Instructions For Completing Experiment …snebulos.mit.edu/projects/voila/file_cabinet/0/02002/... · Web viewThe head and body tracker system is built from COTS components. It consists

Instructions For Completing Experiment Document Worksheets

Hardware Requirements Document (HRD)

for

Visuomotor and Orientation Investigation on

Long-duration Astronauts (VOILA)

CCB CONTROL

PROJECT DOCUMENT APPROVAL SHEET

document number

DATE

NO. OF

ls-XXXXX

TBD

PAGES

TBD

TITLE:


for

VOILA

aPPROVED:

EB/Elizabeth Bauer

Technical Manager

approved:

NT3/V. Watkins

GFE Assurance Branch

approved:

EA2/L. Bromley

Project Management Office

approved:

EB/James LeBlanc

Division Chief

approved:

SM3/D. Baumann

HRF Experiment Support Manager

DATE

PREPARED BY

CHANGE APPROVALS

CHANGENUMBER

jsc form 604 (rev jul 81)nasa-jsc

Report NumberLS-71099

Date11/20/01


for

VOILA

Prepared by:

Larry WaltersSystem Engineer

Date

Approved:

Ara Kulhanjian

Project Manager

Date

Approved:

Don Kilbourn

Manager, S&PA Department

Date

Approved:

Jerry McDonald

HRF Hardware Development Section Manager

Date

Prepared By:

Lockheed Martin Engineering and Sciences

Houston, Texas

for

National Aeronautics and Space Administration

Johnson Space Center

REVISION/CHANGE APPROVALS

Change

Approved by:

Date

Number

Prepared by

Unit Manager

SR&QA Manager

Projects Manager

Lockheed Martin Space Operations (March 1999)

document number

DOCUMENT CHANGE/

page 1 OF 1

ls-XXXXX

REVISION LOG

CHANGE/REVISION

DATE

DESCRIPTION OF CHANGE

PAGESAFFECTED

Basic

TBD

Baseline Issue Reference CCBD:

All

Altered pages must be typed and distributed for insertion.

jsc form 278 (rev APR 81)nasa-jsc

Preface

This Hardware Requirements Document (HRD) defines the minimum set of requirements for the VOILA hardware to be placed on the International Space Station (ISS) and mounted within the HRF Rack. This document is under the control of the HRF Configuration Control Board (CCB).

___________________________________

HRF CCB Chair DATE

CONTENTS

SectionPage

11.0SCOPE1-

Error! Bookmark not defined.1.1GUIDELINES FOR COMPLETION OF THE HARDWARE REQUIREMENTS DOCUMENT TEMPLATE1-

12.0APPLICABLE DOCUMENTS2-

12.1DOCUMENTS2-

42.2ORDER OF PRECEDENCE2-

13.0SYSTEM REQUIREMENTS3-

13.1ITEM DEFINITION3-

103.2CHARACTERISTICS3-

103.2.1Performance Characteristics3-

103.2.1.1Functional Performance Characteristics3-

133.2.2Physical Characteristics3-

133.2.2.1Mass and Center of Gravity Properties3-

143.2.2.1.1HRF Rack Mounted Standard Interface Rack (SIR) Drawer Center-of-Gravity Constraints3-

Error! Bookmark not defined.3.2.2.2Envelope3-

Error! Bookmark not defined.3.2.2.2.1Stowed Envelope3-

153.2.2.2.2Deployed Envelope3-

153.2.2.2.2.1On-Orbit Payload Protrusions3-

163.2.2.2.2.1.1On-Orbit Permanent Protrusions3-

173.2.2.2.2.1.2On-Orbit Semi-Permanent Protrusions3-

183.2.2.2.2.1.3On-Orbit Temporary Protrusions3-

193.2.2.2.2.1.4On-Orbit Momentary Protrusions3-

193.2.2.2.2.2Deployed Envelope Dimensions3-

193.2.3Reliability, Quality and Non-Conformance Reporting3-

203.2.3.1Failure Propagation3-

203.2.3.2Useful Life3-

213.2.3.2.1Operational Life (Cycles)3-

213.2.3.2.2Shelf Life3-

213.2.3.2.3Limited Life3-

213.2.4Maintainability3-

223.2.4.1Logistics and Maintenance3-

223.2.4.1.1Payload In-Flight Maintenance3-

223.2.4.1.2Maintenance3-

223.2.5Environmental Conditions3-

223.2.5.1On-Orbit Environmental Conditions3-

CONTENTS (Contd)

SectionPage

223.2.5.1.1On-Orbit Internal Environments3-

223.2.5.1.1.1Pressure3-

223.2.5.1.1.2Temperature3-

233.2.5.1.1.3Humidity3-

233.2.5.1.2Use of Cabin Atmosphere3-

233.2.5.1.2.1Active Air Exchange3-

233.2.5.1.2.2Oxygen Consumption3-

233.2.5.1.2.3Chemical Releases3-

233.2.5.1.2.4Cabin Air Heat Leak3-

233.2.5.1.3Ionizing Radiation Requirements3-

233.2.5.1.3.1Instrument Contained or Generated Ionizing Radiation3-

233.2.5.1.3.2Ionizing Radiation Dose3-

233.2.5.1.3.3Single Event Effect (SEE) Ionizing Radiation3-

243.2.5.1.4Additional Environmental Conditions3-

273.2.5.1.5Pressure Rate of Change3-

283.2.5.1.6Microgravity3-

293.2.5.2Acoustic Emission Limits3-

293.2.5.2.1Continuous Noise Limits3-

303.2.5.2.2Intermittent Noise Limits3-

313.2.5.3Lighting Design3-

323.2.5.4Front Panel Surface Temperature3-

323.2.6Transportability3-

323.2.6.1Launch and Landing3-

333.2.7Operational Interface Requirements3-

333.2.7.1Mechanical Interface Requirements3-

333.2.7.1.1Connector Physical Mate3-

333.2.7.1.2HRF Rack to SIR Drawer Structural Interface Requirements3-

343.2.7.1.2.1Dimensional Tolerances3-

353.2.7.1.2.2SIR Drawer Structural/ Mechanical Interfaces3-

353.2.7.1.2.3Reserved3-

353.2.7.1.2.4HRF Rack Seat Track Interfaces3-

353.2.7.2Electrical Power Interface Requirements3-

353.2.7.2.1HRF Rack Power Output Connectors3-

353.2.7.2.1.1SIR Drawer Power Connectors3-

363.2.7.2.1.2Rack Connector Panel J1 Power Connector3-

363.2.7.2.2Voltage Characteristics3-

363.2.7.2.2.1Steady-State Operating Voltage Envelope3-

363.2.7.2.2.2Transient Operating Voltage Envelope3-

CONTENTS (Contd)

SectionPage

363.2.7.2.2.3Ripple Voltage/Noise Characteristics3-

393.2.7.2.3Maximum Current Limit3-

403.2.7.2.4Reverse Current3-

403.2.7.2.5Reverse Energy3-

403.2.7.2.6Capacitive Loads3-

403.2.7.2.7Electromagnetic Compatibility (EMC)3-

403.2.7.2.7.1Electrical Grounding3-

403.2.7.2.7.2Electrical Bonding3-

413.2.7.2.7.3Electromagnetic Interference3-

423.2.7.2.8Electrostatic Discharge3-

423.2.7.2.9Corona3-

423.2.7.2.10Cable/Wire Design and Control Requirements3-

423.2.7.2.10.1Wire Derating3-

423.2.7.2.10.2Exclusive Power Feeds3-

433.2.7.2.11Loss of Power3-

433.2.7.2.12Alternating Current Magnetic Fields3-

433.2.7.2.13Direct Current Magnetic Fields3-

433.2.7.3Command and Data Handling Interface Requirements3-

433.2.7.3.1HRF Rack Data Connectors3-

433.2.7.3.1.1SIR Drawer Data Connectors3-

463.2.7.3.1.2HRF Rack Connector Panel J2 Data Connector3-

463.2.7.3.2HRF Ethernet Interfaces3-

463.2.7.3.3HRF TIA/EIA-422 Interfaces3-

463.2.7.3.4HRF Bi-Directional Discretes Interfaces3-

463.2.7.3.5HRF Analog Interfaces3-

463.2.7.3.6HRF Software Requirements.3-

593.2.7.3.7Reserved3-

593.2.7.3.8Reserved3-

593.2.7.3.9Reserved3-

593.2.7.3.10Medium Rate Data Link3-

Error! Bookmark not defined.3.2.7.3.10.1Data Transmissions3-

Error! Bookmark not defined.3.2.7.3.10.2Consultative Committee for Space Data Systems (CCSDS) Data3-

Error! Bookmark not defined.3.2.7.3.10.2.1CCSDS Data Packets3-

Error! Bookmark not defined.3.2.7.3.10.2.1.1CCSDS Primary Header3-

Error! Bookmark not defined.3.2.7.3.10.2.1.2CCSDS Secondary Header3-

Error! Bookmark not defined.3.2.7.3.10.2.2CCSDS Data Field3-

Error! Bookmark not defined.3.2.7.3.10.2.3CCSDS Application Process Identification Field3-

CONTENTS (Contd)

SectionPage

593.2.7.4Payload National Television Standards Committee (NTSC) Video Interface Requirements3-

Error! Bookmark not defined.3.2.7.4.1HRF Rack Video Connectors3-

Error! Bookmark not defined.3.2.7.4.1.1SIR Drawer Video Interface3-

Error! Bookmark not defined.3.2.7.4.1.2Rack Connector Panel Interface3-

Error! Bookmark not defined.3.2.7.4.2HRF Rack Video Interface Characteristics3-

593.2.7.5Thermal Control Interface Requirements3-

593.2.7.5.1HRF Rack Provided Internal Thermal Control System (ITCS) Moderate Temperature Loop (MTL) Interface3-

Error! Bookmark not defined.3.2.7.5.1.1HRF Rack MTL Interface Connectors3-

Error! Bookmark not defined.3.2.7.5.1.2ITCS Fluid Use and Charging3-

Error! Bookmark not defined.3.2.7.5.1.3Reserved3-

Error! Bookmark not defined.3.2.7.5.1.4Coolant Maximum Design Pressure3-

Error! Bookmark not defined.3.2.7.5.1.5Payload Coolant Quantity3-

Error! Bookmark not defined.3.2.7.5.1.6Fail Safe Design3-

Error! Bookmark not defined.3.2.7.5.1.7Leakage3-

Error! Bookmark not defined.3.2.7.5.1.8Quick-Disconnect Air Inclusion3-

593.2.7.5.2HRF Rack Heat Exchanger to SIR Drawer Interface3-

593.2.7.5.2.1Reserved3-

603.2.7.5.2.2HRF Rack Mounted SIR Drawer Cooling Fans3-

613.2.7.6Vacuum System Requirements3-

Error! Bookmark not defined.3.2.7.6.1HRF Rack Vacuum Interface Connectors3-

Error! Bookmark not defined.3.2.7.6.2VES Requirements3-

Error! Bookmark not defined.3.2.7.6.2.1Input Pressure Limit3-

Error! Bookmark not defined.3.2.7.6.2.2Input Temperature Limit3-

Error! Bookmark not defined.3.2.7.6.2.3Input Dewpoint Limit3-

Error! Bookmark not defined.3.2.7.6.2.4Acceptable Exhaust Gases3-

Error! Bookmark not defined.3.2.7.6.2.4.1Acceptable Gases List3-

Error! Bookmark not defined.3.2.7.6.2.5External Contamination Control3-

Error! Bookmark not defined.3.2.7.6.2.6Incompatible Gases3-

Error! Bookmark not defined.3.2.7.6.3Vacuum Resource System Requirements3-

Error! Bookmark not defined.3.2.7.6.3.1Input Pressure Limit3-

Error! Bookmark not defined.3.2.7.6.3.2VRS Through-Put Limit3-

Error! Bookmark not defined.3.2.7.6.3.3Acceptable Gases3-

613.2.7.7Pressurized Gas Interface Requirements3-

Error! Bookmark not defined.3.2.7.7.1Nitrogen Interface Requirements3-

Error! Bookmark not defined.3.2.7.7.1.1HRF Rack Nitrogen Interface Connectors3-

Error! Bookmark not defined.3.2.7.7.1.2Nitrogen Interface Control3-

CONTENTS (Contd)

