Space and Life Sciences Criticality 3

Space And Life Sciences Criticality 3
Experiment Unique Equipment

System Requirements Document

E085/507

Visuomotor and Orientation Investigations in

Long-duration Astronauts (VOILA)

LS-71143

Preface

This experiment specific SRD has been derived from the JSC provided template LS-71143 dated 28 February 2000.

LS-71143 - 1/28/00

CONTENTS

SectionPage

1.0SCOPE1-

1.1GUIDELINES FOR COMPLETION OF THE SYSTEM REQUIREMENTS DOCUMENT TEMPLATE 1-

2.0APPLICABLE DOCUMENTS2-

2.1DOCUMENTS2-

2.2ORDER OF PRECEDENCE2-

3.0SYSTEM REQUIREMENTS3-

3.1ITEM DEFINITION3-

3.1.1Experiment Description3-

3.1.1.1Experiment Overview3-

3.1.1.2Operational Overview3-

3.2CHARACTERISTICS3-

3.2.1Performance Characteristics3-

3.2.1.1Functional Performance Characteristics3-

3.2.1.2Equipment Performance Characteristics3-

3.2.2Physical Characteristics3-

3.2.2.1Mass Properties3-

3.2.2.2Envelope3-

3.2.2.2.1Stowed Envelope3-

3.2.2.2.2Deployed Envelope3-

3.2.2.2.2.1Hardware Protrusion Limits3-

3.2.2.2.2.1.1Permanent Protrusions3-

3.2.2.2.2.1.2Intermittent Protrusions3-

3.2.2.2.2.1.3Temporary Protrusions3-

3.2.2.2.2.1.4Clearance for Crew Restraints and Mobility Aids3-

3.2.2.2.2.2Deployed Envelope Dimensions3-

3.2.3Reliability3-

3.2.3.1Failure Propagation3-

3.2.4Maintainability3-

3.2.4.1Logistics and Maintenance3-

3.2.4.1.1Payload In-Flight Maintenance3-

3.2.4.1.2Maintenance Functions3-

3.2.5Environmental Conditions3-

3.2.5.1On-Orbit Environmental Conditions3-

3.2.5.1.1On-Orbit Internal Environments3-

3.2.5.1.1.1Pressure3-

3.2.5.1.1.2Temperature3-

3.2.5.1.1.3Humidity3-

CONTENTS (Cont'd)

SectionPage

3.2.5.1.2Use of Cabin Atmosphere3-

3.2.5.1.2.1Active Air Exchange3-

3.2.5.1.2.2Oxygen Consumption3-

3.2.5.1.2.3Chemical Releases3-

3.2.5.1.2.4Cabin Air Heat Leak3-

3.2.5.1.2.5Cabin Air Cooling3-

3.2.5.1.3Ionizing Radiation Requirements3-

3.2.5.1.3.1Instrument Contained or Generated Ionizing Radiation3-

3.2.5.1.3.2Ionizing Radiation Dose3-

3.2.5.1.3.3Single Event Effect (SEE) Ionizing Radiation3-

3.2.5.1.4Additional Environmental Conditions3-

3.2.5.1.5Pressure Rate of Change3-

3.2.5.2Acoustic Emission Limits3-

3.2.5.2.1Continuous Noise Limits3-

3.2.5.2.2Intermittent Noise Limits3-

3.2.5.3Instrument Surface Temperature3-

3.2.6Transportability3-

3.2.6.1Launch and Landing3-

3.2.7Operational Interface Requirements3-

3.2.7.1Mechanical Interface Requirements3-

3.2.7.1.1Connector Physical Mate3-

3.2.7.2Electrical Interface Requirements3-

3.2.7.2.1Electromagnetic Radiation3-

3.2.7.2.1.1Electromagnetic Compatibility (EMC)3-

3.2.7.2.1.1.1Electrical Grounding3-

3.2.7.2.1.1.2Electrical Bonding3-

3.2.7.2.1.2Electromagnetic Interference3-

3.2.7.2.2Electrostatic Discharge3-

3.2.7.2.3Corona3-

3.2.7.2.4Cable/Wire Design and Control Requirements3-

3.2.7.2.4.1Wire Derating3-

3.2.7.2.4.2Exclusive Power Feeds3-

3.2.7.2.5Loss of Power3-

3.2.7.2.6Alternating Current Magnetic Fields3-

3.2.7.2.7Direct Current Magnetic Fields3-

3.2.7.3Command and Data Handling Interface Requirements3-

3.2.7.3.1Word/Byte Notations, Types and Data Transmissions3-

3.2.7.3.1.1Word/Byte Notations3-

3.2.7.3.1.2Data Types3-

3.2.7.3.2HRF Software Requirements3-

CONTENTS (Cont'd)

