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Sustained Phase Human Landing System Program Concept of Operations June 2022

HLS-CONOP-006

REVISION A

National Aeronautics and Space Administration RELEASE DATE: JUNE 29, 2022

SUSTAINED PHASE HUMAN LANDING SYSTEM (HLS)

CONCEPT OF OPERATIONS

Publicly Available: Release to Public Websites Requires Approval of

Chief, Office of Primary Responsibility, and approval via the Scientific and Technical

Information (STI) process, if applicable

Revision: A Document No: HLS-CONOP-006

Release Date: June 29, 2022 Page: 2 of 38

Title: SUSTAINED PHASE HLS PROGRAM CONCEPT OF OPERATIONS

Sustained Phase Human Landing System Program Concept of Operations June 2022

REVISION AND HISTORY PAGE

Revision No.

Change No.

Description Release

Date

- HLS-C0207 Initial Release (Reference HCB.12.15.2021) 03/03/22

A - Revision A (Reference OSB HCB.06.27.2022)

Updated in support of the response to App P provider feedback.

06/29/22

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Sustained Phase Human Landing System Program Concept of Operations June 2022

TABLE OF CONTENTS

SECTION PAGE

1 INTRODUCTION

1.1 PURPOSE

1.2 SCOPE

1.3 CHANGE AUTHORITY AND RESPONSIBILITY

1.4 APPLICABLE DOCUMENTS

1.5 REFERENCE DOCUMENTS

2 SUMMARY

3 DESIGN REFERENCE MISSIONS (DRM)

3.1 DRM-H-001 POLAR SORTIE MISSION

3.1.1 DRM-H-001b Non-Polar Sortie Mission Variant

3.2 DRM-H-002 POLAR EXCURSION MISSION

4 MISSION PHASES

4.1 UNCREWED LAUNCH, TRANSIT, AND AGGREGATION

4.1.1 HLS Launch to NRHO Insertion

4.2 INITIAL LUNAR ORBIT OPERATIONS

4.2.1 Initial Loiter

4.2.2 Initial Rendezvous, Proximity Operations, & Docking (IRPOD)

4.2.3 Initial Uncrewed Docked Operations

4.2.4 Initial Crewed Docked Operations (IDOPS)

4.2.5 Initial Undock & Backaway (IU&B)

4.3 DESCENT

4.3.1 NRHO Departure Burn (NRD)

4.3.2 Descent Transit

4.3.3 Descent Phasing Orbit Loiter

4.3.4 Final Descent

4.3.5 Descent Abort

4.4 SURFACE OPERATIONS

4.4.1 Sortie Missions

4.4.2 Extended Surface Excursion Missions

4.4.3 EVA

4.4.4 Ascent Preparations

4.4.5 Surface Early Mission Termination

4.5 ASCENT

4.5.1 Powered Ascent

4.5.2 Ascent Phasing Orbit Loiter

4.5.3 Ascent Transit

4.5.4 NRHO Insertion Burn

4.6 RETURN LUNAR ORBIT OPERATIONS

4.6.1 Return Loiter (RLTR)

4.6.2 Return Rendezvous, Proximity, Operations and Docking (RRPOD)

4.6.3 Return Docked Operations (RDOPS)

4.6.4 Shared Environment

4.6.5 RTE Preparations

4.6.6 Return Undock & Backaway

4.7 POST-CREWED MISSION OPERATIONS

5 OFF NOMINAL AND CONTINGENCY OPERATIONS

5.1 EMERGENCIES

5.2 SYSTEM CONTINGENCIES

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5.3 HLS CREW CONTINGENCIES

APPENDIX

APPENDIX A ACRONYMS AND ABBREVIATIONS AND GLOSSARY OF TERMS

APPENDIX B OPEN WORK

TABLE

Table 1.4-1 Applicable Documents Table 1.5-1 Reference Documents Table 3-1 Overview of Primary DRMs Table 3-2 DRM-H-001 Variant Table A1-1 Acronyms and Abbreviations Table A2-1 Glossary of Terms Table B1-1 To Be Specified Items Table B2-1 Forward Work Items

FIGURES

Figure 3-1 Sustained Phase Mission Architecture (Generic 3-Element Option) Figure 3-2 DRM-H-001 Polar Sortie Mission Figure 3-3 DRM-H-001B Non-Polar Sortie Mission Figure 3-4 DRM-H-002 Extended Surface Excursion Mission

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Sustained Phase Human Landing System Program Concept of Operations June 2022

1 INTRODUCTION

The sustained phase Human Landing System (HLS) Concept of Operations (ConOps) describes the HLS integrated lander mission concepts that will enable a sustained human lunar presence.

The HLS integrated lander is a vehicular system that first transports crew essential logistics and mission support equipment from Earth to near-rectilinear halo orbit (NRHO). The HLS integrated lander then transports crew from Gateway in NRHO to the lunar surface, enables the crew to perform multiple Extravehicular Activity (EVA) events and access surface assets, and then safely returns the crew to Gateway for return to Earth (RTE). The HLS integrated lander also returns lunar samples and other equipment to NRHO to enable sample Return-to-Earth (RTE) for further scientific study.