SectionPage

Error! Bookmark not defined.3.2.7.7.1.3Nitrogen Interface Maximum Design Pressure (MDP)3-

Error! Bookmark not defined.3.2.7.7.1.4Nitrogen Interface Temperature3-

Error! Bookmark not defined.3.2.7.7.1.5Nitrogen Leakage3-

Error! Bookmark not defined.3.2.7.7.2Pressurized Gas Systems3-

Error! Bookmark not defined.3.2.7.7.3Manual Valves3-

613.2.7.8Payload Support Services Interfaces Requirements3-

Error! Bookmark not defined.3.2.7.8.1Potable Water3-

Error! Bookmark not defined.3.2.7.8.1.1ISS Potable Water Interface Connection3-

Error! Bookmark not defined.3.2.7.8.1.2Potable Water Interface Pressure3-

Error! Bookmark not defined.3.2.7.8.1.3Potable Water Use3-

Error! Bookmark not defined.3.2.7.8.2Fluid System Servicer3-

613.2.7.9Fire Protection Interface Requirements3-

623.2.7.9.1Fire Prevention3-

623.2.7.9.2Payload Monitoring and Detection Requirements3-

623.2.7.9.2.1Parameter Monitoring3-

Error! Bookmark not defined.3.2.7.9.2.1.1Parameter Monitoring Use3-

Error! Bookmark not defined.3.2.7.9.2.1.2Parameter Monitoring Response in Subrack3-

623.2.7.9.3Fire Suppression3-

623.2.7.9.3.1Portable Fire Extinguisher3-

623.2.7.9.3.2Fire Suppression Access Port Accessibility3-

643.2.7.9.3.3Fire Suppressant Distribution3-

643.2.7.9.4Labeling3-

643.2.7.10Other Interface Requirements3-

663.3DESIGN AND CONSTRUCTION3-

663.3.1Materials, Processes, and Parts3-

663.3.1.1Materials and Processes3-

663.3.1.1.1Materials and Parts Use and Selection3-

663.3.1.1.1.1Russian Materials Usage Agreement3-

663.3.1.1.2Commercial Parts3-

663.3.1.1.3Fluids3-

663.3.1.1.4Cleanliness3-

663.3.1.1.5Fungus Resistant Material3-

663.3.1.2Sharp Edges and Corner Protection3-

673.3.1.3Holes3-

673.3.1.4Latches3-

673.3.1.5Screws and Bolts3-

673.3.1.6Securing Pins3-

673.3.1.7Levers, Cranks, Hooks and Controls3-

CONTENTS (Contd)

SectionPage

673.3.1.8Burrs3-

673.3.1.9Locking Wires3-

673.3.2Nameplates and Product Marking3-

673.3.2.1Equipment Identification3-

683.3.3Workmanship3-

683.3.4Interchangeability3-

683.3.5Safety Requirements3-

683.3.5.1Electrical Safety3-

683.3.5.1.1Safety-Critical Circuits Redundancy3-

683.3.5.1.2EMI Susceptibility for Safety-Critical Circuits3-

683.3.5.1.3Mating/Demating of Powered Connectors3-

683.3.5.1.4Power Switches/Controls3-

693.3.5.1.5Ground Fault Circuit Interrupters/Portable Equipment DC Sourcing Voltage3-

693.3.5.1.6Portable Equipment/Power Cords3-

693.3.6Human Engineering3-

693.3.6.1Closures or Covers Design Requirements3-

693.3.6.2Interior Color3-

693.3.6.2.1Rack Mounted Equipment3-

693.3.6.2.2Stowed/Deployable Equipment3-

703.3.6.2.3Colors for Soft Goods3-

703.3.6.3Full Size Range Accommodation3-

703.3.6.4Operation and Control of Payload Equipment3-

733.3.6.5Maintenance Operations3-

733.3.6.6Adequate Clearance3-

733.3.6.7Accessibility3-

743.3.6.8One-Handed Operation3-

743.3.6.9Continuous/Incidental Contact - High Temperature3-

743.3.6.10Continuous/Incidental Contact - Low Temperature3-

743.3.6.11Equipment Mounting3-

743.3.6.12Drawers and Hinged Panels3-

743.3.6.13Alignment3-

753.3.6.14Slide-Out Stops3-

753.3.6.15Push-Pull Force3-

753.3.6.16Covers3-

753.3.6.17Self-Supporting Covers3-

753.3.6.18Accessibility3-

753.3.6.19Ease of Disconnect3-

CONTENTS (Contd)

SectionPage

763.3.6.20Indication of Pressure/Flow3-

763.3.6.21Self Locking3-

763.3.6.22Connector Arrangement3-

763.3.6.23Arc Containment3-

763.3.6.24Connector Protection3-

763.3.6.25Connector Shape3-

763.3.6.26Fluid and Gas Line Connectors3-

763.3.6.27Alignment Marks or Guide Pins3-

773.3.6.28Coding3-

773.3.6.29Pin Identification3-

773.3.6.30Orientation3-

773.3.6.31Hose/Cable Restraints3-

773.3.6.32Non-Threaded Fasteners Status Indication3-

783.3.6.33Mounting Bolt/Fastener Spacing3-

783.3.6.34Multiple Fasteners3-

783.3.6.35Captive Fasteners3-

783.3.6.36Quick Release Fasteners3-

783.3.6.37Threaded Fasteners3-

783.3.6.38Over Center Latches3-

803.3.6.39Winghead Fasteners3-

803.3.6.40Fastener Head Type3-

803.3.6.41One-Handed Actuation3-

803.3.6.42DELETED3-

803.3.6.43Access Holes3-

803.3.6.44Controls Spacing Design Requirements3-

803.3.6.45Accidental Activation3-

823.3.6.45.1Protective Methods3-

823.3.6.45.2Noninterference3-

823.3.6.45.3Dead-Man Controls3-

833.3.6.45.4Barrier Guards3-

833.3.6.45.5Recessed Switch Protection3-

833.3.6.46Position Indication3-

833.3.6.47Hidden Controls3-

843.3.6.48Hand Controllers3-

843.3.6.49Valve Controls3-

843.3.6.50Toggle Switches3-

863.3.6.51Restraints and Mobility Aids3-

863.3.6.51.1Stowage Drawer Contents Restraints3-

CONTENTS (Contd)

SectionPage

863.3.6.51.2Stowage and Equipment Drawers/Trays3-

863.3.6.51.3Captive Parts3-

863.3.6.51.4Handle and Grasp Area Design Requirements3-

863.3.6.51.4.1Handles and Restraints3-

873.3.6.51.4.2Handle Location/Front Access3-

873.3.6.51.4.3Handle Dimensions3-

873.3.6.51.4.4Non-Fixed Handles Design Requirements3-

873.3.6.52Electrical Hazards3-

903.3.6.52.1Mismatched3-

903.3.6.52.2Overload Protection3-

903.3.6.52.2.1Device Accessibility3-

903.3.6.52.2.2Extractor -Type Fuse Holder3-

903.3.6.52.2.3Overload Protection Location3-

913.3.6.52.2.4Overload Protection Identification3-

913.3.6.52.2.5Automatic Restart Protection3-

913.3.6.53Audio Devices (Displays)3-

913.3.6.54Egress3-

913.3.7System Security3-

913.3.8Design Requirements3-

913.3.8.1Structural Design Requirements3-

913.3.8.1.1On-orbit Loads3-

923.3.8.1.2Safety Critical Structures Requirements3-

923.3.8.1.3First Modal Frequency3-

923.3.8.1.4Launch and Landing Loads3-

943.3.8.2Electrical Power Consuming Equipment Design3-

943.3.8.2.1Batteries3-

943.4ACCEPTANCE AND QUALIFICATION REQUIREMENTS3-

943.4.1Thermal Environment Compatibility3-

943.4.2Vibration and Sine Sweep3-

943.4.3Functional Acceptance3-

943.4.4Electrical, Electronic and Electromechanical Parts Control, Selection and Burn-In3-

953.4.5Flammability3-

953.4.6Offgassing3-

953.4.7Shock3-

953.4.8Bench Handling3-

953.4.9Payload Mass3-

953.4.10Electromagnetic Compatibility3-

CONTENTS (Contd)

SectionPage

953.4.11Acoustic Noise3-

963.4.12Safety Critical Structure Verification3-

963.4.12.1Safety Critical Structure Dimensional Check3-

963.4.12.2Safety Critical Structure Material Certification3-

963.4.13Software Acceptance3-

963.4.14Pre-Delivery Acceptance3-

963.4.15Pre-Installation Acceptance3-

963.5HRP PROGRAM REQUIREMENTS3-

963.5.1Safety3-

963.5.2Documentation Requirements3-

963.5.2.1Acceptance Data Package (ADP)3-

983.5.2.1.1ADP Statement in SOW3-

983.5.2.2Additional Required Documentation3-

14.0VERIFICATION PROVISIONS4-

14.1GENERAL4-

24.2FUNCTIONAL PERFORMANCE ACCEPTANCE TESTING4-

24.3ACCEPTANCE AND QUALIFICATION VERIFICATION METHODS4-

24.3.1Thermal Cycle Tests4-

34.3.1.1Qualification Thermal Cycle Test4-

34.3.1.2Acceptance Thermal Cycle Test4-

64.3.2Vibration Tests4-

64.3.2.1Sinusoidal Resonance Survey4-

64.3.2.2Random Vibration Test4-

74.3.2.2.1Qualification Vibration Analysis4-

74.3.2.2.2Qualification for Acceptance Vibration Test4-

74.3.2.2.3Acceptance Vibration Test4-

84.3.3Functional Testing4-

84.3.4Electrical, Electronic, and Electromechanical Parts Control, Selection, and Burn-In4-

94.3.5Flammability4-

94.3.6Offgassing4-

94.3.7Shock Test4-

104.3.8Bench Handling4-

104.3.9Payload Mass4-

104.3.10Electromagnetic Compatibility4-

104.3.11Acoustic Noise4-

CONTENTS (Contd)

