment, and Associated Components, Requirements For (Reference paragraph 5.1)

NHB 8060.1

April 2, 1991 Flammability, Odor, and Offgassing Requirements and Test Procedures for Materials in Environments that Support Combustion (Reference Figure 3)

NSTS 07700

ICD 2-19001

Rev. K, CN 01, 02, up to and including IRN 369 December 17, 1993 Handbook Volume XIV/Shuttle Orbiter/Cargo Standard Interfaces (Reference paragraph 3.3.6.12.3.1)

NSTS 21000-IDD-ISS

Rev. A, change packages 009 through 049 February 18, 1998 International Space Station Interface Definition Document (Reference paragraphs 3.3.6.13.6.4, 3.3.6.13.7, 3.3.6.13.8, 3.3.11)

NSTS 37329

Rev. B, Change 3 October 18, 2004 Structural Integration Analyses Responsibility Definition for Space Shuttle Vehicle and Cargo Element Developers (Reference paragraph 3.3.12.5)

PSS-01-301

April 1992 Derating Requirements Applicable to Electronic, Electrical, and Electro-mechanical Components for ESA Space Systems (Reference paragraph 3.3.6.8.1.2)

PSS-01-702

Thermal Vacuum Test for the Screening of Space Materials (Reference paragraph 3.3.10.3)

SSP 41150

Interface Requirements Document United States On-orbit Segment (USOS) to Columbus Attached Pressurized Module (APM) (Reference paragraphs 3.1.5.1.1, 3.2.1.1.1.17, 3.2.1.1.1.29, 3.2.1.1.1.49, 3.2.1.1.1.50, 3.2.1.1.1.54, 3.2.1.1.1.55, 3.2.1.3.8, 3.2.1.3.9, 3.2.4.13.2, 3.3.11.2, 3.3.12.3, 3.3.17, 3.3.18.4, 3.3.19, Tables IV-C, IV-D)

SSP 41152

Interface Requirements Document International Standard Payload Rack (ISPR) (Reference paragraph 3.2.2.7)

SSP 42004

Rev. K June 3, 2013 Mobile Servicing System (MSS) to User (Generic) Interface Control Document Part I (Reference paragraphs 3.1.5.1.2, 3.3.11)

SSP 50036

April 15, 2003 Microgravity Control Plan (Reference paragraph 3.2.1.1.4.1)

SSQ 26000

Rev. Basic October 16, 1996 Space Station Program Office Standard Repair for Sharp Edges on SSQ 21635 NZGL Type Connector Assemblies and Components (Reference paragraph 3.3.6.12.3.1)

Nongovernment documents.

None

Order of precedence.

In the event of a conflict between the text of this specification and references cited herein, the text of this specification takes precedence. Nothing in this specification, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.

Meet or exceed.

All ESA documents applicable in this document have undergone an extensive “Meet-or-Exceed” process between ESA and National Aeronautics and Space Administration (NASA). The relationship from the NASA to the ESA requirements is established through a detailed traceability matrix as Annex 1 to JESA 30000, section 3, revision B (Change B4).

The following documents have undergone the “Meet-or-Exceed” process:

SSP 41160

Revision H

SYSTEM REQUIREMENTS

System definition.

The APM is comprised of a pressurized module used for the conduct of experiments.

System description.

APM.

The APM is a facility developed by ESA for the purpose of supporting microgravity research in an earth orbit as a segment of the International Space Station (ISS). The APM supports internally and externally mounted user payloads. The main purpose of the APM is to support microgravity research in a laboratory environment as a part of the on-orbit Space Station. The Columbus architecture for launch is “scarred” for uplink/downlink capability and external accommodations of the Communication Terminal (CT).

Missions.

The mission of the APM is to perform engineering research, conduct scientific experiments in an international, Earth orbiting, research facility in a microgravity environment at a nominal orbit of 220 nautical miles at 51.6 degree inclination. This mission’s definition is discussed in detail in document SSP 50011-01.

Threat.

Not applicable.

Deleted.

FIGURE 1. Deleted Interface requirements.

External interfaces.

The following subparagraphs identify the external interfaces of the APM. The external interfaces of the APM are shown in Figure 2.

FIGURE 2. APM external interfaces United States On-orbit Segment (USOS) external interface descriptions.