1.1 PURPOSE

NPR 7123.1C Appendix A states that a ConOps "stimulates the development of the requirements and architecture related to the user elements of the system. It serves as the basis for subsequent definition documents." NPR 7123.1C also illustrates in Figure 3-1 SE Engine that SE Process 1 Stakeholder Expectations Definition feeds into SE Process 2 Technical Requirements Definition.

One of the outputs of SE Process 1 is a ConOps, whereas requirements documents and interface requirement documents (IRDs) are an output of SE Process 2.

The primary purpose of this document is to define the concept of operations for the sustained phase of the NASA Artemis effort to establish a sustained human presence on the Moon. This document captures the top-level operational concept for how the HLS sustained phase service providers will be expected to participate in the broader NASA effort. This document is also used to define HLS mission phases and is intended to inform the functional analysis that provides the basis for HLS Program requirements.

The Design Reference Missions (DRMs) are included to describe the current understanding of mission types to be used in the sustained phase of lunar exploration. The DRMs establish an operational context, descriptions of situations that will be encountered during the selected mission types, and top-level operational sequences with a focus on interactions between the HLS integrated lander, non-HLS systems, and NASA crew. Also, the DRMs are intended to capture capabilities, rather than a manifest or specific mission plan. The DRMs are representative of currently known bounding cases.

1.2 SCOPE

The NASA Artemis effort encompasses two exploration campaign segments, the Human Lunar Return (initial) and Sustained Lunar Presence (sustained). This document defines the mission concepts for the early portions of the sustained campaign missions. It also identifies the potential functional interactions of the HLS integrated lander with Orion, Gateway, Extravehicular Activity (EVA) system, lunar surface systems, and NASA crew. The specific architecture/vehicle implementation of this ConOps will be provided in future documentation, as this represents only provider-agnostic information.

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Sustained Phase Human Landing System Program Concept of Operations June 2022

1.3 CHANGE AUTHORITY AND RESPONSIBILITY

Proposed changes to this document shall be submitted via a Change Request (CR) to the appropriate Human Landing System Control Board for consideration and disposition.

All such requests will adhere to the Human Landing System Configuration and Data Management Plan, documented in HLS-PLAN-004. The appropriate NASA Office of Primary Responsibility (OPR) identified for this document is HLS Systems Engineering & Integration Office.

1.4 APPLICABLE DOCUMENTS

The following documents include specifications, models, standards, guidelines, handbooks, and other special publications. The documents listed in this paragraph are applicable to the extent specified herein.

TABLE 1.4-1 APPLICABLE DOCUMENTS

DOCUMENT NUMBER DOCUMENT TITLE

AES-50007 AES Concept of Operations

GP 10027 Gateway Concept of Operations

HEOMD-003

(ANNEXES 1-8)

Crewed Deep Space Systems Human Rating Certification Requirements and Standards for NASA Missions

HEOMD-007 HEOMD SCOPE

HEOMD-404 Artemis Base Camp Reference Mission

HLS-CONOP-008 HLS Sustaining Phase RF Communications Concept of Operations

HLS-PLAN-004 HLS Configuration and Data Management Plan

LTV-CONOP-001 Lunar Terrain Vehicle Concept of Operations

1.5 REFERENCE DOCUMENTS

The following documents contain supplemental information to guide the user in the application of this document. Requirements and IRDs are listed within the ConOps as reference documents because NPR 7123.1C Appendix A states that a ConOps "stimulates the development of the requirements and architecture related to the user elements of the system. It serves as the basis for subsequent definition documents."

TABLE 1.5-1 REFERENCE DOCUMENTS

Document Number Document Title

AES-50002 AES Artemis Lunar Exploration Requirements

ESD 10012 ESD CONOPS

EVA-EXP-0042 Exploration EVA System Concept of Operations

EVA-EXP-0067 HLS - xEVA Interface Requirement Control Document

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Sustained Phase Human Landing System Program Concept of Operations June 2022

TABLE 1.5-1 REFERENCE DOCUMENTS

Document Number Document Title

EVA-EXP-0070 HLS EVA Compatibility Interface Requirements Document (IRD)

EVA-EXP-0070-ANX-02 HLS EVA Compatibility IRD Annex - Integrated Lunar Sustained Phase

GP 10031-01 Gateway to Visiting Vehicle IRD, Annex 1: HLS Program Integrated Lander Requirements

GP 10045-01 Gateway to Visiting Vehicle RF IRD, Annex 1: HLS Program Integrated Lander Requirements

GP 10046-01 Gateway to Lunar Systems RF IRD, Annex 1: HLS Program Integrated Lander Requirements

GP 10164 Artemis Specification for the Rendezvous, Proximity Operations and Docking/Undocking (RPODU) Targets

HEOMD-003-01-08 Crewed Deep Space Systems Human Rating Certification Requirements and Standards for NASA Missions

HEOMD-006 Human Exploration and Operations (HEO) Utilization Plan

HLS-IRD-004-01 HLS Program Integrated Lander to Mission Systems IRD – Sustained Phase

HLS-PAP-008 Human Landing System (HLS) Landing Site Considerations for Sustained Phase Missions

