EHP-10028 _Baseline_AdminChg1_Finalwcover.pdf

August 2024

NASA/TM−20240009010

EXTRAVEHICULAR ACTIVITY AND HUMAN SURFACE

MOBILITY PROGRAM (EHP)

EXPLORATION EVA (XEVA) SYSTEM COMPATIBILITY

STANDARDS

Christine N. Kovich

The Aerospace Corporation

Johnson Space Center (JSC) Houston

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DAA #20240009010

EHP-10028

BASELINE

National Aeronautics and Space Administration

EFFECTIVE DATE: MAY 9, 2024

EXTRAVEHICULAR ACTIVITY AND HUMAN

SURFACE MOBILITY PROGRAM (EHP)

EXPLORATION EVA (XEVA) SYSTEM

COMPATIBILITY STANDARDS

VERIFY THAT THIS IS THE CORRECT VERSION BEFORE USE

Verify that this is the correct version before use

Revision: Baseline Document No: EHP-10028

Release Date: 09 MAY 2024 Page: 2 of 280

Title: EHP xEVA System Compatibility Standards

This document has been approved for public release per DAA #20240009010.

REVISION AND HISTORY PAGE

Revision No.

Change No.

Description Release

Date Baseline EHP-C0570 Initial Release- Approval and release authorized by signed Directive EHP-D0570

05/09/24

Admin Chg

EHP-D0758 Straight-to-Directive (S2D) acknowledges publicly available marking DAA #20240009010, and authorizes release of the document.

8/9/24

Release Date: 09 MAY 2024 Page: 3 of 280

TABLE OF CONTENTS

SECTION PAGE

1.0 INTRODUCTION

1.1 Purpose

1.2 Scope

1.3 Applicability/Allocations

1.4 Conventions and Notations

Shall Statements (Standards/Requirements)

Requirement Identification

Rationale

Units

1.5 Change Authority/Responsibility

2.0 DOCUMENTS

2.1 Applicable Documents

2.2 Reference Documents

3.0 REQUIREMENTS

3.1 Clearances

Microgravity Translation Path Hardware Protrusion

Partial Gravity Translation Path Hardware Protrusion

Tool Interface Clearance

Bolt Clearance

Gloved-Hand Clearance

Handrail/Handhold Mounting Clearance

Handrail/Handhold Side Clearance

APFR EVA Installation/Removal Clearance

3.2 Translation

Contiguous EVA Translation Path

Translation Path

Incapacitated Crewmember Interfaces

EVA Contact Hazards Preclusion Beyond Translation Corridor

Partial Gravity EVA Contact Hazards Preclusion

3.3 EVA Handling

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Microgravity EVA Equipment Handling Features

Partial Gravity EVA Handling Capability <TBR-EHP-10028-003>

Partial Gravity Step Design Parameter

Airlock and Hatch Transfer Volumetric Constraints

Pressurized xEVA Suit Transfer through Airlock Hatch

EVA Lunar Hatch Dimensions

Handling Alignment Criteria

Manual Locking Features

Unique Labeling

Hand Tools

EVA Actuated Controls

EVA Handrails/Handholds

3.4 Worksite Outfitting

Worksite Mobility

Worksites

Dedicated EVA Worksite

Robotic Assisted EVA Worksites

Free-Float Worksites

Installation of Passive Worksite Interface (WIF) Sockets

Foot Restraint Ingress/Egress Aids

Visual Contrast at Worksite

3.5 Loads

Equipment Tether Attach Points

Microgravity EVA Crew-Induced Loads

Partial Gravity EVA Crew-Induced Loads

EVA Actuated Loads

EVA Mechanical Feedback

WIF Structural Loading

3.6 Connectors

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One-Handed EVA Operable Connectors

Connector Accessibility

Gloved-Hand Connector Accessibility

Incorrect Connector Mating Prevention

Connector Coding

Connector Protective Caps

Connector Rotational Travel

Connector Locking Feature

Visible Connector Alignment Markings

Connector Locking Ring

Connector Mating Status

Electrical Connectors

Fluid Connectors

3.7 EVA Operable Fasteners

Captive Fastener Design

Locking Features

EVA Hand-Actuated Fasteners Operation

EVA Push-in-Pull (PIP) Pins

Tool-Actuated Fasteners

3.8 Hardware Design

Battery Powered Devices

EVA Tools

Cable Routing/Restraint

Cable Routing Spacing

Paint

3.9 Safety

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Hazardous Material Control

Venting of Hazardous Materials

Electrical and Safety Design

Shock Protection

Operation During Pressure Change

Component Hazardous Energy Provision

Detachable Parts

Touch Temperatures xEVA Suit Glove Palm External Touch-Temperature Compliance for Small, Handheld Hardware

Incidental and Unlimited Contact Heat Transfer Rates

Sharp Edge and Protrusions Protection

Levers, Cranks, Hooks, and Controls

Exposed Holes or Slots

Pinch Hazard Protection

Equipment Clearance for Entrapment Hazard

Protection from Moving or Rotating Equipment

Emergency Ingress of Pressurized Habitable Environment

Emergency Ingress/Egress of Unpressurized Mobile Asset

External Surface Cleanliness Level

Tethering / Restraint

Crew Safety Tether Attachment

Crew Safety Restraint

Color for Crew Load-Rated Handhold/Handrails, Crew Safety Tethers and Safety Restraint Attachment Points

Manual Overrides

Entanglement, Cable Clamps, Ducts, or Retractors

3.10 Environments

Magnetic Field Limit

Voltage Potential Discharge

Lunar Surface Dust Tolerance

Lunar Surface Dust Mitigation

4.0 VERIFICATION

4.1 Responsibilities

4.2 Verification approach

4.3 Verification methods

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4.4 Verification Matrix

4.5 Artemis System Verifications

4.6 EHP Verifications

APPENDIX A ACRONYMS AND ABBREVIATIONS AND GLOSSARY OF TERMS .