SectionPage

3.2.7.3.3ISS Command and Data Handling Services Through HRF Common Software Interface 3-

3.2.7.4Fire Protection Interface Requirements3-

3.2.7.4.1Fire Prevention3-

3.2.7.4.2Fire Suppression3-

3.2.7.4.2.1Portable Fire Extinguisher3-

3.2.7.4.2.2Fire Suppression Access Port Accessibility3-

3.2.7.4.2.3Fire Suppressant Distribution3-

3.2.7.4.3Labeling3-

3.2.7.5Other Interface Requirements3-

3.3DESIGN AND CONSTRUCTION3-

3.3.1Materials, Processes, and Parts3-

3.3.1.1Materials and Processes3-

3.3.1.2Sharp Edges3-

3.3.1.2.1Edge and Corner Requirements3-

3.3.1.3Electrical, Electronic, and Electromechanical Parts Selection3-

3.3.1.3.1Burn In Screening Tests3-

3.3.2Nameplates and Product Marking3-

3.3.2.1Equipment Identification3-

3.3.3Workmanship3-

3.3.4Interchangeability3-

3.3.5Safety Requirements3-

3.3.5.1Electrical Safety3-

3.3.5.1.1Mating/Demating of Powered Connectors3-

3.3.5.1.2Power Switches/Controls3-

3.3.5.1.3Ground Fault Circuit Interrupters/Portable Equipment DC Sourcing Voltage 3-

3.3.5.1.4Portable Equipment/Power Cords3-

3.3.6Human Engineering3-

3.3.6.1Closures or Covers Design Requirements3-

3.3.6.2Interior Color3-

3.3.6.2.1Rack Mounted Equipment3-

3.3.6.2.2Stowed/Deployable Equipment3-

3.3.6.2.3Colors for Soft Goods3-

3.3.7Anthropometry3-

3.3.7.1Full Size Range Accommodation3-

3.3.8System Security3-

3.3.9Design Requirements3-

3.3.9.1Structural Design Requirements3-

3.3.9.1.1Crew Induced Load Requirements3-

CONTENTS (Cont'd)