HLS-PAP-014 Lunar Surface Standby Operations

HLS-PAP-018 Initial Evaluation of Non-Polar Access

HLS-PLAN-016 HLS Technical Management Plan

HLS-RQMT-006 HLS Program Integrated Lander Requirements Document – Sustained Phase

SPD-1 Space Policy Directive-1 Reinvigorating America's Human Space Exploration Program

2 SUMMARY

The HLS integrated lander is a vehicular system that enables the transport of logistics and mission support equipment from Earth to an Earth-Moon L2 NRHO, which is oriented over the southern pole with a 9:2 synodic resonance with the Moon’s orbit around Earth. The HLS integrated lander transports crew and cargo from Gateway in NRHO to the lunar surface, provides crew habitation and EVA support on the surface, and then safely returns crew and cargo to the Gateway for return to Earth. After the initial mission phase, the lunar campaign will evolve to the sustained phase for

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Sustained Phase Human Landing System Program Concept of Operations June 2022 more ambitious surface missions. In the sustained phase, the HLS integrated lander will require the capability to dock to Gateway, land up to four crew members on the lunar surface for transfer to habitable lunar surface assets, operate for extended durations near the lunar south pole, and support eight-hour EVAs for the advancement of surface goals. Also, the agency has a goal of being able to perform two-crew sorties to non-polar landing sites.

3 DESIGN REFERENCE MISSIONS (DRM)

The DRMs contained in this section are intended to serve as the bounding mission cases that describe the top-level operational sequence that drives HLS system and mission design during the sustained phase of the Artemis lunar exploration campaign. There are currently two primary DRMs and one variant; any DRM variants are intended to be a representation of using the primary DRM established capabilities in different operational contexts and external environments. The overall Artemis mission architecture is generically represented in Figure 3.0 from Space Launch System (SLS) launch through Orion’s NRHO departure; the shown three-element architecture is for reference only and represents one possible approach.

Figure 3-1 Sustained Phase Mission Architecture (Generic 3-Element Option)

The total set of capabilities needed for the campaign have been broken down into sets of capabilities, with each set being defined by a design reference mission. Table 3-1 provides a summary of the primary DRMs.

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TABLE 3-1 OVERVIEW OF PRIMARY DRMS

DRM-H-001

POLAR SORTIE

DRM-H-002

POLAR EXCURSION

CREW STAGING VEHICLE Gateway Gateway

SURFACE CREW SIZE 2 4

SURFACE STAY (DAYS) 6.25 33

LANDING LOCATION South Pole Artemis Base Camp

DARKNESS (HOURS) 0-40

120-230 (per period) 240-460 (total duration)

SURFACE HABITATION HLS Integrated Lander HLS Integrated Lander and Artemis Base Camp Elements

NUMBER OF EVAS

5 total:

• 4 planned

• 1 unplanned

2 total:

• 1 full round-trip transfer by EVA

• 1 unplanned

3.1 DRM-H-001 POLAR SORTIE MISSION

Figure 3-2 DRM-H-001 Polar Sortie Mission

DRM-H-001 is a sortie to the lunar south pole region with two crew members and a surface stay of up to 6.25 days. The HLS integrated lander element(s) will launch and be delivered uncrewed into NRHO. Once the HLS integrated lander element(s) are integrated in NRHO, the first part of the Lunar Orbit Checkout Review (LOCR) will be conducted, and the HLS integrated lander will dock to Gateway after a “GO” call is made. After docking, the second part of LOCR will be

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Sustained Phase Human Landing System Program Concept of Operations June 2022 conducted to ensure the HLS integrated lander is healthy prior to crew launch on Orion. Once an “GO” call is made from LOCR, the Initial Uncrewed Docked Operations Phase begins. During this phase, the HLS integrated lander may remain docked to Gateway or undock and loiter separately to manage vehicle consumable constraints but must be successfully redocked prior to Orion arrival in NRHO.

Once Orion has arrived, it will deliver a co-manifested payload to Gateway as part of its arrival and Gateway docking activities. Co-manifested payload delivery and operations will be payload specific. Some of the payloads will be new Gateway modules that require some initial activation before preparation for the surface mission may begin. Also, some deliveries may require Orion to relocate to a different Gateway port upon successful co-manifested payload docking. These delivery operations could require an additional revolution in NRHO prior to beginning the surface mission, for a total initial docked operations time of approximately 1.5 revolutions, or 9-10 days.

The HLS integrated lander will remain docked to Gateway during these operations.

The Initial Docked Operations (IDOPS) phase will begin when Orion has successfully docked to the port where it will be located for the remainder of the crewed NRHO mission, the hatches are opened to connect the two environments, and the crew has successfully ingressed into Gateway.

IDOPS is focused on ensuring that the crew, HLS integrated lander, and EVA and intravehicular activity (IVA) suits are ready to perform the surface operations mission phase. The preparation activities will occur at Gateway, and Gateway will be responsible for delivery of some of the surface mission equipment via Deep Space Logistics (DSL). This equipment will then need to be transferred to the HLS integrated lander. The items delivered by DSL and the HLS integrated lander will be determined on a mission specific basis.

