SSP_50670-Rev_A-DCN001-Collated_Master.doc

SSP 50670

Revision A

JSC XXXXX

Release Date

Advanced Resistive Exercise Device (ARED) to the International Space Station Interface Control Document International Space Station Program Revision A Incorporates DCN 001 March 2008

REVISION AND HISTORY PAGE

A

Initial Release (Reference per SSCD 010984, EFF. 03-02-08) Revision A (Reference per SSCD 010584, EFF. 05/02/08)

DCN 001 (Reference per SSCD 011074, EFF. 05/19/08)

03-26-08 05-13-08

07-03-08

PREFACE

Advanced Resistive Exercise Device (ARED) to the International Space Station Interface Control Document This document defines all the interface requirements to be met by the ARED during launch and on-orbit use.

This document is developed and maintained by the ARED Project, EA3. The initial baseline release is under the control of the Space Station Program Control Board (SSPCB)/Space Station Control Board (SSCB). The SSPCB/SSCB delegates control and approval authority via SSCN 010984 for future updates and/or revisions to the Vehicle Control Board.

International Space Station Program

Advanced Resistive Exercise Device (ARED) to the International Space Station

Interface Control Document

Concurrence

March 2008

International Space Station Program

Advanced Resistive Exercise Device (ARED) to the International Space Station

Interface Control Document

LIST OF CHANGES

June 2008 All changes to paragraphs, tables, and figures in this document are shown below:

SSPCB

Entry Date

Change

Paragraph(s)

March 2008

Baseline

All

May 2008

Revision A

All

June 2008

DCN 001

Table of Contents

11.

INTRODUCTION

11.1 Purpose and Scope

11.2 Responsibility and Change Authority

22.

APPLICABLE AND REFERENCE DOCUMENTS

22.1 Applicable Documents

32.2 Reference Documents

32.3 Order of Precedence

43.

INTERFACES

43.1 General

43.1.1 System Description

53.1.1.1 Structural

53.1.1.2 Power

63.1.1.3 Data

63.1.1.4 Stowage

63.1.2 Coordinate System

63.1.3 Engineering Units, Tolerances, and Conversions

63.1.4 Interface Responsibilities

63.1.4.1 Responsibility for ARED Interfaces

63.1.4.2 Responsibility for ISS Interfaces

63.2 Interface Requirements

63.2.1 Envelope

63.2.1.1 Envelope Definitions

83.2.1.2 Detailed Specifications

83.2.1.3 Transfer Configuration Dimensions

83.2.1.4 Visibility and Access to Critical Equipment and Controls

83.2.1.5 Translation Paths

103.2.2 Mass Properties

103.2.2.1 On-Orbit ARED Mass

103.2.2.2 On-Orbit Spares Mass

113.2.3 Structural/Mechanical

113.2.3.1 Functional Characteristics

163.2.4 Electrical (Power)

163.2.4.1

163.2.4.2

173.2.5 Electronic (Signal)

173.2.6 Software and Data

183.2.7 Environmental

183.2.7.1

183.2.7.2

List of Tables

19Table 3.2.7-1: Micro-gravity Limits

List of Figures

4Figure 3.1-1: ARED Interface Diagram

5Figure 3.1.1-1: Advanced Resistive Exercise Device

7Figure 3.2.1-1: Orientation of ARED in Node 1

9Figure 3.2.1-2: Node 1 Sand Volume – Port Side

10Figure 3.2.1-3: Node 1 Sand Volume – Starboard Side

12Figure 3.2.3-1: Node 1 Model – Facing Aft (into FGB)

13Figure 3.2.3-2: Node 1 Model – Facing Forward (into Lab)

14Figure 3.2.3-3: Zenith Seat Track Attachment Envelope

15Figure 3.2.3-4: Seat Track Limit Loads Orientation

15Figure 3.2.3-5: Light Bar Mounting Locations for ARED

16Figure 3.2.4-1: ISS-to-ARED Electrical Power Interface Description

17Figure 3.2.4-2: ARED Power Supply Location

19Figure 3.2.7-1: Micro-gravity Limits

Appendices

21Appendix A - Acronyms and Abbreviations

21Appendix B - Definition of Terms / Notes (Reserved)

1. INTRODUCTION

1.1 Purpose and Scope

This Interface Control Document (ICD) defines and controls the interface requirements between the Advanced Resistive Exercise Device (ARED), developed by EA3, and Node 1 managed by the International Space Station (ISS) Program Vehicle Office. This document is intended to define the agreement so that the design of the interfacing hardware may proceed. The document is intended to define functional characteristics and detailed specifications of all interfaces between ARED and Node 1.