SectionPage

3.3.9.1.2Safety Critical Structures Requirements3-

3.3.9.2Electrical Power Consuming Equipment Design3-

3.3.9.2.1Batteries3-

4.0VERIFICATION PROVISIONS4-

4.1GENERAL4-

4.1.1Responsibility for Verifications4-

4.2ACCEPTANCE AND QUALIFICATION TEST REQUIREMENTS4-

4.2.1Description of Tests4-

4.2.1.1Thermal Cycle Tests4-

4.2.1.1.1Qualification Thermal Cycling4-

4.2.1.1.2Acceptance Thermal Cycling4-

4.2.1.2Vibration Tests4-

4.2.1.2.1Qualification for Acceptance Random Vibration Test4-

4.2.1.2.2Acceptance Random Vibration Test4-

4.2.1.3Electromagnetic Compatibility Testing4-

4.2.1.4Functional Testing4-

4.2.1.5Burn-In4-

4.2.1.6Flammability4-

4.2.1.7Offgassing (Toxicity)4-

4.2.1.8Bench Handling Test4-

4.2.1.9Other Tests4-

4.2.1.10Pre-Delivery Acceptance Test4-

4.2.1.11Science Verification Testing4-

4.3DOCUMENTATION OF VERIFICATION AND CERTIFICATION TESTING 4-

5.0PREPARATION FOR SHIPMENT5-

5.1GENERAL5-

5.2PACKING, HANDLING, AND TRANSPORTATION5-

5.3PRESERVATION AND PACKING5-

5.4MARKING FOR SHIPMENT5-

5.5NASA CRITICAL SPACE ITEM LABEL5-

6.0NOTES6-

6.1DEFINITIONS6-

APPENDIX ACRITICALITY 3 EQUIPMENT PROGRAM REQUIREMENTSA-1

APPENDIX BVERIFICATION AND CERTIFICATION COMPLIANCE MATRIXB-1

APPENDIX CFUNCTIONAL REQUIREMENTS, HUMAN FACTORS, AND JHB 8080.5 C-1

LIST OF TABLES

TablePage

3.1-1[EXPERIMENT DESIGNATION] EXPERIMENT UNIQUE EQUIPMENT 3-1

3.1-2[EXPERIMENT DESIGNATION] EXPERIMENT UNIQUE EQUIPMENT SOFTWARE 3-1

3.2.2.1-1STOWAGE UNIT WEIGHT ALLOWANCE3-3

3.2.2.2.1-1STOWAGE UNIT VOLUME ALLOWANCE3-4

3.2.5.1.2.5-1AIR HEAT LOAD3-8

3.2.5.1.4-1ENVIRONMENTAL CONDITIONS ON ISS3-9

3.2.5.1.5-1ISS PRESSURE RATE OF CHANGE3-10

3.2.5.1.5-2MPLM PRESSURE RATE OF CHANGE3-11

3.2.5.2-1CONTINUOUS NOISE LIMITS3-12

3.3.2.2-1RS03PL3-15

3.3.1.2.1-1LOOSE EQUIPMENT EDGE AND CORNER RADIUSING REQUIREMENTS 3-23

3.3.5.1.3-1LET-GO CURRENT PROFILE THRESHOLD VERSUS FREQUENCY 3-27

3.2.5.2.2-1INTERMITTENT NOISE LIMITS3-13

3.3.9.1.1-1CREW-INDUCED LOADS3-30

4.2-1NON-CRITICAL HARDWARE QUALIFICATION TEST REQUIREMENTS 4-3

4.2-2NON-CRITICAL HARDWARE ACCEPTANCE TEST REQUIREMENTS 4-4

4.2.1.2.1-1QUALIFICATION ACCEPTANCE RANDOM VIBRATION TEST LEVELS 4-8

4.2.1.2.2-1ACCEPTANCE RANDOM VIBRATION WORKMANSHIP TEST LEVELS 4-9

LIST OF FIGURES

FigurePage

3.2.5.1.4-1Operating Limits of the ISS Atmospheric Total Pressure, Nitrogen, and Oxygen Partial Pressures 3-10

3.2.5.1.5-1Manual Fire Suppression System Performance Characteristics3-11

3.2.7.4.2.2-1Manual Fire Suppression Hardware Envelope3-20

3.2.7.4.2.2-2Closed Volume PFE Nozzle3-21

4.2.1.1.1-1Qualification Thermal Cycling4-6

4.2.1.1.2-1Acceptance Thermal Cycling4-7

ACRONYMS AND ABBREVIATIONS

{Add and delete entries as necessary}

ACRONYMS AND ABBREVIATIONS (Cont'd)

ACRONYMS AND ABBREVIATIONS (Cont'd)

LS-71143 - 3/3/001

1.0SCOPE

This specification defines the Human Research Facility (HRF) program requirements for Visuomotor and Orientation Investigations in Long-duration Astronauts (VOILA)—E085/507. The VOILA consists of Criticality 3 Experiment Unique Equipment (EUE) hardware and software that will be used to support the HRF. The term “Experiment Unique Equipment,” as used in this document, is defined as hardware designed to support an HRF Program experiment and not intended for general use.

The primary governing document for the requirements levied in this document is LS-71000, Program Requirements Document for the Human Research Facility. Other requirements are derived from SSP 57200, Human Research Facility - Rack One Hardware Interface Control Document, and interface requirement documents for the various items of HRF equipment.

The requirements in Sections 3, 4, and 5 of this document consist of a minimum set of constraints for Criticality 3 EUE hardware and software. Criticality 3 items are defined in SSP 30234. Provisions for verification and subsequent use of Criticality 3 equipment as part of the HRF program are delineated in Section 5 of LS-71000.

The VOILA Experiment Unique Equipment shall be reviewed through the International Space Station (ISS) Payload Safety Review Panel (PSRP) for Safety Certification and JSC/NT3 Reliability for designation as Criticality 3 hardware.

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. Any change in functionality that requires equipment designated as Criticality 3 to be used in a manner that is not consistent with the requirements specified herein and in LS-71000 will require that item or items to be reassessed for criticality as well as applicability 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, as of the date the contract is issued.

All specifications, standards, exhibits, drawings or other documents referenced in this specification are hereby incorporated as cited in the text of this document.

2.1Documents

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.

LS-71143 - 1/28/0012-1

3.0SYSTEM REQUIREMENTS

3.1Item Definition

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

Table 3.1-1 lists the equipment items covered by this document.

TABLE 3.1-1. VoiLA EXPERIMENT UNIQUE EQUIPMENT

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

Table 3.1-2. VOILA Experiment Unique Equipment Software

3.1.1Experiment Description

3.1.1.1Experiment Overview

This ISS HRF investigation extends, simplifies, and merges two sensory motor and performance experiments originally developed for the 1998 STS90 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. Tests 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. Three pre-flight, three in flight, and three post-flight performances of each test 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 Tests); (2) the onset of x-axis illusory linear self-motion without haptic cues (Linear Vection Test); (3) the effect of perceived orientation on visual object recognition and shape recognition (Object Recognition Tests); (4) whether information used in grasping remembered objects is stored in head fixed, body fixed, or exocentric reference frames (Virtual Grasping Test); and (5) how the timing of catching movements depends on anticipation of downward acceleration (Virtual Catching Test).