Appendix A-1 Acronyms and Abbreviations

Appendix A-2 Glossary of Terms

APPENDIX B EVA BEST PRACTICES (BP)

APPENDIX C NON-EVA BPS FOR CONSIDERATIONS

APPENDIX D OPEN WORK

Appendix D-1 To Be Determined

Appendix D-2 To Be Resolved

Appendix D-3 Forward Work

APPENDIX E ARTEMIS SYSTEM ALLOCATIONS

TABLES

Table 1.3.1-1 Convention and Notations Descriptions

Table 2.1-1 Applicable Documents List

Table 2.2-1 Reference Documents List

Table 3.3.1-1 Constraints for EVA Transport of Objects

Table 3.3.2 -1 Constraint for Partial Gravity Large Mass Items – Lifting

Table 3.3.2-2 Constraint for Partial Gravity Large Mass Items – Carrying

Table 3.3.2 -3 Partial Gravity Volume Limit Surface Carry

Table 3.3.3-1 Partial Gravity Step Design Parameter

Table 3.3.8.5-1 Soft Dock Force

Table 3.3.12.6.1-1 Partial Gravity Work Envelope

Table 3.4.3-1 Worksite Forces

Table 3.5.1.1-1 EVA Handling and EVA Equipment Tether Point Colors <TBR-EHP- 10028-012>

Table 3.5.2-1 Microgravity EVA Crew-Induced Loads

Table 3.5.3-1 Partial Gravity EVA Crew-Induced Loads <TBR-EHP-10028-002>

Table 3.5.4-1 Miscellaneous Crew Induced Limit Loads

Table 3.7.3.4-1 EVA External Hexagonal Drive Interface

Table 3.7.5.4-1 Fastener Torque Data

Table 3.9.5-1 Depress and Repress Rates

Table 3.9.8-1 Touch Temperatures <TBR-EHP-10028-011>

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Table 3.9.9-1 30-Minute Touch Temperature Compliance for Small, Handheld Hardware

<TBR-EHP-10028-011>

Table 3.9.9-2 30-Minute Touch Temperature Heat Rate Compliance <TBR-EHP-10028- 011>

Table 3.9.10-1 Heat Transfer Rates <TBR-EHP-10028-011>

Table 3.9.11-1 Edge, Corner, and Protrusion Criteria – Edge and In-Plane Corner Radii

Table 3.9.11-2 Edge, Corner, and Protrusions Criteria – Protrusions and Outside Corners

Table 3.9.17-1 Emergency Ingress Capability

Table 3.9.19-1 External Surface Cleanliness Level

Table 3.9.23-1 Crew Load-Rated Colors <TBR-EHP-10028-012>

Table 3.10.1-1 Magnetic Field Limit

Table 4.4-1 Artemis Systems Verification Matrix

Table 4.5-1 Artemis System Verifications

Table 4.6-1 EHP Verifications

Table B-1 PIP Pin Acceptance Vibration Test (AVT) Levels

Table C-1 Standard Interface Temperature Differential

Table D1-1 To Be Determined

Table D2-1 To Be Resolved

Table D3-1 Forward Work

Table E-1: Artemis System Allocation Matrix

FIGURES

Figure 3.1.1-1 Translation Path Hardware Protrusion Envelope

Figure 3.1.1-2 Translation Path Minimum Diameter

Figure 3.1.2-1 Top View Partial Gravity Crew Envelope Diameter

Figure 3.1.2-2 Side View Partial Gravity Crew Envelope Height

Figure 3.1.3-1 Tool Interface Clearance

Figure 3.1.5-1 Gloved-Hand Clearance

Figure 3.1.6-1 EVA Handrail/Handhold Mounting Clearance Envelope

Figure 3.1.7-1 Handrail/Handhold Side Clearance

Figure 3.1.8-1 APFR Installation/Removal EVA Clearance Envelope – Top Mounted WIF

Figure 3.2.4-1 EVA Contact Hazard Preclusions Envelope

Figure 3.2.5-1 Side View Partial Gravity EVA Contact Hazards Height

Figure 3.3.12.1-1 Handrail/Handhold Profile Dimensions

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Figure 3.3.12.1-2 Partial Gravity Handrail/Handhold Profile Dimensions

Figure 3.3.12.4-1 Handrail/Handhold Gaps

Figure 3.3.12.6.1-1 Work Envelope – Microgravity

Figure 3.3.12.6.1-2 Partial Gravity Work Envelope

Figure 3.3.12.6.1-3 Partial Gravity Work Envelope – Reach Envelope

Figure 3.3.12.6.1-4 Two-Handed Reach Envelope Width

Figure 3.3.12.6.4-1 Crew Aids for Stability

Figure 3.4.2.2-1 Microgravity Working Volume for Manipulative EVA Tasks

Figure 3.4.2.2-2 Partial Gravity Working Volume

Figure 3.4.7-1 Ingress and Egress Aids for Foot Restraint

Figure 3.5.1.2-1 EVA Equipment Tether Point Dimensions

Figure 3.5.2-1 Opposing Forces on Handrail/Handhold

Figure 3.5.6-1 Top Mounted WIF Worksite Half Loading Criteria

Figure 3.7.3.3-1 Flight Knob Examples

Figure 3.7.5.2-1 11 mm Hexagonal EVA and Robotic Compatible Bolt

Figure 3.7.5.2-2 7/16-Inch Hexagonal Eva and Robotic Compatible Bolt

Figure 3.9.11-1 Exposed Corner and Edges

Figure B-1 EVABP-27 Connector Spacing

Figure B-2 EVABP-30 Minimum Don/Doff Volume Dimensions for a Single xEVA Suit

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Preface

Over the life of the Extravehicular Mobility Unit (EMU), series of products detailing “how to build Extravehicular Activity (EVA) System hardware”, “how to interface with EVA System hardware” and “how to design hardware EVA will access and utilize” were created to provide consolidated locations of the best practices and lessons learned of the EVA Community to projects unfamiliar with EVA. There were multiple documents describing these “how to” about EVA, from three different eras of human spaceflight. While these documents may be associated with specific programs or address specific needs such as payload requirements, there is an overlap of the type of information contained in each of them. For instance, three documents refer to the needs for “handling features to interface with other mass handling systems” such as the Body Restraint Tether (BRT), with some providing outdated values, no values at all or the correct values. Since the inception of each of these documents, some have continued to receive updates due to the necessity of an on-going program while others have remained unchanged for 20+ years and have led to discrepancies between the current accepted values and these outdated documents.