Once the crew, spacesuits, and any additional mass to be delivered to the surface (such as defined by HLS-RQMT-006) are in the HLS integrated lander and ready for the surface operations phase, then the HLS integrated lander will undock and back away from Gateway and descend to the lunar south pole. The total HLS integrated lander habitation capability for two crew members for DRM-H-001 and variants is required to be at least eight days from staging vehicle undocked to staging vehicle docked. The HLS integrated lander surface habitation (SH) duration will be driven by the mission-specific duration spent in descent and ascent, but this duration is expected to be approximately six days. While on the surface, the crew will perform multiple EVAs that begin and end in the HLS integrated lander to support utilization and exploration goals. The sustained phase HLS integrated lander design will have the capability to support up to five (four planned and one unplanned) EVAs per sortie with EVA durations lasting up to eight hours, as defined by HLS-RQMT-006, and the capability for an additional hour of contingency. The total number of conducted EVAs will be a function of achievable surface stay time and other operational considerations (to be determined by or negotiated with NASA). When the approximately six-day surface operations are completed, the HLS integrated lander will perform ascent to return the crew, samples, and selected equipment (such as defined by HLS-RQMT-006) to Gateway in

NRHO.

Once in NRHO, the HLS integrated lander will rendezvous and dock to Gateway. The crew and lunar samples will be transferred to Orion for RTE. Excess trash will be transferred out of Orion to ensure that Orion does not exceed its Earth re-entry mass limit. At the end of the crewed phase of the mission, the hatches between Gateway and the HLS integrated lander will be closed. The HLS integrated lander will remain docked to Gateway until after Orion undocks and begins the RTE. If the provider chooses to dispose of the HLS integrated lander, this must be done safely after Orion has begun RTE and should be done in a way as to not interfere with the Gateway NRHO Reference Trajectory. The disposal must also meet all planetary protection requirements.

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Sustained Phase Human Landing System Program Concept of Operations June 2022

Alternatively, the provider may begin preparations for future HLS missions with the HLS integrated lander after Orion has begun RTE.

3.1.1 DRM-H-001B NON-POLAR SORTIE MISSION VARIANT

DRM-H-001b is a variant of DRM-H-001 and outlined in Figure 3-3 and Table 3-2 below. It is a two-crew surface sortie mission that will use the non-polar sortie capability to target a lunar landing at a location of scientific interest other than the lunar south pole. The Non-Polar Sortie missions could land at sites within a wide range of latitudes and are not restricted to solely the Earth-facing side, which requires the HLS integrated lander to be capable of operating in a wide range of surface thermal and solar angle environments.

Figure 3-3 DRM-H-001B Non-Polar Sortie Mission

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Sustained Phase Human Landing System Program Concept of Operations June 2022

TABLE 3-2 DRM-H-001 VARIANT

DRM-H-001B

NON-POLAR SORTIE

CREW STAGING VEHICLE Gateway

SURFACE CREW SIZE 2

SURFACE STAY (DAYS)

2 (threshold) 6 (goal)

LANDING LOCATION Non-Polar

DARKNESS (HOURS) 0-40

SURFACE HABITATION HLS Integrated Lander

NUMBER OF EVAS

2 (threshold):

• 1 planned

• 1 unplanned 5 (goal):

• 4 planned

• 1 unplanned

Similar to DRM-H-001, this variant includes the HLS provider delivering manifested logistics and equipment from Earth to NRHO and using DSL to deliver some of the surface mission equipment.

This equipment will need to be transferred to the HLS integrated lander. The items delivered by DSL will be determined on a mission-specific basis.

Because the overall capability of the vehicle should be determined by the primary DRM-H-001, transit and surface stay times for non-polar sorties will vary based on landing location. More detail on NRHO-based non-polar flight profile considerations may be found in HLS-PAP-018 Initial Evaluation of Non-Polar Access. While the overall HLS crewed mission duration is similar to DRM- H-001, the split between in-space operations time and surface operations time should be tailored to the orbital mechanics specific to the selected landing site and mission date. This tailoring will allow mission planners to balance surface exploration goals with HLS operational requirements.

The surface stay duration will be no longer than six days but may be shorter (e.g., approximately two days as shown in Figure 3-3) if the HLS integrated lander spends more time in transit from NRHO or in low lunar orbit (LLO) loiter.

Like other sortie DRMs, the crew of two will live and work out of the HLS integrated lander during their surface stay and will perform multiple EVAs to support utilization and exploration goals. The total number of conducted EVAs will be a function of achievable surface stay time and other operational considerations (to be determined by or negotiated with NASA). Once the surface operations are complete, the HLS integrated lander will perform ascent to return the crew, selected equipment, samples, and any additional return mass (as defined by HLS-RQMT-006) to Gateway in NRHO.

Once in NRHO, the HLS integrated lander will rendezvous and dock to Gateway. The crew and lunar samples will be transferred to Orion for RTE. Excess trash will be transferred out of Orion to ensure that Orion does not exceed its Earth re-entry mass limit. Prior to Orion departure, the

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Sustained Phase Human Landing System Program Concept of Operations June 2022 hatches between Gateway and the HLS integrated lander will be closed. If the provider chooses to dispose of the HLS integrated lander, this must be done safely after Orion has begun RTE and should be done in a way as to not interfere with Gateway. Alternatively, the provider may begin preparations for future HLS missions with the HLS integrated lander after Orion has begun RTE.