The following definitions differentiate between requirements and other non-binding statements.

Shall:

This is the only verb used for defining binding requirements

Should/May:

These verbs are used for stating non-mandatory goals.

Will:

This verb is used for stating facts or declaration of purpose

1.2 Responsibility and Change Authority

The Systems Architecture and Integration Division, EA3, will control and provide support to maintain this document until base lined by ISS. Then ISS will assume change authority and EA3will maintain the document and provide change support as directed by the appropriate ISS control board. The Configuration Control is based on the EA Work Instruction EA‑WI‑023, Revision C. Additionally, this document was created per SSP 50010, Standards for ISS Program Documentation.

APPLICABLE AND REFERENCE DOCUMENTS

1.3 Applicable Documents

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

Version 15 May 19, 2003 Node 1 Geometry Model

Version 0 April 28, 2003 Node 1 Sand Volume Model

January 2002 Project Management of GFE Flight Projects Work Instruction

July 28, 1998 Space Station Reference Coordinate Systems

May 3, 2002 Space Station Electromagnetic Emission and Susceptibility Requirements

July 31, 2002 Space Station Grounding Requirements

July 31, 2002 Space Station Requirements for Electromagnetic Compatibility

May 3, 2002 Space Station Electrical Bonding Requirements

Jan 21, 1994 Space Station External Contamination Control Requirements

June 28, 2002 System Specification for the International Space Station

June 28, 2002 Segment Specification for the United States On-orbit

Dec. 15, 1999 International Space Station Flight Crew Integration Standard (NASA-STD-3000/T)

Mar. 28, 2000 Microgravity Control Plan

Dec. 1998

DCN 005

Mar. 11, 2002 Generic Ground rules, Requirements, and Constraints, Part 1: Strategic and Tactical Planning

Volume 1: 120 Volt DC Loads

Oct. 31, 2001 International Standard Payload

Rack (ISPR) Structural Integrator’s

Handbook

July 14, 1997 Track Assy, Seat, Handrail

April 22, 1998 Furnishings Installation – Node 1

Dec 17, 1999 Plate – R&MA Attachment

1.4 Reference Documents

The following documents are reference documents utilized in the development of this ICD. These documents do not form a part of this ICD and are not controlled by their reference herein.

February 2007 Standards for ISS Program Documentation

Formerly

JSC 28169

Interface Control Document for the International Space Station Resupply Stowage Platform 1 Stowage System to Cargo Providers

Aug. 28, 2001 Operations Local Area Network (OPS LAN) Interface Control Document

Jan. 24, 2001 Space Station Program Utility Outlet Panel Standard Interface Control Document

Drawings

1.5 Order of Precedence

This document is a definitive set of interface requirements required to integrate the ARED with the ISS. In the event of a conflict between the requirements specified in this document and an applicable document cited herein, the text of this document takes precedence.

INTERFACES

1.6 General

The following paragraphs describe the system interfaces between the ARED, Part Number SGG52100319-301, and Node 1 of the ISS. Interface responsibilities are defined with respect to the interface boundaries shown in Figure 3.1-1, ARED Interface Diagram. Interfaces with the Multi-Purpose Logistics Module / Resupply Stowage Platform (MPLM / RSP) are governed by SSP 50751 and are not detailed herein.

Figure 3.1-1: ARED Interface Diagram

1.6.1 System Description

The Advanced Resistive Exercise Device (ARED) functions to maintain crew health in space. Crewmembers exercise daily to maintain their pre-flight muscle and bone strength and endurance. ARED provides users with the resistive exercise capability as specified in JSC 29685. The ARED instrumentation system will record exercise data for near real time display to the crew and to allow physicians on the ground to analyze exercise sessions. The ARED mechanical system is supported by the Vibration Isolation System (VIS), which will attach to the Seat Tracks in Node 1. The ARED is depicted in Figure 3.1.1-1, Advanced Resistive Exercise Device.