The APM interface with the USOS consists of structural/mechanical and utility connections. At this interface the APM receives electrical power and gaseous nitrogen from the USOS; shares data, thermal energy, video, audio, atmosphere, structural/mechanical, loads and vibrations with the USOS; and returns water to the USOS. This interface is applicable during all modes defined by the perform mission on-orbit states. The USOS to APM physical and functional interfaces are described in SSP 41150, Interface Requirements Document United States On-orbit Segment (USOS) to Columbus Attached Pressurized Module (APM).

Canadian Mobile Servicing System external interface descriptions.

The APM interface with the Mobile Servicing System (MSS) consists of mechanical and utility connections. These interfaces permit the MSS Space Station Remote Manipulator System (SSRMS) to translate and position the APM, and to provide necessary “keep alive” utilities. MSS interfaces also allow the use of Special Dexterous Manipulator (SPDM) for external payloads installation and operations on the APM External Payloads Facility. At the interface the APM can receive power and data, and shares a mechanical interface, loads, and vibrations. This interface is applicable during unberthed survival modes for SSRMS interfaces, and nominal operational modes for SPDM interfaces. The MSS to APM physical and functional interfaces are described in SSP 42004, Mobile Servicing System (MSS) to User (Generic) Interface Control Document Part I.

Deleted.

Deleted.

Orbiter external interface description.

The APM interface with the Orbiter consists of mechanical connections. This interface is applicable to the transport of the APM by the Orbiter. The APM to Orbiter physical and functional interfaces will be defined in a mission unique Interface Control Document (ICD) developed from NSTS 21000-IDD-ISS, International Space Station Interface Definition Document.

Launch/landing site support facilities external interface description.

For launch of APM equipment and payloads by the Orbiter, the NASA launch/landing site support facilities are used. The detailed requirements for these physical and functional interfaces are defined in SID 82K0076.

User payloads external interface description.

The APM interface will consist of the areas needed to support user payloads. The APM interface to internal user payloads is defined in SSP 41002, International Standard Payload Rack to NASA/ESA/NASDA Modules Interface Control Document.

The APM interface to external user payloads is defined in SSP 42001, Space Station Manned Base to Columbus Attached Pressurized Module Interface Control Document.

Deleted.

Crew external interface descriptions.

The APM interfaces with the crew to allow the monitoring and control of user payloads, conduct of scientific experiments, and to perform maintenance tasks. The crew interfaces with the APM, as a segment of the International Space Station, are described in SSP 50011-01.

Characteristics.

Performance characteristics.

State: Perform mission - On-orbit.

A stable condition of the Space Station defined by the provision of unique station modes to support the accomplishment of mission objectives.

Mode: Standard.

This mode represents the core operations of the Space Station when it is tended or preparing to support a human presence. The vehicle actively determines and controls its attitude non-propulsively. This mode provides a “shirt sleeve” environment for the crew. Both internal and external user payload operations are being supported, monitored, and controlled. The crew can perform Intravehicular Activity (IVA) maintenance actions. The functional capabilities for this mode are in the following paragraphs.

Capability: Relieve overpressure.

When isolated, the APM shall control the maximum internal-to-external differential pressure to less than the maximum design pressure of the APM. Venting of atmosphere to space shall initiate at no less than 15.05 psid (1037 hPa) and shall stop at a pressure of no less than 14.4 psid (993 hPa).

Capability: Control atmosphere temperature.

The APM shall control the atmosphere temperature in the APM cabin aisleway within the range of 65-80 degrees F. The APM atmosphere temperature setpoint shall be selectable by the flight or ground crew and the setpoint controlled within +/-2 degrees F.

Capability: Control atmosphere moisture.

The APM shall maintain the atmosphere dewpoint in the APM cabin aisleway within the range of 40-60 degrees F.

Capability: Circulate atmosphere.

The APM shall maintain an effective atmosphere velocity in the APM cabin aisleway within the range of 15-40 ft per minute.

Capability: Control internal lighting.

The APM shall control internal lighting levels. The APM shall provide centralized and localized lighting control.

Capability: Illuminate internal area.

The APM shall illuminate the interior of the APM in support of system operation and conduct of experiments.

Capability: Illuminate video area - external.

Markings and lights shall be provided to support computer vision and other vision requirements for APM maintenance.