3.2 DRM-H-002 POLAR EXCURSION MISSION

Figure 3-4 DRM-H-002 Extended Surface Excursion Mission

DRM-H-002 is an extended surface excursion mission that will leverage pre-placed assets at the lunar south pole to support four crew for a longer duration surface mission of up to 33 days. The HLS integrated lander will deliver mass from Earth to NRHO that includes all or part of the total manifested mission logistics and equipment, as defined by HLS-RQMT-006.

The HLS integrated lander element(s) will launch and be delivered uncrewed into NRHO. Once the HLS integrated lander element(s) are integrated in NRHO, the first part of the Lunar Orbit Checkout Review (LOCR) will be conducted, and the HLS integrated lander will dock to Gateway after a “GO” call is made. After docking, the second part of LOCR will be conducted to ensure the HLS lander is healthy prior to crew launch on Orion. Once an “GO” call is made from LOCR, the Initial Uncrewed Docked Operations Phase begins. During this phase, the HLS integrated lander may remain docked to Gateway or undock and loiter separately to manage vehicle consumable constraints but must be successfully redocked prior to Orion arrival in NRHO.

After Orion inserts into NRHO, it will dock to Gateway for preparation for the extended lunar surface operations phase. During some missions, Orion will be delivering a co-manifested payload to Gateway as part of its arrival activities. Each co-manifested payload will have module-specific delivery and initial operations that need to occur prior to beginning preparation for the surface mission. Delivery of some co-manifested payloads may require Orion relocating to a

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Sustained Phase Human Landing System Program Concept of Operations June 2022 different Gateway port upon successful co-manifested payload docking. The HLS integrated lander will remain docked to Gateway during these operations.

The IDOPS phase will begin when Orion has successfully docked to the port where it will be located for the remainder of the crewed NRHO mission, the hatches are opened to connect the two environments, and the crew has successfully ingressed into Gateway. IDOPS is focused on ensuring that the crew, HLS integrated lander, and EVA and IVA suits are ready to perform the surface operations mission phase. Part of the preparation activities for DRM-H-002 are preparing Gateway to be uncrewed for approximately 35 days. Gateway is responsible for delivery of the surface mission equipment via the DSL. The items delivered by DSL will be determined on a mission-specific basis. DSL cargo might be transferred to the HLS integrated lander. These additional operations may require an additional NRHO revolution of integrated stack operations prior to the surface excursion.

Once all vehicles have been properly prepared and crew and supplies are ready for the surface operations, the HLS integrated lander will undock from Gateway and descend to the Artemis Base Camp at the lunar south pole with four crew on board. The total HLS integrated lander habitation capability for four crew for DRM-H-002 is required to be at least eight days.

Once on the lunar surface, the crew will prepare to perform transfers to other pre-placed habitable elements at the Artemis Base Camp (ABC) to live in for the duration of their surface stay. The HLS integrated lander will need the capability to provide 5 days of crewed surface habitation time for this DRM, split between pre- and post-transfer activities. The crew will then transfer from the HLS integrated lander to the habitable surface element(s) where they will live and work for the remainder of the excursion. The sustained missions will have the capability to perform EVAs for a max duration of eight hours, plus an additional hour allocated as contingency. This will facilitate the transfer to surface elements and advancement of surface goals.

Once the crew has transferred to the surface elements, the HLS provider may choose to operate their vehicles in standby mode. Standby mode is a state in which the HLS integrated lander is not the source of crew life support and is not in the critical path for dynamic surface activities such as EVA, rover expeditions, etc., but it remains the crew’s lifeboat in some off-nominal and early mission termination scenarios. The HLS integrated lander standby mode may be leveraged to reduce power use, consumables use, etc., and the minimum vehicle functions that should still be present are defined in HLS-PAP-014 Lunar Surface Standby Operations. The HLS integrated lander will be capable of maintaining communication with prepositioned surface assets. During any part of the surface operations phase, the HLS integrated lander will be required to survive periods of both prolonged, continuous, and intermittent darkness due to surface feature shadowing. Additionally, due to the length of the surface stay, the sun may travel 360 degrees around the HLS integrated lander, changing solar angles and shadowing. At the end of the surface operations phase, the crew will transfer to the HLS integrated lander and prepare the HLS integrated lander for departure from the lunar surface.

Once the surface operations phase has been completed, the HLS integrated lander will perform ascent to return the crew, utilization equipment, Government-Furnished Property (GFP), and samples to Gateway in NRHO. Once in NRHO, the HLS integrated lander will rendezvous and return docked operations will begin. When the vehicle has safely docked, lunar samples, any return cargo, and crew will be transferred to Orion for RTE. Excess trash will be transferred out of Orion to ensure that Orion does not exceed its Earth re-entry mass limit. At the end of the crewed portion of the HLS mission, the hatches between Gateway and the HLS integrated lander will be closed. The HLS integrated lander will remain docked until after Orion undocks and departs for Earth. The HLS integrated lander may then undock or remain docked to Gateway and prepare

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Sustained Phase Human Landing System Program Concept of Operations June 2022 for future missions with the HLS integrated lander or dispose of itself as necessary.