SectionPage

104.3.12Safety Critical Structure Verification4-

104.3.12.1Safety Critical Structure Dimensional Check4-

104.3.12.2Safety Critical Structure Material Certification4-

104.3.13Software Acceptance4-

104.3.14Pre-Delivery Acceptance4-

114.3.15Pre-Installation Acceptance (PIA)4-

15.0PREPARATION FOR SHIPMENT5-

15.1GENERAL5-

15.2PACKING, HANDLING AND TRANSPORTATION5-

15.3PRESERVATION AND PACKING5-

15.4MARKING FOR SHIPMENT5-

25.5NASA CRITICAL SPACE ITEM LABEL5-

16.0NOTES6-

16.1DEFINITIONS6-

APPENDIX ARESERVEDA-1

APPENDIX BISS PRESSURIZED PAYLOAD INTERFACE REQUIREMENTS DOCUMENT VERIFICATION MATRIXB-1

APPENDIX CFUNCTIONAL PERFORMANCE VERIFICATION MATRIXC-1

APPENDIX DACCEPTANCE AND QUALIFICATION TEST APPLICABILITY MATRICESD-1

APPENDIX EJHB 8080.5 DESIGN GUIDANCE MATRIXE-1

LIST OF TABLES

TablePage

13.1-1EQUIPMENT ITEMS3-

33.1-2[HARDWARE DESIGNATION] SOFTWARE3-

Error! Bookmark not defined.3.2.2.1-1STOWAGE UNIT WEIGHT ALLOWANCE3-

143.2.2.1.1-1HRF SIR DRAWER CENTER-OF-GRAVITY CONSTRAINTS3-

Error! Bookmark not defined.3.2.2.2.1-1STOWAGE UNIT VOLUME ALLOWANCE3-

253.2.5.1.4-1ENVIRONMENTAL CONDITIONS ON ISS3-

273.2.5.1.5-1ISS PRESSURE RATE OF CHANGE3-

273.2.5.1.5-2MPLM PRESSURE RATE OF CHANGE3-

273.2.5.1.5-3ORBITER MIDDECK PRESSURE RATE OF CHANGE3-

303.2.5.2.1-1CONTINUOUS NOISE LIMITS3-

313.2.5.2.2-1INTERMITTENT NOISE LIMITS3-

323.2.5.3-1SURFACE INTERIOR COLORS AND PAINTS3-

Error! Bookmark not defined.3.2.5.3-2PAYLOAD REQUIRED ILLUMINATION LEVELS3-

343.2.7.1.2.1-1DIMENSIONAL TOLERANCES3-

363.2.7.2.1.1-1SIR DRAWER POWER CONNECTOR PIN ASSIGNMENTS3-

Error! Bookmark not defined.3.2.7.2.1.2-1RACK CONNECTOR PANEL J1 POWER CONNECTOR PIN ASSIGNMENTS3-

413.2.7.2.7.3-1RS03PL3-

443.2.7.3.1.1-1HRF SIR DRAWER DATA CONNECTOR PIN ASSIGNMENTS3-

Error! Bookmark not defined.3.2.7.3.1.2-1HRF RACK CONNECTOR PANEL J2 DATA CONNECTOR PIN ASSIGNMENTS3-

Error! Bookmark not defined.3.3.5.1.5-1LET-GO CURRENT PROFILE THRESHOLD VERSUS FREQUENCY3-

893.3.6.52-1LET-GO CURRENT PROFILE, THRESHOLD VERSUS FREQUENCY3-

923.3.8.1.1-1CREW-INDUCED LOADS3-

933.3.8.1.4-1RANDOM VIBRATION CRITERIA FOR HRF RACK POST MOUNTED EQUIPMENT WEIGHING 100 POUNDS OR LESS IN THE MPLM3-

933.3.8.1.4-2RANDOM VIBRATION CRITERIA FOR HRF RACK POST MOUNTED EQUIPMENT WEIGHING MORE THAN 100 POUNDS IN THE MPLM3-

933.3.8.1.4-3HRF RACK MOUNTED EQUIPMENT LOAD FACTORS (EQUIPMENT FREQUENCY 35 HZ)3-

74.3.2.2.2-1QUALIFICATION FOR ACCEPTANCE VIBRATION TEST LEVELS4-

84.3.2.2.3-1ACCEPTANCE VIBRATION TEST LEVELS4-

LIST OF TABLES (Contd)

TablePage

1D-1ACCEPTANCE AND QUALIFICATION TEST APPLICABILITY MATRIXD-

3D-2NON-CRITICAL HARDWARE QUALIFICATION TEST REQUIREMENTSD-

4D-3NON-CRITICAL HARDWARE ACCEPTANCE TEST REQUIREMENTSD-

LIST OF FIGURES

FigurePage

173.2.2.2.2.1.2-1SIR and ISIS Drawer Handles Protrusion Envelope3-

183.2.2.2.2.1.2-2On-Orbit Semi-Permanent Protrusions Envelope3-

193.2.2.2.2.1.3-1On-Orbit Temporary Protrusions Envelope3-

Error! Bookmark not defined.3.2.5.1.1.3-1ISS Temperature/Humidity Envelope3-

263.2.5.1.4-1Operating Limits of the ISS Atmospheric Total Pressure, Nitrogen and Oxygen Partial Pressures3-

283.2.5.1.5-1Manual Fire Suppression System Performance Characteristics3-

343.2.7.1.2-1HRF Rack SIR Drawer Accommodations3-

353.2.7.2.1.1-1SIR Drawer Power Connector Part Number M83733/2RA0183-

Error! Bookmark not defined.3.2.7.2.1.2-1Rack Connector Panel J1 Power Connector Part Number MS27468T17F6SN3-

383.2.7.2.2.3-1HRF Rack Power Output Ripple Voltage Spectrum3-

393.2.7.2.3-1HRF Rack Power Output Trip Curves3-

433.2.7.3.1.1-1HRF SIR Drawer Data Connector Part Number M83733/2RA1313-

Error! Bookmark not defined.3.2.7.3.1.2-1HRF Rack Connector Panel J2 Data Connector Part Number MS27468T15F35S3-

Error! Bookmark not defined.3.2.7.5.1.1-1HRF Rack/Instrument Moderate Temperature Loop Interface3-

Error! Bookmark not defined.3.2.7.6.1-1HRF Rack VES and VRS Interface Connectors3-

Error! Bookmark not defined.3.2.7.7.1.1-1HRF Rack Nitrogen Interface Connectors3-

633.2.7.9.3.2-1Manual Fire Suppression Hardware Envelope3-

643.2.7.9.3.2-2Closed Volume PFE Nozzle3-

713.3.6.4-1Arm, Hand and Thumb/Finger Strength (5th Percentile Male Data)3-

723.3.6.4-2Leg Strength at Various Knee and Thigh Angles (5th Percentile Male Data)3-

723.3.6.4-3Torque Strength3-

Error! Bookmark not defined.3.3.6.5-1Maximal Static Push Forces3-

Error! Bookmark not defined.3.3.6.5-2Male Grip Strength as a Function of the Separation Between Grip Elements3-

733.3.6.7-1Minimum Sizes for Access Openings for Fingers3-

793.3.6.33-1Minimal Clearance for Tool-Operated Fasteners3-

813.3.6.44-1Control Spacing Requirements for Ungloved Operation3-

833.3.6.45.4-1Rotary Switch Guard3-

Error! Bookmark not defined.3.3.6.49-1Valve Handle - Central Pivot Type3-

Error! Bookmark not defined.3.3.6.49-2Valve Handle - Lever Type3-

853.3.6.50-1Toggle Switches3-

883.3.6.51.4.3-1Minimum IVA Handle Dimensions for IVA Applications3-

44.3.1.1-1Qualification Thermal Cycling4-

54.3.1.2-1Acceptance Thermal Cycling4-

ACRONYMS AND ABBREVIATIONS

AC

Alternating Current

ADP

Acceptance Data Package

A

Ampere

ANSI

American National Standards Institute

APID

Application Process Identification

APM

Attached Pressurized Module

ASC

Aisle Stowage Container

ATT

Acceptance Thermal Test

ATV

Automated Transfer Vehicle

AVT

Acceptance Vibration Testing

C&DH

Command and Data Handling

CAM

Centrifuge Accommodation Module

CCB

Configuration Control Board

CCSDS

Consultative Committee for Space Data Systems

CFU

Colony Forming Units

CG

Center of Gravity

CI

Cargo Integration

CIL

Critical Items List

cm

centimeters

COTS

Commercial Off-the-Shelf

CTBE

Cargo Transfer Bag Equivalent

dB

Decibels

dBA

Acoustic Decibel Level

DC

Direct Current

DGCS

Display and Graphics Commonality Standards

dia

diameter

DR

Discrepancy Report

DRDs

Data Requirements Documents

EEE

Electrical, Electronic, and Electromechanical

EIA

Electronic Industry Association

EMC

Electromagnetic Compatibility

EMI

Electromagnetic Interference

EPCE

Electrical Power Consuming Equipment

ESD

Electrostatic Discharge

EVA

Extravehicular Activity

EXPRESS

EXpedite the PRocessing of Experiments to Space Station

fc

footcandle

FIAR

Failure Investigation Analysis Report

ACRONYMS AND ABBREVIATIONS (Contd)

FMEA

Failure Modes and Effects Analysis

FPD

Flight Projects Division

FSS

Fluid System Servicer

ft

feet

g

Gravity

GFCI

Ground Fault Circuit Interrupter

GHz

Gigahertz

GIDEP

Government and Industry Data Exchange Program

GPVP

Generic Payload Verification Plan

GSE

Ground Support Equipment

HR

Hazard Report

hr

Hour

HRD

Hardware Requirements Document

HRF

Human Research Facility

HRP

Human Research Program

Hz

Hertz

ICD

Interface Control Document

IDD

Interface Definition Document

IEEE

Institute of Electrical and Electronic Engineers

IMS

Inventory Management System

IMV

Intermodule Ventilation

in

inch

ISIS

International Subrack Interface Standards

ISPR

International Standard Payload Rack

ISS

International Space Station

ITCS

Internal Thermal Control System

IVA

Intravehicular Activity

JEM

Japanese Experiment Module

JSC

Johnson Space Center

kg

Kilogram

kHz

Kilohertz

kPa

KiloPascal

KSC

Kennedy Space Center

lb

pound

lbf

pounds force

lbm

Pounds Mass


m/s

Meters Per Second

mA

Milliamperes

max

Maximum

MDM

Multiplexer-Demultiplexer Module

MDP

Maximum Design Pressure

MHz

Megahertz

MIL-ER

Military Established Reliability

min

minimum

min

minute

ML

milliliter

mm

millimeter

mm Hg

Millimeters of Mercury

MOTS

Modified Off-the-Shelf

MPLM

Mini Pressurized Logistics Module

MRDL

Medium Rate Data Link

ms

Milliseconds

MSFC

Marshall Space Flight Center

MTL

Moderate Temperature Loop

MUA

Material Usage Agreement

N

Newton (metric force measurement)