Figure 3.1.1-1: Advanced Resistive Exercise Device

1.6.1.1 Structural

The ARED VIS mounts to the internal structure of ISS Node 1 via standard seat tracks. The ARED will be located at the radial ports in Node 1. See Figure 3.2.3-1, Nod1 Model – Facing Aft (into FGB), Figure 3.2.3-2, Node 1 Model – Facing Forward (into Lab), and Figure 3.2.3-3, Zenith Seat Track Attachment Envelope.

1.6.1.2 Power

The ARED operates from an ISS-supplied A31p power supply, part number SEG33116412-303. The A31p power supply will receive power from a standard Utility Outlet Panel (UOP) in Node 1 via a standard ISS-supplied power cable such as SEZ39129260-305 or SEZ39129260-311. The interface between the A31p power supply and the UOP is specified in SSP 30257:002.

1.6.1.3 Data

The ARED interfaces with the ISS Ops LAN (Operations Local Area Network) via a wireless link for the download of exercise data and the upload of prescription information and software updates. The external data interfaces are governed by JSC 36381 and are therefore not addressed in this document.

1.6.1.4 Stowage

The ARED will utilize 3 Cargo Transfer Bag (CTB) equivalents (volume / mass) for on-orbit stowage of ARED spares and accessories. The ISS will provide a stowage location for these CTB equivalents.

1.6.2 Coordinate System

The coordinate system for Node 1 is defined in SSP 30219, Space Station Reference Coordinate Systems, Section 9-7, Figure 9.0-6.

The coordinate system used for integration of the ARED into the “sand volume” (see 3.2.1.2) and into Node 1 is defined by the intersection of three planes, where two planes are at the center of the forward hatch (25" from a side) defining one vertical and one horizontal, and the third plane is parallel to the radial port closeout panels, midway (27”) between the forward or aft plane. This coordinate system references the three planes such that the positive Z‑axis points to the Deck (a.k.a. the Nadir direction), the positive X-axis points Aft, and the positive Y-axis points in the Port direction. (Note that this is not the center of the radial port hatch, and is not identical to the Node 1 coordinate system.)

1.6.3 Engineering Units, Tolerances, and Conversions

Measurements in this document are given in the English (inch, pound, second) system of units. The following tolerances and assumptions are used when assessing the integration of ARED into Node 1:

1. Tolerances will be ±0.5 inch in the X-direction, Y-direction, and Z-direction as applied to the “seat track-to-seat track” dimensions.

2. The seat tracks are mounted at a 45-degree angle with respect to the mounting plane. The angular tolerance for the seat track mounting is ± 5 degrees.

3. The seat tracks are straight and not deformed, i.e. no twisting or deformation due to pressurization of the Node.

4. The X-direction dimensions may decrease by up to 0.050” due to Node depressurization.

1.6.4 Interface Responsibilities

1.6.4.1 Responsibility for ARED Interfaces

The Biomedical Systems Division of EA is responsible for the ARED interface requirements defined in the document.

1.6.4.2 Responsibility for ISS Interfaces

The ISS Vehicle Office is responsible for the ISS interface requirements defined in the document.

1.7 Interface Requirements

1.7.1 Envelope

1.7.1.1 Envelope Definitions

1.7.1.1.1 Deployed Envelope

The ARED deployed envelope is the space occupied by the exercise device in its unfolded configuration when the exercise device is not in use. The ARED in its deployed configuration in Node 1 is depicted in Figure 3.2.1-1, Orientation of ARED in Node 1.

1.7.1.1.2 Operational Envelope

The ARED operational envelope is the space occupied by the exercise device and crewmember when the exercise device is in use for on-orbit exercise. This includes the motion of the exercise device on the VIS as a result of performing exercises.

Figure 3.2.1-1: Orientation of ARED in Node 1 (Looking from Lab Module through Node 1 into FGB)

1.7.1.1.3 Stowed Envelope

The ARED stowed envelope is the space occupied by the exercise device when the exercise device is folded. For this configuration, the ARED need not be mounted to the seat tracks in Node 1.

1.7.1.1.4 Spares Envelope

The ARED spares envelope is the space occupied by the ARED spares and accessories when stowed.