To prevent conflicts between multiple sources of information and to assess what is truly applicable to Exploration EVA System (xEVA) activities at Exploration Destinations (e.g., cislunar space and lunar surface), EVA-EXP-0035, Exploration EVA System Compatibility document was generated to produce a set of EVA design standards that apply to all hardware and systems that interface with the xEVA Suit and EVA activities at Exploration Destinations. While prior Space Shuttle Program, International Space Station (ISS) and Constellation Program (CxP) documents were reviewed and in part incorporated into this document, no document from those specific programs will be directly levied on any future Exploration Mission. This does not supersede documents for current and inactive programs, as documentation applicable to any on-going program will continue until the conclusion of that program.

Efforts in the past, such as the creation of JSC 28918, EVA Design Requirements and Considerations were attempted to provide a common source, that included ISS lessons learned, for all EVA requirements for future programs, but due to the on-going churn of ISS-EVA documentation and a lack of new programs going into development, resources were spent on maintaining and updating only the active program documentation. JSC 28918 was never officially levied as an ISS program document. Thus, JSC 28918 has not been updated. Instead, the focus has continued to keep ISS Program-levied EVA requirements documents up to date.

After generation of tailored versions for Artemis Systems such as Gateway and Human Landing System (HLS) Programs, and the existing EVA-EXP-0035 document, the newly formed Extravehicular Activity and Human Surface Mobility Program (EHP) determined that there was a need to consolidate into one document that would apply to all Artemis Systems. This led to the creation of this document EHP-10028, EHP Exploration EVA (xEVA) System Compatibility Standards.

Release Date: 09 MAY 2024 Page: 11 of 280

This document establishes design standards that minimize the performance risks to EVA flight crewmembers in human space flight programs and applies to future space vehicles, habitats, facilities, or any other hardware that will interface with the suited crewmember during space flight in various missions (e.g., cislunar space and lunar surface). As Design Reference Missions (DRM) evolve, this document will be updated to reflect utilizing the xEVA System at that destination.

Release Date: 09 MAY 2024 Page: 12 of 280

1.0 INTRODUCTION

Extravehicular Activity (EVA) is a significant capability for Artemis Systems which includes Gateway Program (modules), Human Landing System (HLS) Program (Integrated Lander and Human Class Delivery Lander), Lunar Terrain Vehicle (LTV), Pressurized Rover (PR), Payloads, and any other future lunar surface assets that will be utilized for exploration or science. The EVA and Human Surface Mobility Program (EHP) will provide the following: Exploration EVA (xEVA) suits, xEVA tools and crew aids along with vehicle integration/support hardware, LTV, and PR. Being a distributed and dynamic capability (moving components), xEVA System hardware will interface with almost all elements of the Artemis architecture. As such, it is important to document a singular set of EVA compatibility standards at the programmatic level to articulate “how to interface with xEVA suit hardware” and “how to design hardware that EVA crewmembers will access and manipulate.”

1.1 PURPOSE

The EHP xEVA Compatibility Standards document establishes a set of EVA compatibility design standards for hardware and systems that have an interface with the xEVA suit and/or must facilitate EVA activities. This document will be used by all Artemis Systems and contains the fundamental necessary information required for building and verifying that Artemis Systems hardware are compatible with suited EVA flight crewmembers to perform successful EVAs in microgravity/lunar orbit and on the lunar surface. It is to be used for the development of lower-level program/project-specific requirements.

Compatibility standards are in section 3.0 with gravity field (microgravity and partial gravity) associated with each requirement.

As an interface standard, EHP-10028 levies requirements on the xEVA System (managed by EVA Development Project), interfacing EHP Projects (LTV and PR) and cross-program partners (Human Landing System, Gateway, and Payloads). It contains verification guidance for Hardware Providers as well as EHP.

The Gateway Program is maintained and inspected both by the Gateway External Robotics Systems (GERS) capability (reference GP 10027, Gateway Concept of Operations) and by EVA capability. GERS is the Extravehicular Robotics (EVR) capability on Gateway. EVA capability is used for certain pre-defined maintenance tasks as well as for contingencies such as failure of the GERS, inability of the GERS to complete a task that was intended for GERS compatibility, or unforeseen tasks. When both accommodations of EVA and GERS operations are required, which are not explicitly defined in this document, an integrated strategy which will be certified or evaluated on a mission-specific basis to determine how best to account for both GERS and EVA design constraints and requirements necessary to support mission objectives.

1.2 SCOPE

This document defines standards controlled by the EHP ensuring that all hardware and Artemis System’s design are compatible with the xEVA suits and EVA activities in any

Release Date: 09 MAY 2024 Page: 13 of 280 given mission destination (e.g., cislunar space, and lunar surface). The standards herein are applicable to any hardware internally or externally that will be near, come in contact with or has features that can present hazards in any way to the xEVA crewmember.

Projects developed for the International Space Station (ISS) will continue to reference SSP 30256 EVA Interface Control Document (ICD), other applicable Interface Requirements Documents (IRDs), and JSC 26626 EVA Hardware Generic design Requirements Document as appropriate.