N/A

Not Applicable

N2

Nitrogen

Nm

Nanometer

NASA

National Aeronautics and Space Administration

NASDA

National Space Development Agency of Japan

NSTS

National Space Transportation System (Do not useuse SSP)

NTSC

National Television Standards Committee

O2

Oxygen

Oct

Octave

ORU

Orbital Replacement Unit

P/L

Payload

Pa

Pascal

PDA

Pre-Delivery Acceptance

PFE

Portable Fire Extinguisher

PHTR

Packaging, Handling, and Transportation Records

PIA

Payload Integration Agreement

PPC

Point-to-Point Communication

PRD

Program Requirements Document

psi

pounds per square inch

psia

pounds per square inch absolute

psig

pounds per square inch


PSRP

Payload Safety Review Panel

PU

Panel Unit

PUL

Portable Utility Light

QAVT

Qualification for Acceptance Vibration Testing

QTT

Qualification Thermal Test

QVA

Qualification Vibration Analysis

Rad

Radiation Absorbed Dose

RIC

Rack Interface Controller

RMA

Reliability, Maintainability and Availability

rms

Root Mean Square

RSP

Resupply Stowage Platform

RSR

Resupply Stowage Rack

SD

Standard Deviation

SE&I

Systems Engineering and Integration

sec

second

SEE

Single Event Effect

SIR

Standard Interface Rack

SLPM

Standard Liter per Minute

SOW

Statement of Work

SPIP

Station Program Implementation Plan

SPL

Sound Pressure Level

SSPC

Solid State Power Controller

TBD

To Be Determined

TBR

To Be Resolved

TIA

Telecommunications Industry Association

TM

Technical Memo

TPS

Task Performance Sheet

UIP

Utility Interface Panel

UOP

Utility Outlet Panel

USL

United States Lab

V

Volts

VC-S

Visibly Clean - Sensitive

Vdc

Volts Direct Current

VDS

Verification Data Sheet

VES

Vacuum Exhaust System

VIPER drawer

VOILA Integrated Processor Electronics Rack drawer

VOILA

Visuomotor and Orientation Investigation on Long-duration Astronauts

VRS

Vacuum Resource System


VVS

Vacuum Vent System

WGS

Waste Gas System

WS2

HRF Workstation 2

WSTF

White Sands Test Facility

C

Degrees Celsius

F

Degrees Fahrenheit

(

pi

(sec

Microsecond

1.0SCOPE

This specification defines the Human Research Facility (HRF) program requirements for Visuomotor and Orientation Investigation on Long-duration Astronauts (VOILA). The VOILA is a subrack payload that will be installed in an HRF rack and will use cameras mounted in the ISS module aisleway to record crew motion when exposed to visual stimulus.

The primary governing document for the requirements levied in this document is LS-71000, Program Requirements Document for the Human Research Facility.

The requirements in Sections 3, 4 and 5 of this document consist of a minimum set of constraints for the VOILA hardware and software.

The HRF Project Office is the controlling authority for this document. The HRF Configuration Control Board (CCB) or a delegated authority must approve any deviations from the requirements of this document.

2.0APPLICABLE DOCUMENTS

The following applicable documents of the exact issue shown herein form a part of this specification to the extent specified herein. If a revision level or date is not cited, the latest version of the document should be used.

All specifications, standards, exhibits, drawings or other documents referenced in this specification are hereby incorporated as cited in the text of this document. Any updated revisions to documents specified herein shall be reviewed to determine the impact to the design. Changes to the design or this document shall only be made upon the direction of the HRF CCB.

2.1Documents

Document Number

Revision

Document Title

FED-STD-595

Rev. B12/89

Colors Used in Government Procurement

JPG 5335.3

Basic

Lyndon B. Johnson Space Center Quality Management System (QMS)

LS-60077

TBR

Standard Interface Rack Specification

LS-71000

Rev. B

Program Requirements Document for the Human Research Facility

LS-71011

TBR

Acoustic Noise Control & Analysis Plan for Human Research Facility Payloads and Racks

LS-71014

TBR

Mass Properties Control Plan Human Research Facility Payload and Racks

LS-71016

TBR

Electromagnetic Compatibility Control Plan for the Human Research Facility

LS-71020

Rev. B Chg 1TBR

Software Development Plan for the Human Research Facility

MIL-PRF-19500

Rev. M10/99

Performance Specification Semiconductor Devices, General Specification for

MIL-STD-810

Rev. E7/95

Environmental Test Methods and Engineering Guidelines

MIL-STD-1686

Rev. C10/95

Electrostatic Discharge Control Program for Protection of Electrical and Electronic Parts, Assemblies and Equipment (Excluding Electrically Initiated Explosive Devices)

NASA TM 102179

6/91

Selection of Wires and Circuit Protective Devices for STS Orbiter Vehicle Payload Electrical Circuits

NSTS/ISS 13830

Rev. C,Ch. 12/99

Payload Safety Review and Data Submittal Requirements for Payloads Using the Space Shuttle and International Space Shuttle

NSTS-1700.7

Rev. B, Ch. 115/01

Safety Policy and Requirements For Payloads Using the Space Transportation System

NSTS-1700.7BISS ADDENDUM

Basic, Ch. 48/02

Safety Policy and Requirements For Payloads Using the International Space Station

NSTS/ISS 18798

Rev. B, Ch. 72/00

Interpretations of NSTS/ISS Payload Safety Requirements

NSTS-21000-IDD-MDK

Rev. B Chg 1510/02

Shuttle/Payload Interface Definition Document for Middeck Accommodations

SN-C-0005

Rev. D Chg 67/98

Space Shuttle Contamination Control Requirements

SP-T-0023

Rev. C05/01

Specification, Environmental Acceptance Testing

SSP30233

Rev. F7/99

Space Station Requirements for Materials and Processes

SSP30237

Rev. F Chg 203/02

Space Station Electromagnetic Emission and Susceptibility Requirements

SSP30240

Rev. D12/02

Space Station Grounding Requirements

SSP30242

Rev. F

12/02

Space Station Cable/Wire Design and Control Requirements for Electromagnetic Compatibility

SSP30243

Rev. G12/02

Space Station Requirements for Electromagnetic Compatibility

SSP30245

Rev. E, Ch. 1610/01

Space Station Electrical Bonding Requirements

SSP30312

Rev. H,

Ch. 211/02

Electrical, Electronic, and Electromechanical (EEE) and Mechanical Parts Management and Implementation Plan for Space Station Program

SSP30512

Rev. C9/94

Space Station Ionizing Radiation Design Environment

SSP 30695

Rev. A01/95

Acceptance Data Package Requirements Specification

SSP 41017

Rev. F1/02

Rack to Mini Pressurized Logistics Module Interface Control Document (ICD) Part 1

SSP41175-2

Rev. G2/03

Software Interface Control Document (ICD) Part 1 Station Management and Control to International Space Station Book 2, General Software Interface Requirements

SSP50005

Rev. C,Ch. 89/01

International Space Station Flight Crew Integration Standard (NASA-STD-3000/T)

SSP50007

Rev. B,

Ch. 29/01

Space Station Inventory Management System Label Specification

SSP50008

Rev. C7/01

International Space Station Interior Color Scheme

SSP 50313

Draft

Display and Graphics Commonality Standard Document

SSP 50467

Baseline

11/00

ISS Cargo Stowage Technical Manual: Pressurized Volume

SSP52005

Rev. C12/01

Payload Flight Equipment Requirements and Guidelines for Safety-Critical Structures

SSP52050

Rev. E1/03

Software Interface Control Document Part 1, International Standard Payload Rack to International Space Station

SSP57000

Rev. E11/00

Pressurized Payloads Interface Requirements Document

SSP57001

Rev. C10/00

Pressurized Payloads Hardware Interface Control Document Template

SSQ 25002

Rev. B 1/02

Supplemental list of Qualified Electrical, Electronic, and Electromechanical (EEE) Parts, Manufacturers, and Laboratories (QEPM&L)

2.2Order 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.

3.0SYSTEM REQUIREMENTS

3.1Item Definition

The following items of VOILA will be designed and certified under this requirements document for use on International Space Station (ISS) as a part of the HRF program. The HRF Rack hardware used with this hardware is certified under separate documentation that is maintained by the appropriate program(s).

Table 3.1-1 lists the equipment items covered by this document, including the stowage kits that will be used to transport the items and contain the items on-orbit.

TABLE 3.1-1. EQUIPMENT ITEMS

Item Name

Part Number

Class

Quantity

Notes

VOILA Integrated Processor Electronics Rack (VIPER) Drawer

SEG46119702-301

I

3

Qualification/Trainer, Flight, Flight Backup

Electronics provided by PI

Chassis & integration provided by NASA

Head Mounted Display (HMD)

85-10100

I

2

Flight, Flight Backup

Provided by PI

Headphones

85-41000

I

2


Provided by PI

Subject Input Device (SID)

85-40600

I

2


Provided by PI

Paddle

85-40500

I

2


Provided by PI

Hand Switch

85-40530.01

I

2


Provided by PI

Optical Tracker Camera Bar

85-20100

I

3

Flight pair, Flight Backup single

Provided by PI

Chest Pack Interconnect Box

85-40400

I

2


Provided by PI

Subject Restraint System (SRS) Vest

SJG46119738-301

I

2


Provided by NASA

Subject Microphone

85-41100

I

2


Provided by PI

Torso Marker Plate

85-40900

I

1

Flight only

Provided by PI

Spring Reel Assembly

SEG46119710-301

I

4

Flight pair, Flight Backup pair

Provided by NASA

SRS Platform

85-40301

I

1

Flight only

Provided by PI

SRS Quasi-free Float Attachment

85-40326

I

1

Flight only

Provided by PI

Subject Surveillance Camera

85-41200

I

2

Flight, Flight Backup Provided by PI

W1, HRF to VIPER Data Cable

85-40801

I

1

Flight only

Provided by PI

W3, CODA to VIPER Cable

85-40803

I

1

Flight only

Provided by PI


85-40804

I

1

Flight only

Provided by PI

W5, Platform to VIPER Cable

85-40805

I

1

Flight only

Provided by PI

W6, VIPER to Chest Pack Cable

85-40806

I

1

Flight only

Provided by PI

W7, Chest Pack to Torso Cable

85-40807

I

1

Flight only

Provided by PI

W8, Chest Pack to Paddle

85-40808

I

1

Flight only

Provided by PI

W9, Chest Pack to SID

85-40809

I

1

Flight only

Provided by PI

Head Mounted Display (HMD)

85-10100

III

2

BDC, Training

Provided by PI

Headphones

85-41000

III

1

BDC, Training

Provided by PI

Subject Input Device (SID)

85-40600

III

1

BDC, Training

Provided by PI

Paddle

85-40500

III

1

BDC, Training

Provided by PI

Hand Switch

85-40530.01

III

1

BDC, Training

Provided by PI


85-20100

III

2

BDC, Training

Provided by PI

Chest Pack Interconnect Box

85-40400

III

1

BDC, Training

Provided by PI

Subject Restraint System (SRS) Vest

SJG46119738-301

III

1

BDC, Training

Provided by NASA

Subject Microphone

85-41100

III

1

BDC, Training

Provided by PI

Torso Marker Plate

85-40900

III

1

BDC, Training Provided by PI

Spring Reel Assembly

SED46116446-301

III

2

BDC, Training

Provided by NASA

SRS Platform

85-40301

III

1

BDC, Training

Provided by PI

SRS Quasi-free Float Attachment

85-40326

III

1

BDC, Training

Provided by PI

Subject Surveillance Camera

85-41200

III

1

BDC, Training Provided by PI

W1, HRF to VIPER Data Cable

85-40801

III

1

BDC, Training

Provided by PI


85-40803

III

1

BDC, Training

Provided by PI


85-40804

III

1

BDC, Training

Provided by PI

W5, Platform to VIPER Cable

85-40805

III

1

BDC, Training

Provided by PI

W6, VIPER to Chest Pack Cable

85-40806

III

1

BDC, Training

Provided by PI

W7, Chest Pack to Torso Cable

85-40807

III

1

BDC, Training

Provided by PI

W8, Chest Pack to Paddle

85-40808

III

1

BDC, Training

Provided by PI

W9, Chest Pack to SID

85-40809

III

1

BDC, Training

Provided by PI

Table 3.1-2 lists the software items covered by this document.