4 MISSION PHASES

This section describes and defines each HLS mission phase when utilizing Gateway and serves as the program reference for mission phase nomenclature. For purposes of simplification, this document will refer to DRM-H-001 and DRM-H-001b as the sortie missions, and DRM-H-002 as the surface excursion missions. This section will indicate where the mission types differ.

HLS DRMs are decomposed into the following mission phases, that are defined further in subsequent subsections:

• Uncrewed Launch, Transit, and Aggregation

• Initial Lunar Orbit Operations

• Descent

• Surface Operations

• Ascent

• Return Lunar Orbit Operations

• Post-Mission Operations

4.1 UNCREWED LAUNCH, TRANSIT, AND AGGREGATION

4.1.1 HLS LAUNCH TO NRHO INSERTION

For each HLS mission, the HLS provider will safely deliver a fully certified HLS integrated lander along with mission logistics and supplies to NRHO. The transit profile from Earth to NRHO will be selected by the HLS provider.

The HLS integrated lander, logistics, and supplies may be launched in any configuration that safely delivers the vehicle, equipment, and supplies to NRHO. For instance, the HLS integrated lander may be launched using a distributed launch concept with separate elements launched individually or using a single integrated launch. Definition of specific launch concepts will be provided in the HLS provider’s ConOps document.

There are multiple trajectory options for delivery to the lunar vicinity. Ballistic lunar transfers, which may range up to 120 days or longer, reduce the delta-V required for insertion into NRHO. Fast transits can reach lunar orbit in a few days but require a higher delta-V insertion to the final orbit.

Ultimately, the trajectory selected must balance the design considerations for the HLS integrated lander with the mission requirements and must support the overall Artemis Mission Schedule as defined by the AES manifest. Definition of specific transit concepts will be provided in the HLS provider’s ConOps document.

4.2 INITIAL LUNAR ORBIT OPERATIONS

Initial Lunar Orbit Operations are defined as the phase of the mission during which the HLS

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Sustained Phase Human Landing System Program Concept of Operations June 2022 integrated lander is in NRHO, prior to the NRHO departure burn (NRD) that begins descent. The primary focus of this mission phase is to prepare for execution of a sortie or excursion prior to crewed descent to the surface. The amount of time that is required between Orion insertion into NRHO and crew departure to the surface is constrained by the end-to-end mission design and crew preparation activities and has a direct effect on mission availability. Therefore, the duration of initial lunar orbit operations will be constrained by the need to minimize the duration of this phase to enable maximum mission availability, and the need to have sufficient time to complete all lunar mission preparation activities.

Initial Lunar Orbit Operations consists of the following mission phases:

• Initial Loiter (ILTR)

• Initial Rendezvous, Proximity Operations, and Docking (IRPOD)

• Initial Docked Operations (IDOPS)

• HLS Undock and Backaway (HU&B)

4.2.1 INITIAL LOITER

The ILTR mission phase begins when the HLS integrated lander is inserted into NRHO, and it ends with the successful completion of the LOCR (both parts) when the integrated lander is docked to Gateway. The purpose of the LOCR is to ensure that the HLS integrated lander is fully assembled, loaded with consumables, and has completed a successful functional checkout and docking prior to crew launch onboard Orion via the SLS. For distributed launch architectures, the HLS integrated lander assembly will be completed prior to initiation of the LOCR and crew launch.

If significant launch slips occur, HLS provider may choose to undock from Gateway, loiter nearby, and then redock to Gateway prior to Orion arrival. If the HLS integrated lander undocks from Gateway during this phase, the mission will revert to ILTR mode of operation and flight rules. After LOCR (both parts), the HLS integrated lander is expected to be able to remain docked to Gateway or loiter undocked for up to 90 days to enable multiple crewed launch opportunities for a given mission. This duration includes the transit duration of Orion from Earth to the Moon.

During uncrewed operations, any HLS integrated lander element operating in the lunar vicinity will do so using ground-based command and control and/or a combination of automation and/or autonomy. The design must consider communications latency when Mission Control is in the operational command and control and/or decision loop in order to support planned and unplanned operation scenarios. This does not imply any requirements on ground-based control versus autonomous operations.

4.2.2 INITIAL RENDEZVOUS, PROXIMITY OPERATIONS, & DOCKING

(IRPOD)

Information on the RPOD sequences will be vehicle specific, and therefore provided in the HLS provider ConOps documents.

IRPOD will follow a standard RPOD sequence for the HLS integrated lander, serving as the chaser vehicle, and Gateway, serving as the target vehicle. IRPOD begins with a rendezvous phase, followed by proximity operations, soft capture, and hard capture. Proximity operations begin when the HLS integrated lander acquires the Gateway docking axis. For Gateway missions, Release Date: June 29, 2022 Page: 17 of 38

Sustained Phase Human Landing System Program Concept of Operations June 2022 the HLS integrated lander docking approach procedures will be governed by GP 10031- 01 Gateway to Visiting Vehicle Interface Requirement Document Annex 1: Human Landing System Requirements. This procedure will be a remote or autonomous docking operation of an uncrewed HLS integrated lander with an uncrewed Gateway for DRM-H-001, DRM-H-001b, and

DRM-H-002.