This document does not include information on the interfaces for space suit servicing, performance, and checkout equipment (e.g., items that directly interface with the space suit, such as fluid and electrical connectors), or non-mechanical interfaces (such as wireless communication, data, video, and audio). All these items will be defined in EHP- 10029, xEVA System to Artemis Systems Interface Requirements Document (IRD)

<TBR-EHP-10028-016>.

As part of the construction of this document, active EVA documents from the Shuttle Program, ISS Program and Constellation Program (CxP) eras were assessed for requirements pertaining to hardware compatibility with the EVA System and operations.

These documents were cross compared, and the relevant information was used to form the basis of the standards included in EHP-10028 and updates were made to correspond with the latest mission destinations. The initial documents reviewed with the specified revisions included the following:

• JSC 26626 Revision A, Extravehicular Activity (EVA) Hardware Generic Design Requirements Document (GDRD)

• JSC 26626 Draft Revision B, GDRD (unreleased)

• JSC 28918 Baseline, EVA Design Requirements and Considerations

• SSP 30256 Revision J, Extravehicular Activity (EVA) Standard ICD

• SSP 57003 Revision L, ISS External Payload IRD

• SSP 50005 Revision F, International Space Station (ISS) Flight Crew Integration Standard (NASA-STD-3001/T) – intent of this document for ISS is satisfied by

NASA-STD-3001

• SSP 50021 Baseline Document Change Notice (DCN) 005, Safety Requirements Document (Note – this document was superseded by Baseline of SSP 51721, Safety Requirements Document)

• CxP 70130 Revision A, CxP EVA Design and Construction Specification (document no longer active)

• NASA–STD-3001 V2 Revision A, Human Factors, Habitability, and Environmental Health.

**Evaluation of revisions to the still active documents are assessed for impacts to standards contained in this document.

In many cases the values used for defining microgravity compatibility with a space suit are based on heritage United States (US) EVA capabilities as carried over from the Space

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Shuttle Program and modified for the International Space Station (ISS) Program. It is expected that the xEVA Suit will either meet or exceed the capabilities of the original EVA suit capabilities. The xEVA System is provided to National Aeronautics and Space Administration (NASA) on a competitive service contract in which vendors are awarded Task Orders for future missions, tasks, and activities in an ongoing basis. Due to the uncertainty of the specific suit design that will be used for each individual mission/task/activity as a result of the ongoing Task Order award schedule, the terminology and noted dimensions/values in this document will be based on the government reference next generation EVA Suit design, also known as the Exploration Extravehicular Mobility Unit (xEMU). In general, an xEVA System consists of the EVA Suit (interchangeable with “xEVA Suit” or “xEMU” for the purposes of this document), EVA tools, and ancillary hardware that support EVA functions.

Each standard was assessed for application in a partial gravity environment and captures partial gravity considerations in the standard. As the xEVA suit design matures and/or as other suppliers of EVA hardware are identified, updates to the standards will be proposed to the appropriate change authority to reflect the improvement/changes in EVA capabilities. This document covers both microgravity and partial gravity EVA requirements. Partial gravity references in this document are specific to the lunar gravity field (1/6 gravity). As missions beyond lunar surface are developed, consideration of additional gravity fields (e.g., Martian gravity) will be addressed. References to weight in this document take into account the applicable gravity field (e.g., approximately 1/6th of Earth gravity for Lunar conditions).

For the purposes of this document, the term payload applies to any utilization science/research specific hardware that will interact with EVA equipment or tools.

Appendix A-2 provides glossary terms associated with payloads. There are external payloads on Gateway, which are not expected to be EVA serviceable but will be designed to protect EVA crewmembers. Gateway Payloads, Maintenance Items (MI), etc. designed for EVA cannot preclude GERS operations.

GP 10031, Gateway Visiting Vehicle Interface Requirements Document (IRD) defines the subset of EVA compatibility requirements for those Visiting Vehicles that may protrude into Gateway EVA translation paths. Any hardware that protrudes into the EVA contact hazard preclusion envelope must meet EVA kickloads, touch temperatures, and EVA safety requirements to protect the crewmember while performing an EVA on Gateway as well as protect the docked Visiting Vehicle hardware, even though the Visiting Vehicle may not have EVA requirements imposed on it. GP 10031, Gateway Visiting Vehicle IRD Annex 1: HLS Requirements requirement INFO-VV-HLS-0112 specifies that when HLS is docked to Gateway that both vehicles will meet EVA compatibility requirements.

Crew health and safety standards that describe the human-to-suit interfaces (like anthropometric requirements), or Intravehicular Activity (IVA) suit-to-vehicle interfaces are not included in this document. Those standards and their requirement guidance are

Release Date: 09 MAY 2024 Page: 15 of 280 included in NASA-STD-3001, Volume 1: Crew Health and Volume 2: Human Factors, Habitability, and Environmental Health, or tailored through respective Program/Project System Requirements Documents (SRDs). Specific crew health and safety related standards are found in NASA-STD-3001 V2. A supplementary NASA document, NASA/SP-2010-3407, Human Integration Design Handbook (HIDH) is a compilation of human space flight history and provides a resource for deriving program-specific requirements in accordance with NASA-STD-3001, Volume 2. EHP Projects, Gateway and HLS tailor NASA-STD-3001 through respective Project/Program documents.

1.3 APPLICABILITY/ALLOCATIONS

All requirements in this standard are applicable to the development of all Artemis program/projects that perform EVA operations or interact with the xEVA System. Each requirement contains the Gravity Field Applicability along with Allocation to the Artemis Systems. For the purposes of this document, “Artemis System” is considered to include the following:

1. External Program Spacecraft with EVA Capabilities – This document is applicable to vehicles that require EVA operations performing nominal and contingency:

maintenance, repair, and replacement, payload, and science utilization. Currently two external Programs (Gateway and HLS) have been identified, but any future EHP external Exploration Programs will utilize this document for EVA compatibility standards. HLS Assumptions for microgravity application: Microgravity requirements would only apply in cases where translation paths are required from HLS airlock to HLS EVA worksites (if vehicle had any), and that being docked to the staging vehicle cannot impede the HLS translation paths with no identified hazards. If no microgravity worksites required, then N/A, but requirement is applicable to drive review of scenarios and vehicle design.