Table 3.1-2. VOILA Software

Program Name

Part Number

Notes

VOILA Software

TBD

3.1.1Experiment Description

3.1.1.1Experiment Overview

VOILA will extend, simplify, and merge two sensory motor and performance experiments originally developed for the 1998 STS-90 Neurolab mission. The two components retain separate numbers (E085/E507) on ISS, but are performed together. The experiments use the HRF Workstation 2 as science kiosk to perform short (typically 30 minute long) tests to study the role of visual, vestibular, and haptic cues on spatial orientation and motor behavior. The experiment utilizes virtual environment generation accessories first developed for the Neurolab as a tool to study these processes during and after long duration (3-6 month) orbital flight. Restrained and free-floating subjects wear a wide field of view, color stereo head mounded display. Protocols are based on 1-G paradigms, require little set-up time, and can be selected and performed by an astronaut in an automated fashion using Session Manager software. Pre-flight, in-flight, and post-flight performances of each protocol are planned on each ISS increment.

The Specific Objectives are to determine the effects of microgravity on:

(1) The influence of scene symmetry, rotation, haptic cues, and expected orientation on static and dynamic self tilt (Virtual Tilting and Tumbling Room Protocols);

(2) the onset of x-axis illusory linear self-motion without haptic cues (Linear Vection Protocol);

(3) the effect of perceived orientation on visual object recognition and shape recognition (Object Recognition Protocols);

(4) whether information used in grasping remembered objects is stored in head fixed, body fixed, or exocentric reference frames (Virtual Grasping Protocol); and

(5) how the timing of catching movements depends on anticipation of downward acceleration (Virtual Catching Protocol).

The general hypothesis is that mental processes involved in self-orientation, object perception and motor control will be fundamentally altered in microgravity environments, as evidenced by visual reorientation, inversion, and proprioceptive illusions frequently reported in-orbit by astronauts. These experiments on self-orientation, linear vection, object perception and motor control will help to characterize the contribution of gravity to the mechanisms underlying these activities.

3.1.1.2Operational Overview

In each session, based on the amount of crew time available, the Session Manager program suggests one or more of 5 different visual perception protocols and one or more of 4 different visuomotor tasks. In-flight protocols are performed in up to 3 possible conditions: quasi-free floating, lightly restrained, and/or with constant-force springs (simulated gravity).

Visual Perception

Protocol 1:Tilted Room. Subject indicates perceived vertical while viewing a series of tilted scenes.

Protocol 2:Tumbling Room. Subject indicates vection magnitude and surface identity while viewing rotating scenes.

Protocol 3:Linear Vection. Subject indicates vection onset and magnitude while viewing a moving corridor scene.

Protocol 4:Figures. Subject indicates which complex 2D figure seems most familiar.

Protocol 5:Shading. Subject indicates which shaded circle seems most convex.

Visuomotor Coordination

Protocol 6:Grasping. Upright. Subjects align the hand with an object oriented in 3D space.

Protocol 7:Grasping. Head Tilt. Subjects repeat Protocol 6 with 30( head tilt.

Protocol 8:Pointing. Subjects perform rapid point-to-point movements with the dominant hand.

Protocol 9:Interception. Subjects intercept a flying ball with the dominant hand.

The following protocols will only be performed pre-flight and post-flight:

Protocol 10:Tilted Bed. Subject aligns the bed to their subjective horizontal in a dark room.

Protocol 11:Luminous Line. Subjects align a luminous line to their subjective vertical meridian in a dark room.

Protocol 12:Tilted grasping. Subjects perform Protocol 6 while seated in a chair inclined by 30( in the frontal plane.

3.1.1.3Hardware Overview

The VOILA experiment depicted in figure 3.1.1.3-1 will utilize the Human Research Facility Workstation 2 (WS2), which is a rack-mounted computer drawer located in HRF Rack 1 and Rack 2. The VOILA experiment will use the following components of the WS2:

1. The graphics accelerator cards in the WS2 are used to render virtual environments on the Head Mounted Display for the experiment protocols.

2. The WS2 sound card is used to record the subjects audio notes.

3. The WS2 data acquisition card is used to capture acceleration data from the Paddle for the Interception protocol.

4. The USB ports of the WS2 are used to operate the head and body tracking system, the SID, and the Video Surveillance Camera.

5. The VOILA software will reside and operate on the WS2 hard drive.

The VOILA experiment also utilizes the HRF Flat Screen Display and the Workstation Keyboard to operate the VOILA Session Manager software and the HRF Common Software on the WS2.

VOILA uses the 4 PU VIPER Drawer to interface its peripherals to the HRF WS2. The PI-provided electronics are housed in a NASA-provided chassis. The electrical components include power converters, head and body tracker control boxes, USB-to-serial converter, and USB hub. The 4PU VIPER Drawer will be located in HRF Rack 1 or Rack 2, near the WS2. It receives 28 VDC power from the HRF rack, and is cooled by the HRF common fan.

The head and body tracker system is built from COTS components. It consists of two major systems: (1) an inertial tracking system based on the Intersense IS300 Pro tracking system and (2) an optical tracking system based on the Charnwood Dynamics CODA camera system. The inertial tracking system uses 1-4 inertial cubes containing linear accelerometers and angular rate sensors to detect orientation and position information. Inertial cubes are mounted on the HMD, on the Paddle, and in the Chest Pack. The optical tracking system provides a second source of position and orientation information by tracking a set of infrared LED markers with cameras. The infrared LED markers are mounted on the HMD, the Paddle, and the Chest Pack. Three cameras are mounted into each Optical Tracker Camera Bar, and two bars are used to track all of the sensors. The Optical Tracker Camera Bars are mounted into the seat track at opposite ends of the module such that the subject wearing the infrared LED markers is in between them. The information from the inertial and the optical systems are combined, resulting in an accurate determination of the objects position and orientation in space. The VIPER Drawer contains the CODA Hub, which controls the cameras and infrared LED markers, and Intersense control box, which integrates the information.

The Subject Restraint System (SRS) is composed of four parts which are used to restrain the subjects in certain postures, prevent them from drifting into other equipment, and provide haptic feedback for certain protocols. The four parts of the Subject Restraint System are the SRS Vest, the SRS Platform, the SRS Spring Reel Assemblies, and the SRS Quasi-free Float Attachment.

The SRS Vest is an adjustable vest worn by the subject. The vest has attachment points for the SRS Spring Reel Assemblies along its waist, and for the SRS Quasi-free Float Attachment on the front and back of the Vest near the wearers center of gravity. A number of adjustment straps on the Vest allow the subject to distribute the force from the SRS spring coils onto the waist and shoulders. The Vest has an attachment point for the Chest Pack, and attachment points for temporary stowage of the SID, the Hand Switch, and the Paddle. The Vest has an attachment point for a Torso Marker Plate, which is a metal plate with infrared LED sensors attached to track the subjects upper torso.

The SRS Platform is an adjustable aluminum platform that mounts onto the seat tracks. A set of infrared LED markers is mounted on the Platform to provide a stationary reference frame for the optical tracking system. Subjects will stand on the SRS Platform when using the SRS Spring Reel Assemblies to simulate gravity in the Room and Vection protocols. It can be folded into a chair for the seated position, and unfolded into a bed for the supine position during the Grasping and Interception protocols. It has removable padding for comfort and wide Velcro straps for restraint.

The SRS Spring Reel Assemblies are two constant force springs that provide 30-40 lbs each of downward force to simulate the haptic sensations of gravity on the subjects feet. One end of each spring is mounted into a slot on the SRS platform. The other end of each spring is attached to the bottom of the SRS Vest. The Spring Reel Assemblies were originally designed and used for the Neurolab E136 experiments.

The SRS Quasi-free Float Attachment is a pole, approximately 1 meter in length, which has an attachment point on one end that fits into a seat track. The other end has a swivel joint and a quick-release attachment point for the SRS vest. The swivel joint allows the subject to drift rotationally somewhat while free-floating but prevents them from drifting into other equipment or out of the head/body trackers working volume. The joint can also be locked to prevent large rotational motion.

The Chest Pack Interconnect Box is a connection box that is worn on the front of the SRS Vest. It has connections for devices that are used by the subject or mounted on the SRS Vest. It connects with the VIPER Drawer through one cable that provides power and data channels. The SID, paddle, HMD microphone, and a set of infrared LED markers on the SRS vest will connect into the Chest Pack Interconnect Box. The Chest Pack Interconnect Box will contain an inertial cube and have infrared LED markers mounted on its exterior.

The Head Mounted Display (HMD) is worn on the subjects head and provides a stereoscopic display to the wearer. It is a modified Kaiser ProView80 LCD-based stereoscopic display with a large field of view (64 degrees horizontal x 48 degrees vertical). The HMDs used in the Neurolab E136 experiments are upgraded with lower power LCD displays, higher contrast units, and stronger space flight quality plastic frames. One inertial cube and several infrared LED markers will be mounted on the outer casing of the HMD. The HMD will connect to the front panel of the VIPER Drawer with two cables.

The Subject Microphone is a modified COTS computer microphone, used for subject voice recording. The Subject Microphone will be mounted to the HMD or the SRS Vest for hands-free operation.

The Headphones are modified COTS noise cancellation headphones. They will be worn with the HMD to suppress audio directionality cues.

The Subject Input Device (SID) is a modified COTS gamepad with two joysticks and several buttons. The SID will connect to the Chest Pack Interconnect Box. It will have an attachment point on the SRS Vest for temporary stowage. Subjects will respond to stimuli presented in the Room, Vection, Figures, and Shading protocols using the SID.

The Paddle is a custom-made interface device, consisting of a handle that can be gripped with either hand. In the dominant hand, the Paddle is used to measure hand movement, position and orientation during the Grasping and Interception protocols. The Paddle contains one inertial cube and a linear accelerometer to detect motion onsets. A set of infrared LED markers is mounted on the exterior. The Paddle is connected to the Chest Pack Interconnect Box through a single Y-cable that it shares with the Hand Switch.