Capability: Isolate to recovery level.

The APM shall isolate detected failures to the functional recovery level for those functions requiring automatic recovery identified in Table I, column 3.

TABLE I. On-orbit APM functions requiring automatic FDIR capabilities

Assessment (2) Automatic Isolation (3)

Control internal lighting

Illuminate internal area

Illuminate video area-external

Respond to hazardous atmosphere

Control airborne particulate contaminants

Control airborne microbial growth

Provide remote visual access

Transmit voice communication

Receive voice communication

Limit accelerations

Deleted.

Capability: Isolate for safing.

The APM shall isolate to the safing level detected hazards that may manifest a catastrophic or critical hazard.

Capability: Safe.

The APM shall safe, in less than the time to catastrophic or critical effect, any hazard that may manifest a catastrophic or critical hazard.

Capability: Provide data to crew.

The APM shall accommodate the crew control interface to provide data to the crew when crew members are present in the APM.

Capability: Accept crew inputs and commands.

The APM shall accommodate the crew control interface for accepting crew inputs and commands when crewmembers are present in the APM.

Capability: Generate functional data.

The APM shall generate data related to performance, configuration, status, failures, and hazards of the APM functions listed in Table I, column 1.

The APM shall support a standard scheme by which air samples may be acquired by the USOS for analysis.

The APM shall provide data to periodically confirm the operational readiness of fire protection (FP) equipment, including suppressant quantity.

Capability: Assess functional data.

The APM shall assess the acquired data to determine APM function status and to detect the occurrence of pre-defined failures within the APM requiring crew or on-orbit automated response, as identified in Table I, column 2. The APM shall assess the acquired data to detect the occurrence of predefined hazards within the APM requiring crew or on-orbit automated response. The APM shall classify each abnormal event as an Emergency, Warning or Caution alarm event. If an APM alarm event occurs, the USOS shall be notified to annunciate the appropriate Space Station alarm.

Deleted.

Capability: Respond to fire.

The APM shall detect a fire event in locations in accordance with the selection criteria in Figure 3 and in the open cabin volume. The APM shall isolate a fire event within 30 seconds of detection, including removal of power and forced airflow at the affected location, in locations in accordance with the selection criteria in Figure 3. The APM shall accommodate Portable Breathing Apparatuses (PBAs) and provide Portable Fire Extinguishers (PFEs).

FIGURE 3. Fire protection selection criteria

FIGURE 3. Fire protection selection criteria - Continued

FIGURE 3. Fire protection selection criteria - Continued

FIGURE 4. Deleted

FIGURE 5. Deleted The APM shall initiate a message, with event location data, to the USOS for a detected fire event in accordance with SSP 41150, paragraph 3.1.5.3. The APM shall visually indicate a fire event at the detection location requiring smoke detection in accordance with the selection criteria in Figure 3. The APM shall terminate forced air circulation between adjacent elements within 30 seconds of generations of a fire event message and close intermodule ventilation valves within 1 minute of annunciation of a Class 1 fire alarm or command from the USOS.

Fixed fire suppression, where installed, shall complete application of fire suppressant within 1 minute of initiation. The APM fire suppression shall reduce the oxygen concentration at the fire event location to less than 10.5 percent by volume within 1 minute of suppressant discharge. The APM shall have fixed fire suppression in locations in accordance with the selection criteria in Figure 3. Fixed fire suppression, where installed, shall have remote activation capability. When initiated by commands from the USOS, the APM shall vent its atmosphere to space to achieve an oxygen partial pressure less than 1.0 psia within 10 minutes.

The APM shall be capable of restoring the habitable environment after a fire event by equalization with Node 2.

Capability: Respond to hazardous atmosphere.

When initiated by the crew or ground, the APM shall vent the atmosphere of the APM to space to achieve pressure of less than 0.4 psia within 24 hrs.

The APM shall isolate for a hazardous atmosphere by termination of forced air circulation between adjacent elements within 30 seconds and closure of intermodule ventilation valves within 1 minute upon command from the USOS.

Capability: Distribute user payload power.

The APM shall distribute power to payload locations as shown in Table II.

TABLE II. Standard payload location services

Space Station Payload Location Services (minimum)

Internal Payload Locations

APM

External Payload Locations

Vacuum Services

Inter-payload location communications data

Gases

Capability: Perform user payload thermal conditioning.