2. Internal EHP Project Spacecrafts (e.g., LTV and PR) with EVA Capabilities – This document is applicable to vehicles that require EVA operations performing nominal and contingency: maintenance, repair and replacement, and payload operations.

3. EVA System (managed by EVA Development Project – This document is applicable to the xEVA System and decomposition of allocated requirements will be performed by EVA Development Project. This document applies to the xEVA System, and specifically to portions of the xEVA System that will be operated by the suited crewmember.

4. Payloads – This document is applicable to science and research instrument hardware that will be near to, come in contact with, or present hazards in any way to xEVA suits or suited EVA flight crewmembers.

All hardware providers need to make provisions for protecting the EVA crewmember from anything that presents a danger or safety hazard. EVA hazards that are not controlled on hardware that are outside the translation paths or associated zones will be declared a keep out zone or no touch area and this information provided to the Flight Operations Directorate (FOD) as operational controls.

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1.4 CONVENTIONS AND NOTATIONS

Shall Statements (Standards/Requirements)

The convention used in this document which indicates requirements, standards, goals, and statements of facts is as follows:

TABLE 1.3.1-1 CONVENTION AND NOTATIONS DESCRIPTIONS

Designation Description

“Shall” used to indicate a requirement that is binding, which must be implemented, and its implementation verified in the design.

“Should” used to indicate good practice or a goal which is desirable, but not mandatory and does not require a formal verification.

“Will” used to indicate a statement of fact or declaration of purpose on the part of the government that is reflective of decisions or realities that exist and are to be taken as a given and not open to debate or discussion.

Those statements that fall more into a design consideration/best practice are in APPENDIX B and APPENDIX C. While not considered requirements, these best practices are highly desirable for the design of hardware compatibility with EVA operations.

Requirement Identification

As documents are revised, there are cases where sections will move; therefore, each requirement in this document is uniquely numbered, and identified by the presence of a tag. The requirements tag “[EVASC.XXXX]” provides a trace to historical information across multiple Programs and Projects.

Rationale

A rationale statement is included for each requirement only when necessary. The purpose of the rationale statement is to indicate why the requirement is needed, the basis for its inclusion in a requirements document, and to provide context and examples to stakeholders. It is important to note that a rationale is not binding, and it only provides supporting information. In the event there is an inconsistency between the requirement and the rationale, the requirement is binding and takes precedence.

Units

Artemis Systems utilize NIST SP 811, Guide for the Use of International System of Units (SI), for standardization and conversions of the units of measure. For the purposes of this document, the unit of measure should be considered as metric as primary with English units in parenthesis unless otherwise noted. Microgravity requirements with associated figures and tables were derived from heritage ISS EVA requirements documents that contained English units. SI units in this document for those microgravity

Release Date: 09 MAY 2024 Page: 17 of 280 applications were converted from the heritage ISS English values. Therefore, the English units are considered to be the driver for metric conversion.

NOTE: Some referenced drawings and documents may use English units as primary and may or may not have metric units as secondary.

1.5 CHANGE AUTHORITY/RESPONSIBILITY

The Extravehicular Activity and Human Surface Mobility Program (EHP) Board Authority for Approval of this product is the EHP Control Board (EHPCB). Board Authority for future revisions of this product is not delegated. Board Authority for changes is the

EHPCB.

The administration of future revisions will be managed by the Office of Primary Responsibility (OPR). Proposed changes to this product shall be submitted via Change Management Workflow (CMW). All such requests will adhere to the EHP-20000, Extravehicular Activity and Human Surface Mobility Program (EHP) Configuration and Data Management Plan.

The appropriate NASA Office of Primary Responsibility (OPR) identified for this product is the EHP Systems Engineering and Integration (SE&I) Office (DI). The EHP Requirements, Interfaces, Verification, and Analysis (RIVA) Panel will be used to bring updates for community and stakeholder review prior to CR release. Approval of the technical accuracy of this document resides within the EHP SE&I Control Board (CB), with Programs/Projects providing agreement/concurrence at the EHPCB.

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2.0 DOCUMENTS

2.1 APPLICABLE DOCUMENTS

The following documents include specifications, models, standards, guidelines, handbooks, and other special publications. The documents listed in Table 2.1-1 are applicable to the extent specified herein. The EHP specific applicable documents and standards revisions listed are in accordance with EHP-10012, Extravehicular Activity and Human Surface Mobility Program (EHP) Systems Requirement Document, section

2.2.1. Any notation of NASA approved alternate standard needs to have Cross-Program Chief Engineer approval. Gateway Program applicable document revisions listed in Table 2.1-1 are in accordance with GP 10000, Gateway Program System Requirements section

2.2.1. HLS Program applicable document revisions listed in Table 2.1-1 are in accordance with the respective HLS SRD (reference Table 2.2-1).