The LPPA tilt chair

The Hand Switch is a modified COTS device with a single button that can be operated with either hand. During the Grasping and Interception protocols, it is held in the hand opposite the Paddle, and the button is pressed to trigger the beginning of a trial. The Hand Switch is connected to the Chest Pack Interconnect Box through a single Y-cable that it shares with the Paddle.

The Subject Surveillance Camera is a modified COTS device used to capture still images of the subject performing the experiment. It will be mounted to the wall or ceiling of the module with a seat track attachment.

HRF Rack

Workstation 2

VIPER Drawer

Power

Power

Data

Fan

Controller

Data

Workstation

Keyboard

Flat Screen

Display

Chest Pack

(LED Markers,

Inertial Cube)

Head Mounted

Display

(LED Marke

rs,

Inertial Cube)

Subject

Microphone

Torso

Marker Plate

(LED

Markers)

Headphones

Hand

Switch

Paddle

(LED Markers, Inertial Cube)

Subject

Input

Device

Subject

Surveillance

Camera



Area

Microph

one

Subject Restraint System Platform

(LED Markers)

Vest

Spring

Reel

Assy.

Spring

Reel

Assy.

Quasi

-

free Float Attachment

Figure 3.1.1.3-1 - VOILA hardware block diagram

3.2Characteristics

3.2.1Performance Characteristics

3.2.1.1Functional Performance Characteristics

3.2.1.1.1Audio/Video Outputs

A.VOILA shall provide stereoscopic video outputs via a head-mounted display.

B.VOILA shall provide the following:

1. identical monoaural outputs via left and right headphone speakers

2. module ambient noise as measured from a single area microphone.

3.2.1.1.2 Measurement Ranges

VOILA shall measure the following parameters within the following ranges:

A.module ambient noise

1-150 dB

B.subject voice

1-150 dB

C.joystick inputs

D.hand-held pushbutton inputs

E.subject head position

0-200 cm in three orthogonal axes

F.subject head orientation

0-359 degrees in three orthogonal axes

G. subject torso position


H. subject torso orientation


I. restraint platform position


J. restraint platform orientation0-359 degrees in three orthogonal axes

K. paddle position


L. paddle orientation


M.paddle acceleration

+/- 100 cm/s2

Nsubject surveillance photos

3.2.1.1.3Measurement Accuracies

VOILA shall measure the following parameters with the following accuracies:

A. module ambient noise

+/- 0 dB

B. subject voice

+/- 0 dB

C. subject head position

+/- 0.2 cm

D. subject head orientation

+/- 0.1 deg

E. subject torso position

+/- 0.2 cm

F.subject torso orientation

+/- 0.15 deg

G.restraint platform position

+/- 0.2 cm

H.restraint platform orientation+/- 0.15 deg

I. paddle position

+/- 0.2 m

J. paddle orientation

+/- 0.15 deg

K. paddle acceleration

+/- 0.1 cm/s2

3.2.1.1.4Measurement Frequencies

VOILA shall measure the following parameters at the following frequencies:


analog

B. subject voice

analog

C. joystick inputs

TBD

D. hand-held pushbutton inputsTBD

E. subject head position

60 Hz

F. subject head orientation

60 Hz


60 Hz


60 Hz


60 Hz

J. restraint platform orientation60 Hz

K. paddle position

60 Hz


60 Hz

M. paddle acceleration

500 Hz

N. subject surveillance photosTBD

3.2.1.1.5Physical Boundaries for Measurement Performance Characteristics

VOILA shall meet 3.2.1.1.2, 3.2.1.1.3, and 3.2.1.1.4 position and orientation measurements within a 2 meter x 2 meter x 2 meter cube.

3.2.1.1.6Data Storage Frequencies

VOILA shall store the following with the following frequencies:


analog

B. subject voice

analog

C. joystick inputs

TBD Hz

D. hand-held pushbutton inputsTBD Hz

E. subject head position

60 Hz

F. subject head orientation

60 Hz


60 Hz


60 Hz


60 Hz

J. restraint platform orientation60 Hz

K. paddle position

60 Hz


60 Hz

M. paddle acceleration

500 Hz

N. subject surveillance photosTBD

3.2.1.1.7Data Storage Capacity

VOILA shall store parameters per 3.2.1.1.6 for:

A. durations of 30 minutes per session.

B. TBD sessions.

3.2.1.1.8Data Storage Return Logistics

VOILA data storage media shall be removable/replacable.

3.2.1.1.9Data Downlink

VOILA shall downlink parameters stored per 3.2.1.1.6 via the HRF Workstation 2.

3.2.1.1.10Software Update Uplink

VOILA shall uplink software updates for HRF Workstation 2 based VOILA experiment software.

3.2.1.1.11Design

A.VOILA Head Mounted Display HMD shall be operable by subjects wearing eyeglasses.

B.VOILA shall allow the subject to make software menu selections.

C.VOILA subject input devices shall be operable via either hand.

D.VOILA equipment not worn or held by the subject shall mount to the ISS Seat Track.

E.VOILA shall provide a 35.0 lb +/- 1.0 lb load originating from the subject restraint platform to the subject with adjustable load distribution between the subject hips and shoulders. This requirement is only applicable when the subject is in the standing posture.

F.VOILA shall provide a quasi-free float attach structure which allows the subject rotational freedom about the subject attach point as acceptable to the Principal Investigator.

G.The VOILA quasi-free float attach structure shall be 1 meter +/- 0.1 meter.

H.VOILA shall provide a Subject Restraint Platform which:

1.provides a subject foot plate.

2.can be adjusted on-orbit to provide a subject seat with backrest and subject restraints.

3.can be adjusted on-orbit to provide a supine/prone plate with subject restraints.

3.2.2Physical Characteristics

3.2.2.1 Mass and Center of Gravity Properties

3.2.2.1.1 VOILA Drawer Mass

The VOILA drawer mass shall be less than 64 pounds per set of slide guides, or a total of 64 pounds (29.03 kg).

3.2.2.1.2 VOILA Ancillary Hardware Mass

VOILA hardware to be stowed outside of the VOILA main housing shall meet the weight limitations of each M02 Bag, 200 lbf, when stowed as defined in section 3.2.2.2.1.B.

3.2.2.1.3VOILA Drawer Center-of-Gravity Constraints

HRF rack mounted SIR drawer instruments shall meet the center of gravity constraints specified in Table 3.2.2.1.1-1, HRF SIR Drawer Center-of-Gravity Constraints. (LS-71000, Section 6.2.1.2.4)

3.2.2.2Envelope

3.2.2.2.1 Stowed Envelope

A. VOILAs main housing will consist of a single 4PU SIR drawer.

B. VOILA hardware to be stowed outside of the VOILA main housing shall fit within one M02 Transfer Bag, 34.25 in (W) x 20.5 in (D) x 19.5 in (H), in the VOILA stowed configuration. (NOTE: The VOILA platform (standing/supine) will be stowed outside the stowage bag.)

TABLE 3.2.2.1.1-1. HRF SIR DRAWER CENTER-OF-GRAVITY CONSTRAINTS

Drawer Configuration

X (in)Min.

X (in)Max.

Y (in)Min.

Y (in)Max.

Z (in)Min.

Z (in)Max.

Single Slide Drawer (4 PU)

-1.75

+1.75

+7.99

+12.00

-0.63

+0.87

Double Slide Drawer (8 PU)

-2.20

+2.20

+10.24

+14.00

+1.675

+3.975

Triple Slide Drawer (12 PU)

-1.50

+1.50

+9.74

+13.00

+6.37

+8.87

NOTE:Center of gravity envelope is measured from the drawer coordinate system as defined below. The geometric center for Z axis is measured from the centerline of the bottom-most rail toward the top of the drawer. Total maximum integrated mass (including drawer, contents and slides) on any one set of slides is limited to 64 pounds. Multiple-slide drawers are to evenly distribute loading between the sets of slides.

Drawer Front Panel

(Inside Face)

Drawer Slide

Centerline

+X

+Y

+Z

3.2.2.2.2Deployed Envelope

3.2.2.2.2.1On-Orbit Payload Protrusions

Definitions for on-orbit permanent protrusions, on-orbit semi-permanent protrusions, on-orbit temporary protrusions, on-orbit momentary protrusions, and protrusions for on-orbit keep alive payloads can be found in Section 6.1, Definitions. The requirements in Section 3.2.2.2.2.1 apply to installation and operation activities, but not to maintenance activities.

NOTE:The on-orbit protrusion requirements in this section are applicable to when the payload is on-orbit and do not apply to other phases of the transportation of the payload (e.g., launch, landing, Mini Pressurized Logistics Module (MPLM) installation). (LS-71000, Section 6.2.1.1.5)

A.On-orbit protrusions, excluding momentary protrusions, shall not extend laterally across the edges of the rack or pass between racks. (LS-71000, Section 6.2.1.1.5.A)

B.The integrated rack hardware, excluding momentary protrusions, shall not prevent attachment of Reliability, Maintainability and Availability (RMA) on any seat track attach holes. (LS-71000, Section 6.2.1.1.5.B)

Constraints which may be associated with payload protrusions include:

removal of the protrusion during rack installation, translation, and crew translation

removal of the protrusion if RMA is installed on the rack

removal of the protrusion to prevent interference with microgravity operations

removal or powering off of the rack if the protrusion blocks Portable Fire Extinguisher (PFE) access or the fire indicator

may limit the rack location (e.g., Protrusion located in the floor and the ceiling are limited to a total of no more than 12 inches.)

may limit operation of the payload

As is indicated by the constraints above, protrusions have a negative impact on crew operations and are to be minimized. (LS-71000, Section 6.2.1.1.5)

3.2.2.2.2.1.1On-Orbit Permanent Protrusions

Not applicable to VOILA.

3.2.2.2.2.1.2On-Orbit Semi-Permanent Protrusions

A.SIR and International Subrack Interface Standard (ISIS) drawer handles shall remain within the envelope shown in Figure 3.2.2.2.2.1.2-1. (LS-71000, Section 6.2.1.1.5.2.A) Note: VOILA will take exception to this requirement.

B.Other on-orbit semi-permanent protrusions shall be limited to no more than 500 square inches within the envelope shown in Figure 3.2.2.2.2.1.2-2. (LS71000, Section 6.2.1.1.5.2.B) Note: VOILA will take exception to this requirement.

NOTE:The sum of the on-orbit semi-permanent protrusions and the on-orbit protrusion for keep alive payloads is limited to no more than 500 square inches. (LS-71000, Section 6.2.1.1.5.2.B)

NOTE:The SIR and ISIS drawer handles are not included in the 500 square inch limit. (LS-71000, Section 6.2.1.1.5.2.B)

C.All on-orbit semi-permanent protrusions shall be designed to be removable by the crew with hand operations and/or standard Intravehicular Activity (IVA) tools. (LS-71000, Section 6.2.1.1.5.2.C)

Figure 3.2.2.2.2.1.2-1. SIR and ISIS Drawer Handles Protrusion Envelope

3. All sections mentioned in figure refer to the applicable section of SSP57000E.

Figure 3.2.2.2.2.1.2-2. On-Orbit Semi-Permanent Protrusions Envelope

3.2.2.2.2.1.3On-Orbit Temporary Protrusions

A.On-orbit temporary protrusions shall remain within the envelope shown in Figure 3.2.2.2.2.1.3-1. (LS-71000, Section 6.2.1.1.5.3.A) Note: VOILA will take exception to this requirement.