1.7.1.2 Detailed Specifications

1.7.1.2.1 Static Envelope

The static envelope of the ARED, in its deployed configuration, shall meet the constraints defined by Model “node1_ared_icd_vol.prt,” Revision 1, Version 0, April 28, 2003. This model defines the “sand volume” of Node 1, which was created from the geometry of the Node 1 Geometry Model “red_node1_complete.asm,” Revision 1 Version 15, May 19, 2003, and includes the specific stay out zones as defined by SSP 50261-01, Generic Ground Rules, Requirements, and Constraints, Part 1: Strategic and Tactical Planning. The Node 1 “Sand Volume” is represented in Figure 3.2.1-2, Node 1 Sand Volume – Port Side, and Figure 3.2.1-3, Node 1 Sand Volume – Starboard Side.

1.7.1.2.2 Dynamic Envelope

The dynamic envelope of the ARED, in its operational configuration (which includes the ARED and the crewmember operating the ARED), shall meet the envelope constraints defined by the Node 1 Geometry Model “red_node1_complete.asm,” Revision 1 Version 15, May 19, 2003.

1.7.1.2.3 Dimensions for Spares and Accessories

The ARED spares and accessories on orbit shall occupy a volume not to exceed the equivalent of three (3) single CTBs when stowed. Refer to drawings SEG33111836, SEG33111837, SEG33111838, SEG33111839, and SEG33111840 for CTB sizes.

1.7.1.3 Transfer Configuration Dimensions

The ARED, in its stowed configuration, shall be sized to allow transfer through a standard ISS hatch defined as 50 inches x 50 inches with 12-inch radius corners as specified in SSP 50261, Part 1, DCN 004.

1.7.1.4 Visibility and Access to Critical Equipment and Controls

The ARED shall not limit visibility and access to critical equipment and controls per GGR&C requirements SSP 50261, paragraph 3.12.3.

1.7.1.5 Translation Paths

1.7.1.5.1 Clearance Requirements

The ARED, in its deployed configuration, shall be designed to meet the translation path requirements as defined in SSP 50005, International Space Station Flight Crew Integration Standard (NASA-STD-3000/T), paragraph 8.8.3.2.

1.7.1.5.2 Nominal Crew Translation Path

The ARED, in its deployed configuration, shall not obstruct the nominal crew translation path as defined in SSP 50261, Part 1, DCN 004.

1.7.1.5.3 Emergency Crew Translation Path

The ARED, in its deployed configuration, shall not obstruct the emergency crew translation path as defined in SSP 50261, Part 1, DCN 004.

1.7.1.5.4 Equipment Translation Path

The ARED, in its stowed configuration, shall not obstruct the equipment translation path as defined in SSP 50261, Part 1, DCN 004.

Figure 3.2.1-2: Node 1 Sand Volume – Port Side

Figure 3.2.1-3: Node 1 Sand Volume – Starboard Side

1.7.2 Mass Properties

1.7.2.1 On-Orbit ARED Mass

Deleted. [SSCN 011074] Rationale: Mass of interest is total upmass of ARED which is addressed in JSC 29685, Project Technical Requirements Specification for the Advanced Resistive Exercise Device (ARED), requirement Paragraph 3.2.2.2.1 – Launch Weight.

1.7.2.2 On-Orbit Spares Mass

Deleted. [SSCN 011074] Rationale: Mass of interest is total upmass of ARED which is addressed in JSC 29685, Project Technical Requirements Specification for the Advanced Resistive Exercise Device (ARED), requirement Paragraph 3.2.2.2.1 – Launch Weight.

1.7.3 Structural/Mechanical

1.7.3.1 Functional Characteristics

The VIS assembly shall act as the interface between the ARED and the ISS Node 1 structure by hard mounting to the seat tracks or Light Bars.

1.7.3.1.1 Seat Track Mounting

The ARED VIS may mount to the ISS using any combination of the Zenith Alcove and Zenith Midbay seat tracks in Node 1. Reference Figure 3.2.3-1 and Figure 3.2.3-2. The seat track on the Node 1 Midbay closeout panels is part number 1F89410‑1. The seat track on the Node 1 Alcove closeout panels is part number 683-60114.