TABLE 2.1-1 APPLICABLE DOCUMENTS LIST

Document Number Document Title EHP-10012 Extravehicular Activity and Human Surface Mobility Program

(EHP) Systems Requirements Document

EHP-10013 Extravehicular Activity and Human Surface Mobility Program (EHP) Verification and Validation Plan

EHP-10029

<TBR-EHP-10028-016>

Exploration Extravehicular Activity (xEVA) System to Artemis System Interface Requirements Document (IRD)

EHP-10074

<TBR-EHP-10028-008>

EHP EVA Tool List and Process for EVA Operations

EHP-20000 Extravehicular Activity and Human Surface Mobility Program (EHP) Configuration and Data Management Plan

EVA-EXP-0049 Extravehicular Activity (EVA) Office Exploration EVA (xEVA) System Labeling Guidelines

GP 10000 Gateway Program System Requirements

GP 11461 Gateway Requirements for the Control of Electromagnetic Interference (EMI) Characteristics of Subsystems and Equipment

GSDO-RQMT-1080 Cross-Program Contamination Control Requirements

HLS-STD-007 Human Landing System (HLS) Requirements for the Control of Electromagnetic Interference (EMI) Characteristics of Subsystems and Equipment

JPR 5322.1 Contamination Control Requirements Manual

NASA-STD-4003 Electrical Bonding for NASA Launch Vehicles, Spacecraft, Payloads, and Flight Equipment

SDG33107728 Tube – Handrail and Handgrip (via SEG33106347, Top Mounted Handrail Assy)

2.2 REFERENCE DOCUMENTS

The following documents contain supplemental information to guide the user in the application of this document and can include Type 3 Technical Authority (TA) Standards.

Reference Documents may be called out in any section or as a part of a requirement

Release Date: 09 MAY 2024 Page: 19 of 280 rationale and are not binding. Table 2-2.1 only lists the reference documents and revisions for this product.

TABLE 2.2-1 REFERENCE DOCUMENTS LIST

Document Number Document Revision

Document Title

2024-ABF-001 January 2024 Suited Capability Requirements for Partial Gravity – Anthropometry and Biomechanical Perspective

ACD-50012 Current Artemis Campaign Development (ACD) Enterprise Verification and Validation Plan

AML-01-02-R1 March 22, 2001 Advanced Materials Laboratory Test Report: Hot D-Ring / Space Suit Assembly (SSA) Lay-up Incidental Contact Test

EHP-10004 Current Extravehicular Activity and Human Surface Mobility Program (EHP) Systems Engineering Management Plan

(SEMP)

ES6-23-044 September 18, Lunar EVA Crew Induced Loads on Restraint Attachment Points from Crew Fall

ES6-24-001 February 22, 2024 Lunar EVA Crew Induced Loads

EX-24-008 April 23, 2024 EX-24-005, Artemis System Lunar Dust Tolerance – Amount of Dust Justification and Calculation

EVA-EXP-0031 Baseline EVA Office Extravehicular Activity (EVA) Airlocks and Alternative Ingress/Egress Methods Document

EVA-EXP-0032 Baseline EVA Office EVA-ISS Interface Definition Document

EVA-EXP-0034 Revision C Extravehicular Activity (EVA) Office Exploration EVA (xEVA) System Technical Standards

EVA-EXP-0035 Baseline w/Admin Change 1

EVA Office xEVA System Compatibility

EVA-EXP-0067 Revision C Human Landing System (HLS) Program Extravehicular Activity (EVA) Interface Requirements Control Document

(IRCD)

EVA-EXP-0070 Revision D with Change 2

HLS Program Extravehicular Activity (EVA) Compatibility Interface Requirements Document (IRD)

GP 10027 Current Gateway Concept of Operations

GP 10031 Current Gateway Visiting Vehicle IRD

GP 10031-01 Current Gateway Visiting Vehicle IRD Annex 1: HLS Requirements

HLS-RQMT-002 Current HLS Partner System Requirements Document (PaSRD) HLS-RQMT-006 Current HLS Integrated Lander Requirements Document –

Sustained Phase

HLS-RQMT-007 Current HLS Human-Class Delivery Lander (HDL) Requirements Document – Sustained Phase

HLS-RQMT-009 Current HLS Provider Integrated Lander Systems Requirements Document -Sustained - SpaceX

HLS-RQMT-109 Current HLS Provider Integrated Lander Systems Requirements Document -Sustained – Blue Origin

JSC 28528 A Preparation and Revision of Cx Mockup Development Requirements Document (MDRD) javascript:void(0)

Release Date: 09 MAY 2024 Page: 20 of 280

TABLE 2.2-1 REFERENCE DOCUMENTS LIST

Document Number Document Revision

Document Title

JSC 39117 C Extravehicular Mobility Unit (EMU) International Space Station (ISS) Extravehicular Activity (EVA) Thermal Environment Requirements for Certification

JSC 39198 3/14/2018 Incidental Contact Temperature Test on Extravehicular Mobility Unit (EMU) Softgoods Materials Lay-Up

JSC 65828 B w/ Change 1 Structural Design Requirements and Factors of Safety for Spaceflight Hardware

MIL-PRF-19500 R Semiconductor Devices, General Specification

MIL-DTL-81381 C

Amendment 1

Wire, Electric, Polyimide-Insulated, Copper, or Copper Alloy, Detail Specification

NASA/SP-2010-

Rev 1 Human Integration Design Handbook (HIDH)

NASA-STD-3001

Volume 2

D NASA Spaceflight Human-System Standard Volume 2:

Human Factors, Habitability, and Environmental Health

NASA-STD-5020 B Requirements for Threaded Fastening Systems in Spaceflight Hardware

NASA-STD-6016 C Standard Materials and Processes Requirements for Spacecraft

NIST SP 811 3/2008 Guide for the Use of the International System of Units (SI)

NPR 8705.4 A Risk Classification for NASA Payloads

SDG33107506 Latest Knob, Push, Pitch Joint Assembly Articulating Portable Foot Restraint (APFR), ISS

SED33107181 Latest EVA Knob Assembly, Bridge Clamp

SEG33114987 Latest 1.0 Inch Quick Disconnect (QD) Button Depress Tool Assy

SLS-SPEC-159 I Cross-Program Design Specification for Natural Environments (DSNE)

SSP 30256 Revision K Extravehicular Activity (EVA) Standard Interface Control Document (ICD)

SSP 30423 L Space Station Approved Electrical, Electronic and Electromechanical (EEE) Part List

SSP 57003 M ISS Payloads Interface Requirements Document (IRD)

Release Date: 09 MAY 2024 Page: 21 of 280

3.0 REQUIREMENTS

This section defines the minimum requirements and constraints that apply to performance, design, interoperability, maintainability, and safety of hardware that may come in contact or be operated by crew in pressurized EVA suits. The gravity field applicability (microgravity and partial gravity) is included after each requirement along with allocation to Artemis Systems. Variances to these requirements may be proposed to EHP, considered by the EHP RIVA Panel in accordance with EHP-10004, Extravehicular Activity and Human Surface Mobility Program (EHP) Systems Engineering Management Plan (SEMP), and approved via the EHP Variance CR process described in EHP-20000, Extravehicular Activity and Human Surface Mobility Program (EHP) Configuration and Data Management Plan.