Using the Gateway visiting vehicle (VV) link, the Gateway transceiver operates in Point B mode and provides range and range rate data to the approaching HLS integrated lander transceiver operating in Point A. If the HLS provider implements a Point B transceiver, then the HLS integrated lander will generate its own solution.

The HLS integrated lander will provide a docking mechanism, either integrated with the vehicle or as part of an Active-Active Docking Adapter (AADA) which will be compatible with Gateway’s passive docking mechanism. In addition, for Gateway missions, the HLS integrated lander must have the ability to dock to Orion in a contingency case for in-flight crew rescue, which requires a docking mechanism compatible with Orion’s active docking mechanism. The HLS integrated lander may require an Active-Active Docking Adapter (AADA) or an androgynous docking adapter for docking to Gateway. This docking adapter may be disposed of at end of mission if a subsequent HLS mission does not require its use (this will be a NASA decision).

4.2.3 INITIAL UNCREWED DOCKED OPERATIONS

The primary objective of the Initial Uncrewed Docked Operations mission phase is the completion of LOCR (second part) and prepare for the crewed Orion launch. During this phase, the HLS integrated lander will send vehicle health and status data to the Gateway vehicle and ground personnel. This phase begins when the HLS integrated lander successfully docks to Gateway.

The phase ends either when the HLS integrated lander undocks and backs away from the Gateway, or when Orion successfully docks to Gateway, where it will remain for the crewed mission.

4.2.4 INITIAL CREWED DOCKED OPERATIONS (IDOPS)

The primary objective of the IDOPS mission phase is to enable the crew to depart for the lunar surface safely and efficiently. All HLS integrated lander operations that occur during this time should be designed to expedite the departure process.

The IDOPS phase will begin when Orion has successfully docked to the port where it will be located for the remainder of the crewed NRHO mission, the hatches are opened to connect the two environments, and the crew has successfully ingressed into Gateway. IDOPS ends at the HLS integrated lander undocking for descent to the lunar surface. Prior to the hatch opening, Orion will adjust its pressure to match shared atmospheric standards. If the Orion has excess gas, it may be used to assist in vestibule pressurization, but Gateway has the primary function.

Similarly, the HLS-Gateway vestibule will be pressurized by the Gateway. The Gateway Vehicle System Manager (VSM) will command Gateway modules to set the proper cabin conditions/set-point. The HLS integrated lander will be commanded by Gateway VSM or ground personnel to set the proper cabin conditions/set-point. If the Gateway pressure is higher than the HLS integrated lander maximum design pressure (MDP), the HLS integrated lander must provide its own automatic pressure relief system. Once pressure equalization has been achieved, the hatches can be opened, and the crew will begin the initial ingress into Gateway. The crew will

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Sustained Phase Human Landing System Program Concept of Operations June 2022 also open the hatch to the HLS integrated lander after sufficient local and remote checkouts have been performed. This includes the cabin atmosphere and constituents. Intermodule Ventilation (IMV) ducting will be installed to establish the shared environment. HLS integrated lander will provide the IMV ducting hardware that will be installed across the hatch interface (i.e., a drag-through duct) and Gateway will provide the fan/circulation through the ducting.

When docked to Gateway, Orion will require a tail-to-Sun orientation to maintain proper thermal and power profiles and this, in addition to port assignment, will determine the attitude of the integrated vehicle stack (Gateway, HLS, and Orion) during IDOPS. When the HLS integrated lander is docked to Gateway, if the HLS integrated lander mass is under 45 metric tons, Gateway will provide stack control. If the HLS integrated lander mass is above 45 metric tons, the HLS integrated lander will provide attitude control and orbital maintenance; Gateway will be responsible for position determination and will send an impulse request to the HLS integrated lander which will then perform the appropriate burn or maneuver needed. Gateway will provide atmosphere control during open hatch operations including pressure control and air revitalization.

Stack control constraints are covered in GP 10031-01 Gateway to Visiting Vehicle Interface Requirements Document Annex 1: Human Landing System Integrated Lander Requirements.

The IDOPS phase may require multiple crew days, and thus the crew will require exercise, nutrition, and sleep during this mission phase. Exercise, nutrition, and waste management system functions will be provided by Gateway during IDOPS.

4.2.4.1 SHARED HABITABLE ENVIRONMENT

When the HLS integrated lander is docked directly to Gateway in an open-hatch configuration, Gateway will provide air revitalization and pressure control (consumables, air scrubbing) for the Gateway and HLS integrated lander habitable volumes. However, the HLS integrated lander is still responsible for performing air circulation within the HLS integrated lander volume. All Environmental Control and Life Support System (ECLSS) functionality between Gateway and HLS integrated lander is covered in the GP 10031-01 Gateway to Visiting Vehicle Interface Requirement Document Annex 1: Human Landing System Integrated Lander Requirements. A joint strategy between HLS, Gateway, and Orion programs will be developed and implemented to ensure low lunar dust levels in the combined habitable volume. Exercise and Waste Management System functions will be provided by Gateway during IDOPS.