B.The combination of all on-orbit temporary protrusions for the integrated rack shall be designed such that they can be eliminated or returned to their stowed configuration by the crew with hand operations and/or standard IVA tools within 10 minutes. (LS-71000, Section 6.2.1.1.5.3.B)

NOTE:Integrated racks must provide stowage for on-orbit temporary protrusions within their stowage allocation. (LS-71000, Section 6.2.1.1.5.3)

NOTE:On-orbit temporary protrusions for payloads located in the floor or ceiling are limited to 6 inches each or a total of 12 inches for both floor and ceiling. (LS-71000, Section 6.2.1.1.5.3)

4. All sections mentioned in figure refer to the applicable section of SSP57000E.

Figure 3.2.2.2.2.1.3-1. On-Orbit Temporary Protrusions Envelope

3.2.2.2.2.1.4On-Orbit Momentary Protrusions


3.2.2.2.2.2 Deployed Envelope Dimensions

There are no requirements for deployed envelope dimensions beyond those documented in section 3.2.2.2.2.1.

3.2.3Reliability, Quality and Non-Conformance Reporting

A.Not applicable to VOILA.

B.Quality

1. Quality Assurance for VOILA hardware developments, handling, or testing at JSC shall be implemented in accordance with JPG 5335.3, JSC Quality Manual. (LS-71000, Section 7.3.1)

2. Quality Assurance for VOILA hardware developments, handling, or testing at MIT shall be implemented in accordance with the following contract: . (LS-71000, Section 7.3.1)

C.Non-Conformance Reporting

1.For flight hardware produced under a contract or subcontract at a site other than JSC, non-conformance reporting requirements shall be specified in the Statement of Work (SOW) Data Requirements List, and Data Requirements Documents (DRDs) shall be used to identify the submittal and data requirements. (LS-71000, Section 7.3.2.1)

2.For flight hardware developed at JSC, non-conformance reporting shall be in accordance with JPG 5335.3 and the applicable technical division plan. (LS-71000, Section 7.3.2.2)

3.Non-conformances, which meet the Level 1 Problem Reporting and Corrective Action criteria for payloads as defined in SSP 30223, shall be reported in accordance with SSP 30223. (LS-71000, Section 7.3.2.3)

4.Software non-conformance reporting shall be in accordance with LS-71020-1, Software Development Plan for the Human Research Facility. (LS-71000, Section 7.3.2.4)

3.2.3.1Failure Propagation

The design shall preclude propagation of failures from the payload to the environment outside the payload. (NSTS 1700.7B, Section 206)

3.2.3.2Useful Life

VOILA hardware shall be designed for a 10 year utilization. (LS71000, Section 7.2.1)

3.2.3.2.1Operational Life (Cycles)

Operational life applies to any hardware that deteriorates with the accumulation of operating time and/or cycles and thus requires periodic replacement or refurbishment to maintain acceptable operating characteristics. Operational life includes the usage during flight, ground testing and pre-launch operations. All components of VOILA shall have an operational life limit of 10 years, except those identified as having limited life, see Section 3.2.3.2.3.

3.2.3.2.2Shelf Life

Shelf life is defined as that period of time during which the components of a system can be stored under controlled conditions and put into service without replacement of parts (beyond servicing and installation of consumables). Shelf life items shall be identified and tracked on a list that is maintained as a part of the hardware acceptance data pack.

3.2.3.2.3Limited Life

Limited life is defined as the life of a component, subassembly, or assembly that expires prior to the stated useful life in Section 3.2.3.2.1. Limited life items or materials, such as soft goods, shall be identified and the number of operation cycles shall be determined. Limited life items shall be tracked on a limited life list that is maintained as a part of the hardware acceptance data pack.

3.2.4Maintainability

A.Not applicable to VOILA.

B.Not applicable to VOILA.

C.Not applicable to VOILA.

D.Electrical connectors and cable installations shall permit disconnection and reconnection without damage to wiring connectors. (LS-71000, Section 6.4.4.3.2C)

E.Not applicable to VOILA.

F.Not applicable to VOILA.

G.The capture elements, including grids, screens, or filter surfaces shall be accessible for replacement or cleaning without dispersion of the trapped materials. (LS-71000, Section 6.4.3.1.2B)

3.2.4.1Logistics and Maintenance

3.2.4.1.1Payload In-Flight Maintenance


3.2.4.1.2Maintenance3.2.5Environmental Conditions3.2.5.1On-Orbit Environmental Conditions

3.2.5.1.1On-Orbit Internal Environments

3.2.5.1.1.1Pressure

VOILA shall be safe when exposed to pressures of 0 to 104.8 kPa (0 to 15.2 psia). (LS-71000, Section 6.2.9.1.1)

3.2.5.1.1.2Temperature

VOILA shall be safe when exposed to the temperatures of 10 to 46 oC (50 to 115 oF). (LS-71000, Section 6.2.9.1.2)

3.2.5.1.1.3Humidity


3.2.5.1.2Use of Cabin Atmosphere

3.2.5.1.2.1Active Air Exchange


3.2.5.1.2.2Oxygen Consumption


3.2.5.1.2.3Chemical Releases

Chemical releases to the cabin air shall be in accordance with Paragraphs 209.1a and 209.1b in NSTS 1700.7, ISS Addendum. (LS-71000, Section 6.2.9.2.3)

3.2.5.1.2.4Cabin Air Heat Leak

Cabin air heat rejection is defined by the ISS program at the module level only. Instrument cabin air heat leak must be coordinated with HRF SE&I. (LS-71000, Section 6.2.5.4)

3.2.5.1.3Ionizing Radiation Requirements

3.2.5.1.3.1Instrument Contained or Generated Ionizing Radiation

Equipment containing or using radioactive materials or that generate ionizing radiation shall comply with NSTS 1700.7, ISS Addendum, Paragraph 212.1. (LS71000, Section 6.2.9.3.1)

3.2.5.1.3.2Ionizing Radiation Dose

Instruments should expect a total dose (including trapped protons and electrons) of 30 Rads (Si) per year of ionizing radiation. A review of the dose estimates in the ISS (SAIC-TN-9550) may show ionizing radiation exposure to be different than 30 Rads (Si) per year, if the intended location of the rack in the ISS is known. (LS71000, Section 6.2.9.3.2)

NOTE: This is a testing guideline and is not a verifiable requirement.

3.2.5.1.3.3Single Event Effect (SEE) Ionizing Radiation

VOILA shall be designed not to produce an unsafe condition or one that could cause damage to equipment external to VOILA as a result of exposure to SEE ionizing radiation assuming exposure levels specified in SSP 30512, Paragraph 3.2.1, with a shielding thickness of 25.4 mm (1000 mils). (LS-71000, Section 6.2.9.3.3)

3.2.5.1.4Additional Environmental Conditions

The environmental information provided in Table 3.2.5.1.4-1, Environmental Conditions on ISS, and Figure 3.2.5.1.4-1, Operating Limits of the ISS Atmospheric Total Pressure, Nitrogen and Oxygen Partial Pressures, is for design and analysis purposes. (LS-71000, Section 6.2.9.4)

TABLE 3.2.5.1.4-1. ENVIRONMENTAL CONDITIONS ON ISS

Environmental Conditions

Value

Atmospheric Conditions on ISS

Pressure Extremes

0 to 104.8 kPa (0 to 15.2 psia)

Normal operating pressure

See Figure 3.2.5.1.4-1

Oxygen partial pressure


Nitrogen partial pressure


Dewpoint

4.4 to 15.6 (C (40 to 60 (F) ref. Figure 3.2.5.1.1.3-1

Percent relative humidity

25 to 75 % ref. Figure 3.2.5.1.1.3-1

Carbon dioxide partial pressure during normal operations with 6 crewmembers plus animals

24-hr average exposure 5.3 mm HgPeak exposure 7.6 mm Hg

Carbon dioxide partial pressure during crew changeout with 11 crewmembers plus animals

24-hr average exposure 7.6 mm HgPeak exposure 10 mm Hg

Cabin air temperature in USL, JEM, APM and CAM

17 to 28 (C (63 to 82 (F)

Cabin air temperature in Node 1

17 to 31 (C (63 to 87 (F)

Air velocity (nominal)

0.051 to 0.203 m/s (10 to 40 ft/min)

Airborne microbes

Less than 1000 CFU/m3

Atmosphere particulate level

Average less than 100,000 particles/ft3 for particles less than 0.5 microns in size

MPLM Air Temperatures

Passive Flights

Active Flights

Pre-Launch

15 to 24 (C (59 to 75.2 (F)

14 to 30 (C (57.2 to 86 (F)

Launch/Ascent

14 to 24 (C (57.2 to 75.2 (F)

20 to 30 (C (68 to 86 (F)

On-Orbit (Cargo Bay + Deployment)

24 to 44 (C (75.2 to 111.2 (F)

16 to 46 (C (60.8 to 114.8 (F)

On-Orbit (On-Station)

23 to 45 (C (73.4 to 113 (F)

16 to 43 (C (60.8 to 109.4 (F)

On-Orbit (Retrieval + Cargo Bay)

17 to 44 (C (62.6 to 111.2 (F)

11 to 45 (C (51.8 to 113 (F)

Descent/Landing

13 to 43 (C (55.4 to 109.4 (F)

10 to 42 (C (50 to 107.6 (F)

Post-Landing

13 to 43 (C (55.4 to 109.4 (F)

10 to 42 (C (50 to 107.6 (F)

Ferry Flight

15.5 to 30 (C (59.9 to 86 (F)

15.5 to 30 (C (59.9 to 86 (F)

MPLM Maximum Dewpoint Temperatures

Pre-Launch

13.8 (C (56.8 (F)

12.5 (C (54.5 (F)

Launch/Ascent

13.8 (C (56.8 (F)

12.5 (C (54.5 (F)

On-Orbit (Cargo Bay +Deployment)

13.8 (C (56.8 (F)

12.5 (C (54.5 (F)

On-Orbit (On Station)

15.5 (C (60 (F)

15.5 (C (60 (F)

On-Orbit (Retrieval +Cargo Bay)

10 (C (50 (F)

10 (C (50 (F)

Descent/Landing

10 (C (50 (F)

10 (C (50 (F)

Post Landing

10 (C (50 (F)

10 (C (50 (F)

Ferry Flight

15.5 (C (60 (F)

15.5 (C (60 (F)

Thermal Conditions

USL module wall temperature

13 (C to 43 (C (55 (F to 109 (F)

JEM module wall temperature

13 (C to 45 (C (55 (F to 113 (F) (TBR)

APM module wall temperature

13 (C to 43 (C (55 (F to 109 (F) (TBR)

CAM module wall temperature

13 (C to 43 (C (55 (F to 109 (F) (TBR)

Other integrated payload racks

Front surface less than 37 (C (98.6 (F)