3.1 CLEARANCES

Microgravity Translation Path Hardware Protrusion

[EVASC.0001] The Artemis System shall design or configure equipment to not protrude into the minimum 1.1 m (43 in) diameter translation path envelope, excluding translation aids (handrails/handholds) in microgravity as outlined in Figure 3.1.1-1 Translation Path Hardware Protrusion Envelope and Figure 3.1.1-2 Translation Path Minimum Diameter.

Rationale: In microgravity, the minimum diameter of the translation corridor of

1.1 m (43 in) is to accommodate hand-over-hand EVA crewmember translation.

Interference in translation paths may pose hazards to EVA crewmembers or impact the success of EVA activities by precluding translation to worksites. This includes any obstructions or intrusions in the envelope. This microgravity minimum diameter is based on the heritage ISS EMU suit and is associated with microgravity application.

Gravity Field Applicability: Microgravity

Allocation: EVA Dev, Gateway, HLS

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FIGURE 3.1.1-1 TRANSLATION PATH HARDWARE PROTRUSION ENVELOPE

FIGURE 3.1.1-2 TRANSLATION PATH MINIMUM DIAMETER

Partial Gravity Translation Path Hardware Protrusion

[EVASC.0171] The Artemis System shall design or configure equipment to not protrude into the minimum 1.1 m (43 in) diameter translation path envelope, excluding translation aids (handrails/handholds) and provide a translation path free of equipment and protrusions that accommodates the volume of the suited crewmember in partial gravity as outlined in Figure 3.1.2-1 Top View Partial Gravity Crew Envelope Diameter and Figure 3.1.2-2 Side View Partial Gravity Crew Envelope Height.

1.1 m (43 in)

1.1 m (43 in)

0.61 m

(24 in)

Release Date: 09 MAY 2024 Page: 23 of 280

Rationale: In partial gravity, the breadth and height of the translation path must accommodate the volume of the suited crewmember in any direction which the crew is expected to move. Interference in translation paths may pose hazards to EVA crewmembers or impact the success of EVA activities by precluding translation to worksites. This includes any obstructions or intrusions in the envelope. Partial gravity application ensures crewmembers can traverse around, to and from vehicle worksite areas (e.g., catwalk around a cargo lander, walking under the lander, ingress/egress of vehicle to the surface, areas around unpressurized and PRs).

Gravity Field Applicability: Partial Gravity

Allocation: EVA Dev, LTV, PR, HLS

FIGURE 3.1.2-1 TOP VIEW PARTIAL GRAVITY CREW ENVELOPE DIAMETER

EVA Translation Crew Envelope Diameter:

1.1 m (43 in)

[99th percentile shown]

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FIGURE 3.1.2-2 SIDE VIEW PARTIAL GRAVITY CREW ENVELOPE HEIGHT

Tool Interface Clearance

[EVASC.0002] The Artemis System shall maintain 7.6 cm (3.0 in) of clearance between the gripping portions of a tool interface and any surrounding hardware or obstructions with a tool handle offset maximum of 35.6 cm (14.0 in) as defined in Figure 3.1.3-1 Tool Interface Clearance.

Rationale: Tools to be used during EVAs are to be identified by the Artemis System, and clearances for efficient application are to be accommodated to ensure that the EVA task can be accomplished. The intent is that this requirement applies to EVA crew operated manual tools interfacing with EVA fasteners. To ensure the task can be accomplished, the clearance between the work surface and the tool design needs to include operation by a pressurized gloved hand. This includes

Release Date: 09 MAY 2024 Page: 25 of 280 protecting for the 7.6 cm (3.0 in) clearance to the nearest obstruction(s) in addition to the grasp length of the tool handle. Reference [EVASC.0004] which defines the handrail mounting clearance distance that accommodates grasp of the pressurized gloved hand. The bolt head tool clearance is defined in requirement [EVASC.0007]. Minimum grip length is assumed to be length of handrail/handhold/handle requirement [EVASC.0030].

Gravity Field Applicability: Microgravity, Partial Gravity

Allocation: EVA Dev, LTV, PR, Gateway, HLS, Payloads

FIGURE 3.1.3-1 TOOL INTERFACE CLEARANCE

Bolt Clearance

[EVASC.0007] The Artemis System shall maintain a 2.5 cm (1.0 in) clearance around the bolt head outer edge with a minimum tool head engagement height of 0.8 cm (0.3 in) to

7.6 cm (3 in) clearance radially around handle grasp surface, and from end of tool to nearest adjacent obstructions/structure

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Rationale: The intent of this requirement is to ensure tool access with the fastener head.

Gravity Field Applicability: Microgravity, Partial Gravity

Allocation: EVA Dev, LTV, PR, Gateway, HLS, Payloads

Gloved-Hand Clearance

[EVASC.0003] The Artemis System shall maintain minimum clearance envelope for a gloved hand access as specified in Figure 3.1.5-1 Gloved-Hand Clearance.

Rationale: Pressurized EVA gloves have their own thickness in addition to the human hands they protect. Interfaces to be operated by the EVA crewmember must accommodate the dimensions of the hand/glove combination.