The APM shall perform thermal conditioning for payload locations as shown in Table II.

Capability: Supply vacuum services to user payloads.

The APM shall supply vacuum services to payload locations as shown in Table II.

Capability: Distribute gases to user payloads.

The APM shall distribute gases to payload locations as shown in Table II.

Capability: Transfer user payload command and control data.

The APM shall transfer data for command and control to and from payload locations as shown in Table II.

Capability: Support user payload telemetry services.

The APM shall transfer user payload data for telemetry from payload locations as shown in Table II.

Capability: Support user payload video services.

The APM shall transfer data for video to and from payload locations as shown in Table II.

Capability: Command onboard processes.

The APM shall provide automated command and control of payloads and systems supporting payloads.

Capability: Accommodation of Local Area Network Hub.

The APM shall accommodate a NASA provided U.S. Payload Local Area Network (LAN) Hub (PEHG) to support U.S. Payload LAN extension in the APM.

Deleted.

Capability: Distribute power.

The APM shall distribute electric power for sustaining operations to electrical power consuming equipment (EPCE) with Power Quality in accordance with SSP 30482, Electric Power Specifications and Standards Volume 1: EPS Electrical Performance Specifications, Volume 1 or COL-ESA-RQ-014, Columbus EMC and Power Quality Requirements.

The APM shall operate on electric power as allocated in Table III.

TABLE III. APM power allocations, distribution, and housekeeping

(kilowatts) Input Power Distribution Capacity (kilowatts) (2) Housekeeping Power Maximum Allocation (kilowatts) (1)

The APM shall interface with the USOS in accordance with SSP 41150 for electrical power.

The APM electrical power consuming equipment shall comply with the requirements of SSP 30482, Electric Power Specifications and Standards Volume 2: Consumer Constraints, Volume 2 or COL-ESA-RQ-014.

Capability: Collect thermal energy.

The APM shall collect thermal energy to maintain thermal conditioning of the APM.

Capability: Distribute thermal energy.

The APM shall transfer no more than 22 kW of thermal energy to USOS.

Capability: Provide time interface.

The APM shall distribute time to payloads through the payload MIL-STD-1553 bus to locations as specified in Table II.

Deleted.

Capability: Support internal crew restraint and mobility.

The APM shall support internal crew translation. Minimum interior cross section dimensions of 50 inches shall be maintained throughout the APM to support crew translation. Handholds and handrails shall be incorporated into the interior arrangement of pressurized volumes to facilitate crew mobility and stability. The APM shall include a means of maintaining internal crew body position as necessary to accomplish nominal, maintenance, or emergency tasks. The APM shall include a means of providing both “float up” temporary restraint as well as firm, fixed restraint.

Capability: Control airborne particulate contaminants.

The APM shall limit the average atmosphere particulate level of the APM atmosphere compliant with class 100,000 clean room requirement.

Capability: Control airborne microbial growth.

The APM shall limit the daily average airborne microbes in the APM atmosphere to 1000 Colony Forming Units per cubic meter.

Capability: Provide direct visual access.

The APM shall provide internal direct visual access of adjacent station habitable volumes to the crew.

Capability: Provide remote visual access.

The APM shall provide remote internal visual access of APM pressurized volume to crew and ground.

Capability: Transmit voice communication.

The APM shall support internal voice communication transmission between crewmembers in the APM and to crewmembers in other locations of the Space Station.

Capability: Receive voice communication.

The APM shall support internal voice communication reception between crewmembers within the APM and crewmembers in other locations in the Space Station.

Capability: Support uplinked data.

Capability: Provide data for downlink.

The APM shall acquire audio and video, and digital data designed for the ground from sources within the APM. The APM shall send audio and video and digital data destined for the ground to the USOS via the interface between the segments for further processing or to the CT.

Deleted.

Deleted.

Capability: Support internal equipment translation.

Items that require moving in the Space Station shall have built-in handles or structural or mechanical parts suitable for gripping and tethering or the capability to interface with portable handholds.

Capability: Support internal equipment removal and replacement.

The APM shall restrain crew and equipment to support removal and replacement of Orbital Replaceable Units (ORUs) and to perform in situ maintenance.

Deleted.

Deleted.

Capability: Maintain station mode.