*Microgravity

Quasi-Steady State Environment

See SSP 57000 Figures 3.9.4 and Table 3.9.4

Vibro-accoustic Environment

See SSP 57000 Figure 3.9.4

General Illumination

108 Lux (10 fc) measured 30 inches from the floor in the center of the aisle

Figure 3.2.5.1.4-1. Operating Limits of the ISS Atmospheric Total Pressure, Nitrogen and Oxygen Partial Pressures

3.2.5.1.5Pressure Rate of Change

A.VOILA shall maintain positive margins of safety for the on-orbit depress/repress rates in Table 3.2.5.1.5-1. (LS-71000, Section 6.2.1.1.6B)

Table 3.2.5.1.5-1. ISS Pressure Rate of Change

Depressurization

878 Pa/sec (7.64 psi/minute)

Repressurization


B.VOILA shall maintain positive margins of safety for maximum depressurization and repressurization rates for the carrier(s) in which it will be transported. (LS71000, Section 6.2.1.1.6B)

1.VOILA shall maintain positive margins of safety for maximum depressurization and repressurization rates for the MPLM documented in Table 3.2.5.1.5-2. (Derived from LS-71000, Section 6.2.1.1.6A)

Table 3.2.5.1.5-2. MPLM Pressure Rate of Change

Depressurization


Repressurization


2.VOILA shall maintain positive margins of safety for maximum depressurization and repressurization rates for the Orbiter Middeck documented in Table 3.2.5.1.5-3. (LS-71000, Section 6.3.1.2A)

Table 3.2.5.1.5-3. Orbiter Middeck Pressure Rate of Change

Depressurization/Repressurization


C. VOILA shall maintain positive margins of safety when exposed to the PFE discharge rate given in Figure 3.2.5.1.5-1. (LS-71000, Section 6.2.1.1.6C)

D.Not applicable to VOILA.

MASS DISCHARGED IN 10 SECONDS = 3.424 LBM

MASS DISCHARGED IN 45 SECONDS = 5.646 LBM

MASS (LBS)

ELAPSED TIME (SECONDS)

7

6

5

4

3

2

1

0

-10

0

10

20

30

40

50

60

70

Figure 3.2.5.1.5-1. Manual Fire Suppression System Performance Characteristics

3.2.5.1.6Microgravity

Microgravity requirements have not been determined by the ISS Program.

A.Quasi-Steady Requirements

TBD (LS-71000, Section 6.2.1.1.7A)

B.Vibratory Requirements

TBD (LS-71000, Section 6.2.1.1.7B)

C.Transient Requirements

TBD (LS-71000, Section 6.2.1.1.7C)

3.2.5.2Acoustic Emission Limits

3.2.5.2.1Continuous Noise Limits

A.Integrated Racks Whose Sub-Rack Equipment Will Not Be Changed Out


B.Integrated Racks Whose Sub-Rack Equipment Will Be Changed Out

The Continuous Noise Source (see Glossary of Terms) for an integrated rack (including any supporting adjunct active portable equipment operated outside the integrated rack that is within or interfacing with the crew habitable volume) whose sub-rack equipment will be changed out on-orbit shall not, except in those cases when the rack meets the Intermittent Noise Source requirements specified in Section 3.2.5.2.2, exceed the limits specified in Table 3.2.5.2.1-1 for all octave bands (NC-40 equivalent) when the equipment is operating in the loudest expected configuration and mode of operation that can occur on orbit under nominal crew, or hardware operation circumstances, during integrated rack setup operations, or during nominal operations where doors/panels are opened or removed. (LS-71000, Section 6.4.3.3.1B)

NOTE:These acoustic requirements do not apply during failure or maintenance operations. (LS-71000, Section 6.4.3.3.1)

C.Independently Operated Equipment


Table 3.2.5.2.1-1. Continuous Noise Limits

Rack Noise Limits Measured at 0.6 Meters Distance From the Test Article

Frequency Band (Hz)

Integrated Rack Sound Pressure Level(SPL)

63

64

125

56

250

50

500

45

1000

41

2000

39

4000

38

8000

37

3.2.5.2.2Intermittent Noise Limits

A.The Integrated rack (including any supporting adjunct active portable equipment operated outside the integrated rack that is within or interfacing with the crew habitable volume) Intermittent Noise Source (See Glossary of Terms) shall not exceed the Total Rack A-weighted Sound Pressure Level (SPL) Limits during the Maximum Rack Noise Duration as specified in Table 3.2.5.2.2-1 when the equipment is operating in the loudest expected configuration and mode of operation that can occur on orbit under any planned operations. (LS-71000, Section 6.4.3.3.2A)

NOTE:These acoustic requirements do not apply during failure or maintenance operations. (LS-71000, Section 6.4.3.3.2)

B.The Rack Noise Duration is the total time that the rack produces intermittent noise above the NC-40 limit during a 24 hour time period. This duration is the governing factor in determining the allowable Intermittent Noise Limits. Regardless of the number of separate sources and varying durations within a rack, this cumulative duration shall be used to determine the A-weighted SPL limit in column B. (LS-71000, Section 6.4.3.3.2B)

TABLE 3.2.5.2.2-1. INTERMITTENT NOISE LIMITS

Rack Noise Limits Measured At 0.6 Meters Distance From The Test Article

Maximum Rack Noise Duration

Total Rack A - Weighted SPL (dBA)

8 Hours

49

7 Hours

50

6 Hours

51

5 Hours

52

4 Hours

54

3 Hours

57

2 Hours

60

1 Hour

65

30 Minutes

69

15 Minutes

72

5 Minutes

76

2 Minutes

78

1 Minute

79

Not Allowed

80

3.2.5.3Lighting Design

The general illumination of the space station in the aisle will be a minimum of 108 lux (10 foot candles) of white light. This illumination will be sufficient for ordinary payload operations performed in the aisle (e.g., examining dials or panels, reading procedures, transcription, tabulation, etc.).

Payloads will meet the following requirements:

A.Payload work surface specularity shall not exceed 20 percent. Paints listed in Table 3.2.5.3-1 meet this requirement. (LS-71000, Section 6.4.3.4A)

B.Not applicable to VOILA.

C.Not applicable to VOILA.

D.Not applicable to VOILA.

E. Not applicable to VOILA.

TABLE 3.2.5.3-1. SURFACE INTERIOR COLORS AND PAINTS

Hardware Description

Color

Finish

Paint Specification PerFED-STD-595

Equipment Rack Utility Panel Recess

White

Semigloss

27925

Equipment Rack Utility Panel Text Characters

Black

Lusterless

37038

ISPR Utility Panel Recess

White

Semigloss

27925

ISPR Utility Panel Recess Text Characters

Black

Lusterless

37038

Functional Unit Utility Panel Recess (as applicable)

White

Semigloss

27925

Functional Unit Utility Panel Recess Text Characters

Black

Lusterless

37038

Rack Front Aisle Extensions

Off-White

Semigloss

27722

Overhead Rack Face Plates

Off-White

Semigloss

27722

Port Rack Face Plates

Off-White

Semigloss

27722

Starboard Rack Face Plates

Off-White

Semigloss

27722

Deck Rack Face Plates

Off-White

Semigloss

27722

Overhead Rack Utility Panel Closeouts

Off-White

Semigloss

27722

Port Rack Utility Panel Closeouts

Off-White

Semigloss

27722

Starboard Rack Utility Panel Closeouts

Off-White

Semigloss

27722

Deck Rack Utility Panel Closeouts

Off-White

Semigloss

27722

Stowage Trays

Off-White

Semigloss

27722

Stowage Tray Handle Straps (any location)

Blue material

Semigloss

25102 or equiv.

Common Seat Track Interface

Clear (Anodized)

Semigloss

none

Glovebox (Aluminum or Plastic)

Medium Gray

Gloss

16329 or 16373

Glovebox (Aluminum)

White

Gloss

17925

Glovebox (Aluminum or Plastic)

Off-White

Gloss

17722

Glovebox (Aluminum)

Tan

Gloss

10475

EXPRESS Program Rack Utility Panels

Off-White

Gloss

17875

3.2.5.4Front Panel Surface Temperature

VOILA shall be designed such that the average front surface temperature is less than 37 C (98.6 F) with a maximum temperature limit not to exceed 49 C (120 F). (LS-71000, Section 6.2.5.3)

3.2.6Transportability

3.2.6.1Launch and Landing

VOILA shall be transportable to and from orbit via the Shuttle middeck and the EXPRESS Transportation Rack.

3.2.7Operational Interface Requirements3.2.7.1Mechanical Interface Requirements

3.2.7.1.1Connector Physical Mate


3.2.7.1.2HRF Rack to SIR Drawer Structural Interface Requirements

HRF rack SIR drawer accommodations are shown in Figure 3.2.7.1.2-1. (LS71000, Section 6.2.1.2)

4 PU

4 PU

4 PU

4 PU

4 PU

4 PU

4 PU

32 PU

Connector bar for 4

-

PU location

Slideguides for 4

-

PU location

NOTE:SIR drawer accommodations viewed from front of the HRF rack.

Figure 3.2.7.1.2-1. HRF Rack SIR Drawer Accommodations

3.2.7.1.2.1Dimensional Tolerances

HRF rack mounted SIR drawer dimensional tolerances shall be in accordance with Table 3.2.7.1.2.1-1. (LS-71000, Section 6.2.1.2.1)

TABLE 3.2.7.1.2.1-1. DIMENSIONAL TOLERANCES

English Dimension

Tolerance

X.XX

0.030

X.XXX

0.010

X

1

3.2.7.1.2.2SIR Drawer Structural/ Mechanical Interfaces

HRF rack mounted SIR drawers shall meet the structural mechanical interfaces as defined in LS-60077, Standard Interface Rack Specification. (LS-71000, Section 6.2.1.2.2)

3.2.7.1.2.3Reserved

3.2.7.1.2.4HRF Rack Seat Track Interfaces

VOILA hardware interfacing with the ISS seat track shall meet ISS seat track dimensional requirements.

3.2.7.2Electrical Power Interface Requirements

Electrical requirements in this section are defined for instrument interfaces to the HRF rack 28 volt power outputs at HRF rack connector bars and rack connector panel. For the purposes of this section, compatibility means to remain safe and to provide operational functions within the range of accuracy specified for the instrument. (LS-71000, Section 6.2.2)

3.2.7.2.1HRF Rack Power Output Connectors

3.2.7.2.1.1SIR Drawer Power Connectors

SIR drawer instruments that receive electrical power from HRF rack connector bar interfaces shall connect to and be compatible with blind mate connector part number M83733/2RA018 with pin assignments as shown Figure 3.2.7.2.1.1-1 and Table 3.2.7.2.1.1-1. (LS-71000, Section 6.2.2.1.1)

Figure 3.2.7.2.1.1-1. SIR Drawer Power Connector Part Number M83733/2RA018

TABLE 3.2.7.2.1.1-1. SIR DRAWER POWER CONNECTOR PIN ASSIGNMENTS

Pin

Type

Function

Note

1

Core

+28 Vdc Supply

0 to 20 Amperes

2

Core

+28 Vdc Return

3

Not used

4

Not used

5

Not used

6

Not used

7

Not used

8

Not used

9

Not used

10

Not used

11

Not used

12

Core

Chas