FIGURE 3.1.5-1 GLOVED-HAND CLEARANCE

Handrail/Handhold Mounting Clearance

[EVASC.0004] The Artemis System shall maintain a minimum clearance distance between the lower surface of the handrail/handhold and the mounting surface of 5.72 cm

20 cm (8 in)

46 cm (18 in)

36 cm (14 in)

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(2.25 in) as shown in Figure 3.1.6-1 EVA Handrail/Handhold Mounting Clearance Envelope.

Rationale: EVA handrail cross sections themselves have been designed to facilitate grasping by the gloved EVA crewmember’s hand. However, it is theoretically possible to mount a handrail in such a way (such as immediately next to structure or over an exposed structural rib) that the EVA crewmember’s gloved hand cannot access the EVA handrail. To ensure EVA handrails are mounted in a manner that preserves/facilitates their use, the area around and underneath handrails/handholds must be free of obstructions within the specified clearance dimensions. Adequate clearance is required to facilitate use by a pressurized gloved hand. This also supports clearance for tether hook attachment to the stanchions.

FIGURE 3.1.6-1 EVA HANDRAIL/HANDHOLD MOUNTING CLEARANCE ENVELOPE

Note: The 71 cm (28 in) handrail is an example.

Handrail/Handhold Side Clearance

[EVASC.0005] The Artemis System shall maintain a minimum 10 cm (4 in) clearance to both sides of handrail/handholds as defined in Figure 3.1.7-1 Handrail/Handhold Side Clearance.

Rationale: To ensure EVA handrails are mounted in a manner that preserves/facilitates their use, the area around and underneath handrails/handholds must be free of obstructions within the specified clearance

5.72 cm (2.25 in)

8.1 cm

(3.2 in)

Release Date: 09 MAY 2024 Page: 28 of 280 dimensions. Adequate clearance is required to facilitate use by a pressurized gloved hand.

FIGURE 3.1.7-1 HANDRAIL/HANDHOLD SIDE CLEARANCE

APFR EVA Installation/Removal Clearance

[EVASC.0006] The Artemis System shall maintain a clearance envelope around the Passive Worksite Interface (WIF) to support EVA installation/removal of the APFR as defined in Figure 3.1.8-1 APFR Installation/Removal EVA Clearance Envelope – Top Mounted WIF.

Rationale: The intent is to ensure adequate clearance is provided to support installation/removal of hardware designed to interface with the passive WIF.

Contact EHP for consideration and potential use of other EVA WIF configurations.

Nominally used in microgravity environment.

Gravity Field Applicability: Microgravity

Allocation: Gateway, HLS

10 cm

(4 in)

Minimum handrail clearance

10 cm

(4 in)

10 cm

(4 in)

10 cm

(4 in)

Minimum handrail clearance

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Notes:

1. Drawing not to scale

2. Point C is the centroid of the bolt pattern

FIGURE 3.1.8-1 APFR INSTALLATION/REMOVAL EVA CLEARANCE ENVELOPE – TOP

MOUNTED WIF

10 cm

(4 in)

10 cm

(4 in)

20 cm

(8.0 in)

44.7 cm

(17.6 in)

10 cm

(4 in) radius

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3.2 TRANSLATION

Contiguous EVA Translation Path

[EVASC.0152] The Artemis System shall provide EVA compatible accommodations to support contiguous translation paths to adjacent berthed/docked vehicles.

Rationale: A contiguous translation path is defined as the path from/to the airlock to/from any vehicle worksite that a crewmember needs to access for EVA operations. For vehicles that are berthed/docked to other vehicles, these contiguous translation paths need to provide for translation from one vehicle to another. Intentionally designed translation paths include illumination and features such as handrails and tether points free from contact hazards that promote safe and efficient EVA translation. These translation paths allow the EVA crewmember to safely translate across multiple vehicles which may include a safe and quick emergency return to the airlock. Translation paths to EVA worksites are addressed in [EVASC.0008].

Gravity Field Applicability: Microgravity

Allocation: Gateway, HLS

Translation Path

[EVASC.0008] The Artemis System shall design a translation path to all EVA worksites.

Rationale: These translation paths within the design constraints of the host vehicle. Intentionally designed translation paths include illumination and features such as handrails and tether points free from contact hazards that promote safe and efficient EVA translation. These translation paths allow the EVA crewmember to safely access worksites as well as to return to the airlock safely and quickly in case of an emergency for microgravity application. Partial gravity application ensures crewmembers can traverse around, to and from vehicle worksite areas (e.g., catwalk around a cargo lander, walking under the lander, ingress/egress of vehicle to the surface).

Gravity Field Applicability: Microgravity, Partial Gravity

Allocation: Gateway, HLS

Incapacitated Crewmember Interfaces

[EVASC.0154] The Artemis System shall provide hardware that aids a suited crewmember in the rescue of an incapacitated suited crewmember from the surface or microgravity location and return for ingressing the vehicle through the EVA hatch, culminating in positioning the suited incapacitated crewmember in an xEVA System for extraction which may require a 1st percentile female to rescue a 99th percentile male.

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Rationale: Incapacitated pressurized-suited crewmembers may be unable to ingress the vehicle (e.g., Tool cart, LTV, PR, HLS) on their own and may require assistance from a second crewmember. Depending on architecture and hatch height from the lunar surface, this can include items such as winch and rescue harness, deck space/porch, hatch seal cover, etc. Devices may need to be operated by a suited crewmember both internal and external to the vehicle.

Microgravity considerations include increased stability and aids for the incapacitated crew handling and/or restraint. NASA will assist in the design definition by identifying credible scenarios and the degree by which a crewmember is incapacitated.

This includes the volume to perform the assisted task, hatch opening size and operation, as well as the external translation path and mobility/stabilization aids.

Removing an incapacitated crewmember from a rear entry suit could be challenging and could require extra support structure, or possible tools to assist the crewmember inside as well as removal from the suit.