1.7.3.1.1.1 ISS Node 1 Seat Track Locations

The Midbay Port, Midbay Starboard, Alcove Port, and Alcove Starboard seat tracks in Node 1 are located as defined in the Node 1 Geometry Model “red_node1_complete.asm” Revision 1, Version 16, February 23, 2006. Reference Figure 3.2.3-1 and Figure 3.2.3-2 and drawing 1F88575.

1.7.3.1.1.2 Seat Track Attachment Envelope

If designed to utilize the Node 1 seat tracks, the ARED VIS Node Interface Structure (NIS) shall be designed to attach to the Zenith seat tracks within the dimensional constraints shown in Figure 3.2.3-3.

1.7.3.1.1.3 Seat Track Limit Loads

The loads applied to any seat track by the ARED shall not exceed the limits defined in AB3T-2005-RET-028 and summarized below. See Figure 3.2.3-4, Seat Track Limit Loads Orientation, for load orientation.

Fx, Fy (shear) = 650 lbf (pounds force) maximum

Fz (tensile) = 470 lbf maximum

Moment = 1,490 in-lbf (inch – pounds force) maximum in any direction

These loads include a factor of safety of 2.0.

1.7.3.1.1.4 Seat Track Cyclic Loading

Cyclic loading on the Node 1 seat tracks shall be limited to 25% of the loads specified in paragraph 3.2.3.1.1.3. Combined loads are subject to the interaction equations specified in SSP 57007, International Standard Payload

Rack (ISPR) Structural Integrator’s Handbook, as defined in AB3T-2004-RET-009.

1.7.3.1.2 Light Bar Mounting

The light bars may also be used for mounting ARED in the ISS Node 1.

1.7.3.1.2.1 Light Bar Attachment Envelope

If designed to utilize the Node 1 Light Bars, the ARED VIS NIS mounting interfaces to the light bar shall be limited to the two bolt locations on the end caps of the Light Bars. See Figure 3.2.3-5, Light Bar Mounting Locations for ARED.

1.7.3.1.2.2 Light Bar Limit Loads

The loads applied to any Light Bar by the ARED shall not exceed the limits defined in AB3T-2004-RET-009 as summarized below. See Figure 3.2.3-5.

Tension = 1,511 lbf per bolt maximum

Shear = 1,485 lbf per bolt maximum

These loads include a factor of safety of 2.0.

1.7.3.1.2.3 Light Bar Cyclic Loading

Cyclic loading on the Node 1 Light Bars shall be limited 25% of the loads specified in paragraph 3.2.3.1.2.2. Combined loads are subject to the interaction equations as defined in AB3T-2004-RET-009.

Figure 3.2.3-1: Node 1 Model – Facing Aft (into FGB)

Figure 3.2.3-2: Node 1 Model – Facing Forward (into Lab)

Figure 3.2.3-3: Zenith Seat Track Attachment Envelope

Figure 3.2.3-4: Seat Track Limit Loads Orientation

Figure 3.2.3-5: Light Bar Mounting Locations for ARED

Electrical (Power)

1.7.3.2 Functional Characteristics

ARED shall connect to a standard ISS UOP in Node 1 via an A31p power supply, part number SEG33116412-303, as shown in Figure 3.2.4-1, ISS-to-ARED Electrical Power Interface Description.

Figure 3.2.4-1: ISS-to-ARED Electrical Power Interface Description

1.7.3.2.1 Electrical Interface to ISS

The electrical interface between the ISS and the ARED shall be at the A31p power supply outlet to ARED Main Power Cable connector as shown in Figure 3.2.4-1.

1.7.3.3 Detailed Specifications

1.7.3.3.1 Power Supply Performance

The ISS-provided A31p power supply will supply power to the ARED at 11.3 to 20 VDC (Volts Direct Current) (16.8 VDC nominal) under nominal and peak loading conditions.

1.7.3.3.2 Peak Power Consumption

ARED power consumption shall not exceed 100 watts for peak power.

1.7.3.3.3 Continuous Power Consumption

ARED power consumption shall not exceed 55 watts for continuous power.

1.7.3.3.4 Power Quality

The ARED shall be compatible with the power quality requirements for Interface D as specified in the SSP 52051, Volume 1, User Electric Power Specifications and Standards Volume 1: 120 Volt DC Loads.