3.1.1.2 Operational Overview

In each session, based on the amount of crewtime available, the Workstation Session Manager program suggests one or more of 5 different visual perception tests and one or more of 4 different visuomotor tasks. Inflight tests are performed in up to 3 possible conditions: quasi-free floating, lightly restrained and/or with constatnt-force springs (simulated gravity). Pre-and post-flight tests will be conducted in one of three conditions: erect, supine, or with a tilted seat.

Visual Perception

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

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

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

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

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

Visuomotor Coordination

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

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

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

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

Three inflight performances of each test. The first should be during Week 2 (FD8 to FD14), the second during Week 5 (FD29 to FD35), and the third during Week 11 (FD71 to FD77). Depending on crew schedules, it would be highly desirable to schedule one additional performance during Week 1 (FD1 to FD7) and another about 3-4 weeks before the end of the increment (R-21 to R-28). If possible, additional performances every six weeks after Week 11 until as late as possible would also be desirable.

3.2Characteristics

3.2.1Performance Characteristics

3.2.1.1Functional Performance Characteristics

A.Note: Functional requirements for the VOILA EUE are described in Visuomotor and Orientation Investigations in Long-duration Astronauts—E085/507 Experiment Document (ED), LS-20427. Functional requirements for HRF subrack payloads, stowed equipment, and deployed equipment that may be used in conjunction with this EUE are described in the individual equipment hardware requirements documents.

B.Equipment provided under this document should, as a minimum, be verified to be functionally acceptable for its intended operational lifetime.

C.Upon arrival at Johnson Space Center (JSC), the VOILA shall undergo full experiment protocol test and checkout.

D.This testing shall be documented on a Task Performance Sheet (TPS) (JSC Form 1225) per JSC Work Instruction NT1-CWI-001.

E.This testing shall be of sufficient level to demonstrate end-to-end functionality of the VOILA EUE.

3.2.1.2Equipment Performance Characteristics

{Specific equipment performance characteristics necessary for the successful completion of the intended experiment should be detailed in this section. As an example, if an item of measuring equipment associated with the experiment were required to measure parameters over a certain range (i.e., 400 millivolts, or 0.2 - 100 ml/min, etc.) and have a certain accuracy (i.e., 0.5% Full Scale, or 2% of reading, etc.), these items would be regarded as equipment performance characteristics.}

3.2.2Physical Characteristics

3.2.2.1Mass Properties

{Weight requirements for the VOILA are as negotiated with the developer and are documented in the ED.}

3.2.2.2Envelope

{Stowed and deployed envelope requirements for the hardware are as negotiated with the developer and are documented in the ED.}

3.2.2.2.1Stowed Envelope

{If stowed envelope dimensions are critical features of the hardware or if there is a dimensional value which must be met within a given tolerance or which cannot be exceeded (e.g., for stowage), that dimensional requirement should be specified in this section. Otherwise, the requirement for hardware to be measured and its dimensions documented on a TPS (JSC Form 1225) should be stated in this section. The tolerance of the measuring system should also be recorded on this form. As an alternative, the hardware provider may provide the item dimensions and the measuring system tolerance as part of the data package. Estimated stowed envelope dimensions should be provided as early in the design process as possible. Note: This data is to be provided for flight integration purposes.}]

{Table 3.2.2.2.1-1 is provided as a guide.}

Table 3.2.2.2.1-1. Stowage Unit Volume Allowance

(1) The volume allowances and dimensions shown are only approximate. The payloads must meet the height, width, and depth limitations of the Stowage unit as well as the interface requirements for the individual Stowage Unit.

3.2.2.2.2Deployed Envelope

3.2.2.2.2.1Hardware Protrusion Limits

3.2.2.2.2.1.1Permanent Protrusions

Integrated rack payload hardware shall only extend beyond the National Aeronautics and Space Administration (NASA) International Standard Payload Rack (ISPR) front face Ground Support Equipment (GSE) attachment points as defined in SSP 41017 and agreed to by ISS in the unique payload ICDs. Payload hardware extended or attached on-orbit may protrude beyond the face of the NASA ISPR front face GSE attachment points only on an intermittent or temporary basis. Payload work corridor will be 50 inches x 72 inches, (50 inches Y axis, 72 inches Z axis). (LS-71000, Section 6.4.4.1.1)

3.2.2.2.2.1.2Intermittent Protrusions

A.Intermittent protrusions are defined as equipment which remains setup in the aisle over a period of days, during which time crew attendance is repeatedly required. Intermittent protrusions shall be limited to 17 inches beyond the plane of the NASA ISPR front face GSE attachment points (except for payloads manifested in the floor or ceiling locations which are limited to 6 inches). (LS-71000, Section 6.4.4.1.2A)