1.7.3.3.5 Power Dropout

The ARED shall withstand a power interruption of 10 milliseconds maximum at the UOP without affecting operation.

1.7.3.3.6 Connector Designation

The interface connector on the ARED side shall be designated as “P2”.

1.7.3.3.7 Pin Assignments

The pin assignment for the interface connector shall be as follows:

P2 Pin A – 16.8 VDC P2 Pin E - Unused

P2 Pin B – 16.8 VDC RTN P2 Pin F – Voltage Trim Resistor

P2 Pin C – Chassis Ground P2 Pin G – Voltage Trim Resistor

P2 Pin D – Unused P2 Pin H – Unused

1.7.3.3.8 Connector Part Number

The interface connector on the A31p power supply is part number MS27497E12F8S.

1.7.3.3.9 Power Supply Location

The A31p Power Supply shall be located on the ARED VIS structure as shown in Figure 3.2.4-2, ARED Power Supply Location.

Figure 3.2.4-2: ARED Power Supply Location

1.7.4 Electronic (Signal)

Not applicable.

1.7.5 Software and Data

The software and data interface between the ISS Ops LAN and the ARED is specified in SSP 36381 and is therefore not addressed herein.

1.7.6 Environmental

1.7.6.1 Functional Characteristics

The ARED shall meet the on-orbit environmental requirements and constraints, including EMI / EMC (Electromagnetic Compatibility / Electromagnetic Interference) as specified in JSC 29685, Paragraph 3.2.3.

1.7.6.2 Detailed Specifications

1.7.6.2.1 Bonding

1.7.6.2.1.1 Structural and Mechanical Interfaces

The ARED-to-Node 1 structural and mechanical interfaces shall meet the requirements of SSP 30245, Space Station Electrical Bonding Requirements, for a Class S bond.

1.7.6.2.1.2 Electrical Interfaces

The ARED-to-Node 1 electrical interfaces shall meet the requirements of SSP 30245 for a Class H bond.

1.7.6.2.2 Grounding

The ARED-to-Node 1 electrical interfaces shall meet the grounding requirements of SSP 30240, Space Station Grounding Requirements, using the ground wire through the A31p power supply.

1.7.6.2.3 ARED Thermal Loads

The thermal load from the ARED to the Node 1 shall not exceed 205 BTU/hr during exercise. This does not include crewmember metabolic loads.

1.7.6.2.4 Acoustic Emissions

The ARED shall meet the acoustic emissions requirements in accordance with JSC 28322.

1.7.6.2.5 Micro-gravity

When the ISS is in Micro-gravity Mode, ARED shall limit accelerations at micro-gravity experiment racks to the values as numerically expressed in Table 3.2.7-1, Micro-gravity Limits and displayed in Figure 3.2.7-1, Micro-gravity Limits.

Table 3.2.7-1: Micro-gravity Limits

Frequency

(Hz) Acceleration

(g) Frequency

(Hz) Acceleration

(g) Frequency

(Hz) Acceleration

(g)

Table 3.2.7-1: Micro-gravity Limits (cont.)

Figure 3.2.7-1: Micro-gravity Limits

1.7.6.2.6 Limit Vibratory Accelerations

1.7.6.2.6.1 Transient Accelerations

The ARED shall limit transient accelerations from individual transient disturbance sources to less than or equal to 1000 micro-gravity per axis, and when integrated over any 10 second interval to less than or equal to 10 micro-gravity seconds per axis when using the transfer functions or system models and methodology as called out in SSP 41162, Segment Specification for the United States On-orbit, paragraph 3.7.30.3.7.7.4b and in accordance with SSP 50036, Microgravity Control Plan, paragraph 5.4.2 and 5.4.3.

1.7.6.2.6.2 Acceleration Levels

ARED acceleration levels shall be met at the structural mounting interfaces to the internal payload locations for a minimum of 180 days per year in continuous time intervals of at least 30 days as called out in SSP 41162, paragraph 3.7.30.3.7.7.4c and as identified in accordance with SSP 50036, paragraph 5.4.

1.7.6.2.6.3 Vibratory Acceleration Environment

The ARED shall provide such a vibratory acceleration environment, concurrently with the quasi-steady acceleration environment as called out in SSP 41162, paragraph 3.7.30.3.7.7.4d and specified in the limit quasi-steady accelerations function.

1.7.6.2.6.4 Quasi-Steady Accelerations

The ARED shall limit quasi-steady (< 0.01 Hz) acceleration magnitude from all ARED combined disturbances to less than or equal to 0.02 micro-gravity, excluding accelerations from aerodynamic and gravitational forces.

1.7.6.2.7 On-Orbit Thermal Environment

The ARED shall meet the performance requirements specified herein when exposed to the on-orbit ISS thermal environment of +63 to 87 degrees F, per SSP 41000, System Specification for the International Space Station, paragraph 3.7.1.3.2.1. Note: Two degrees tolerance has been added to the limits defined in SSP 41000, 3.7.1.3.2.1 based upon the thermal control performance documented in SSP 57000, 3.9.4.

1.7.6.2.8 On-Orbit Pressure Environment

The ARED shall meet specified performance when exposed to an on-orbit nominal pressure environment from 14.2 to 14.9 psia, with a minimum pressure of 13.9 psia as called out in SSP 41000, paragraph 3.7.1.3.1.1B.

1.7.6.2.9 On-Orbit Acceleration Environment

ARED component load factors for design of Node 1 subsystems and components shall be 0.2 g’s (gravities), acting in any direction.

1.7.6.2.10 Electromagnetic Compatibility

The ARED shall meet the electromagnetic compatibility requirements in accordance with SSP 30243, Space Station Requirements for Electromagnetic Compatibility.

1.7.6.2.11 Electromagnetic Interference

The ARED shall meet the electromagnetic interference requirements in accordance with SSP 30237, Space Station Electromagnetic Emission and Susceptibility Requirements, RE02.

1.7.6.2.12 On-Orbit Humidity Environment

The ARED shall meet specified performance when exposed to 25 percent to 75 percent relative humidity, per SSP 41000 paragraph 3.7.1.3.2.2.

1.7.6.2.13 On-Orbit External Contamination Environment

The ARED shall meet specified performance requirements when exposed to the external contamination environments as specified in SSP 30426, Space Station External Contamination Control Requirements, paragraph 3.4 and 3.5, Quiescent Periods and Non-quiescent Periods.

Appendix A Abbreviations and Acronyms

A.1 ABBREVIATIONS AND ACRONYMS

ARED

Advanced Resistive Exercise Device

BTU/hr

British Thermal Units per hour

CTB

Cargo Transfer Bag

DCN

Document Change Notice

EMC

Electromagnetic Compatibility

EMI

Electromagnetic Interference g’s

Gravities

Hz

Hertz

ICD

Interface Control Document in-lbf

Inch-pound force

ISS

International Space Station

ISSP

International Space Station Program lbm pound-mass lbf pound-force

MPLM

Multi-Purpose Logistics Module

NIS

Node Interface Structure Ops LAN Operations Local Area Network psia

Pounds per square inch absolute

RSP

Resupply Stowage Platform

TBR

To Be Resolved

UOP

Utility Outlet Panel

VDC

Volts Direct Current

VDC RTN

Volts Direct Current Return

VIS

Vibration Isolation System g

Microgravities

Instrumentation

- Structure

Vibration

Isolation

System

Z

- Power

Fy

ARED Main Power Cable� SEG52100930-301

X

(out of the page)

Fx

ISS Orientation

ISS-Supplied Power Cable�e.g. SEZ39129260-305 or SEZ39129260-311

Fz

ISS /

Node 1

Note: ARED outline inserted for reference only.

Exercise

Device

Y

J2 / P2

ARED Mounting Points

(NAS1953C8 Bolt, Shear)

Footbridge Housing

Footbridge End Cap

Node 1

Utility Outlet Panel

ARED Instrumentation Box

SEG52100894-301

ARED Capacitor Cable

SEG52100933-301

A31p Power Supply

SEG33116412-303

Zenith Midbay Seat Track

Light Bar

ARED with VIS. Note: Right side VIS removed for clarity.

ISS Orientation

PORT

CUPOLA RADIAL PORT

STARBOARD

AIRLOCK INTERFACE

Z1 RADIAL PORT

ISS / ARED Electrical (Power) Interface

GSE

Crew

Software

ARED

- Volume

MPLM /

RSP

- Data (RF)

OPS LAN

- Volume

ALCOVE AREA

Midbay Area

Zenith Alcove Seat Tracks

Starboard

(Airlock)

Nadir

(MPLM)

Port

(Cupola)

Zenith

(Z1 Truss)

Note: ARED outline inserted for reference only.

Starboard

(Airlock)

Zenith Midbay Seat Track

Nadir

(MPLM)

Zenith Alcove Seat Tracks

Port

(Cupola)

Zenith

(Z1 Truss)

National Aeronautics and Space Administration

International Space Station Program

Johnson Space Center

Houston, Texas

MPLM INTERFACE

ARED

Node Structure

A31p – mounted to the left Y-Plate of the VIS.

_1209906266

_1212997529

_1209905592

_1108813961.xls Chart1

0.0089126

0.01122

0.01122

0.014125

0.014125

0.017783

0.017783

0.022387

0.022387

0.028184

0.028184

0.035481

0.035481

0.044668

0.044668

0.056234

0.056234

0.070795

0.070795

0.089125

0.089125

0.1122

0.1122

0.14125

0.14125

0.17783

0.17783

0.22387

0.22387

0.28184

0.28184

0.35481

0.35481

0.44668

0.44668

0.56234

0.56234

0.70795

0.70795

0.89125

0.89125

1.122

1.122

1.4125

1.4125

1.7783

1.7783

2.2387

2.2387

2.8184

2.8184

3.5481

3.5481

4.4668

4.4668

5.6234

5.6234

7.0795

7.0795

8.9125

8.9125

11.22

11.22

14.125

14.125

17.783

17.783

22.387

22.387

28.184

28.6417796991

35.481

35.481

44.668

44.668

56.234

Requirement

Frequency (Hz)

RSS Acceleration (microg)

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2

0.2657

0.2657

0.34079

0.34079

0.43465

0.43465

0.55666

0.55666

0.71622

0.71622

0.90394

0.90394

1.148

1.148

1.467

1.467

1.8425

1.8425

2.3118

2.3118

2.9688

2.9688

3.7197

3.7197

4.6583

4.6583

5.8784

5.8784

7.474

7.474

9.3512

9.3512

11.7915

11.7915

14.9827

14.9827

18.737

18.737

23.4299

23.4299

30.043875

Sheet1

Frequency ARED Reqt Frequency ARED Reqt Frequency ARED Reqt

0.0089126 0.2

0.01122 0.2

0.01122 0.2

0.014125 0.2

0.014125 0.2

0.017783 0.2

0.017783 0.2

0.022387 0.2

0.022387 0.2

0.028184 0.2

0.028184 0.2

0.035481 0.2

0.035481 0.2

0.044668 0.2

0.044668 0.2

0.056234 0.2

0.056234 0.2

0.070795 0.2

0.070795 0.2

0.089125 0.2

0.089125 0.2

0.1122 0.2

0.1122 0.2

0.14125 0.2

0.14125 0.2657

0.17783 0.2657

0.17783 0.34079

0.22387 0.34079

0.22387 0.43465

0.28184 0.43465

0.28184 0.55666

0.35481 0.55666

0.35481 0.71622

0.44668 0.71622

0.44668 0.90394

0.56234 0.90394

0.56234 1.148

0.70795 1.148

0.70795 1.467

0.89125 1.467

0.89125 1.8425

1.122 1.8425

1.122 2.3118

1.4125 2.3118

1.4125 2.9688

1.7783 2.9688

1.7783 3.7197

2.2387 3.7197

2.2387 4.6583

2.8184 4.6583

2.8184 5.8784

3.5481 5.8784

3.5481 7.474

4.4668 7.474

4.4668 9.3512

5.6234 9.3512

5.6234 11.7915

7.0795 11.7915

7.0795 14.9827

8.9125 14.9827

8.9125 18.737

11.22 18.737

11.22 23.4299

14.125 23.4299

14.125 30.043875

17.783 30

17.783 30

22.387 30

22.387 30

28.184 30

28.6417796991 30

35.481 30

35.481 30

44.668 30

44.668 30

56.234 30

Sheet2

Sheet3