4.2.4.2 SORTIE AND EXCURSION DEPARTURE PREPARATIONS

Before the crew can depart the NRHO for the lunar surface, a series of preparation activities must occur. These activities include, but are not limited to, those described in the following sections.

4.2.4.3 INITIAL INGRESS

Gateway initial ingress will be the first time the crew will enter the Gateway after either Gateway’s initial deployment or after a long uninhabited period. The initial ingress for Gateway will be conducted according to preestablished protocols that ensure the safety of the crew and will allow the crew to perform a checkout prior to proceeding to other operations. The checkout and procedures will follow GP-10027 Gateway ConOps. For some missions, ingress into a co-manifested payload located between Orion and Gateway may have to occur prior to ingress into

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Sustained Phase Human Landing System Program Concept of Operations June 2022 the pre-deployed portions of Gateway.

HLS integrated lander initial ingress will be the first time the crew will enter the HLS integrated lander after successful completion of Orion’s RPOD with Gateway. The initial ingress into the HLS integrated lander will be conducted according to preestablished protocols that ensure the safety of the crew and will allow the crew to perform a checkout prior to proceeding to other operations.

4.2.4.4 SUIT PREPARATION AND CHECKOUT

An important part of the mission preparation process will be ensuring that suits are ready for a sortie or excursion, and any suit to be used will undergo a thorough checkout and preparation process. Suit assembly, fit check, and suit checkout will occur on the HLS integrated lander prior to departure. All vehicle interfaces required for suit checkout will need to be accessible and active during this portion of the IDOPS. Once checkouts are completed, the EVA suits will need to be stowed for descent to the surface, and IVA suits will need to be ready for use during the descent and ascent phases.

4.2.4.5 HLS LOGISTICS AND SUPPLY PREPARATION

The HLS integrated lander may require crew activity to transition between on-orbit mode and surface mission mode. The scope of this activity will be unique to each vehicle architecture. This may include activities such as preliminary vehicle checkout (separate from the final pre-departure checkout) activation of cabin and crew support equipment, or cabin reconfiguration. All such activities must be completed prior to vehicle departure, and the total time required for such activities should be minimized to help enable overall Artemis mission availability.

Depending on vehicle design, some items may need to be reconfigured or relocated from their launch configuration to an IDOPS and/or the sortie/excursion configuration prior to departure.

Some utilization equipment may be launched on DSL and will need to be transferred to the HLS integrated lander. To keep track of this inventory, a NASA and/or provider Inventory Management System will be utilized. The use of this system will help ensure that inventory will remain in the appropriate vehicle or be transferred to the appropriate vehicle.

The EVA suits to be used on the mission may be launched hard-mounted to the HLS integrated lander or in government-provided launch enclosures (soft-stowed). The launch enclosures may be stowed in the Gateway prior to departure for the lunar surface.

A small amount of individual crew supplies might be launched with the crew on Orion and then transferred to the HLS integrated lander, such as the individual crew HLS Medical Accessories Kit (HMAK).

4.2.4.6 FINAL INGRESS AND DEPARTURE CHECKOUT

The specific sequence of final ingress and departure checkout activities will depend on the architecture and design provided by each HLS provider and will be worked into the final ingress timeline and procedures. The HLS integrated lander and the Gateway will be prepared for undock by removing hatch impediments, such as the IMV, and hardware located in the vestibule. For all architectures, prior to ending IDOPS and initiating undock and backaway, the crew must be fully suited in their IVA suits that will be used for lunar descent and landing, and the vehicle must pass

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Sustained Phase Human Landing System Program Concept of Operations June 2022 all checkouts as required by flight rules.

Once the HLS integrated lander lunar surface crew are fully suited in IVA suits and in the HLS integrated lander with the hatch closed, a final system checkout will be performed in conjunction with Mission Control to ensure that the HLS integrated lander is ready for departure and initiation of a sortie or excursion. The crew in IVA suits must have their umbilical connections fully mated and checked out prior to departure, as required. Crew not participating in the lunar sortie or excursion will remain aboard the Gateway.

Lunar saturation operations at reduced pressure environment will be used to reduce prebreathe duration prior to EVA. The crew may have to begin their desaturation operations prior to departing for the lunar surface to achieve the shortest prebreathe duration. If a certain assumed desaturation time is not achieved prior to the first EVA, then prebreathe duration for the first EVA will be somewhat longer.

4.2.5 INITIAL UNDOCK & BACKAWAY (IU&B)

IU&B begins after successful departure checkout and ends at NRHO departure burn. Once final checkout has been completed, an Authority to Proceed (ATP) decision to begin IU&B, based on mission criteria to be established in flight rules, will be made by Mission Control. Upon a “Go” call for the HLS integrated lander departure, initial separation and backaway will be performed. The crew onboard the HLS Integrated lander will be suited in pressure suits during this phase through completion of the HLS integrated lander’s NRHO departure burn using restraints as required to operate the HLS integrated lander.

The integrated Gateway and HLS integrated lander stack will maneuver to the specified undock attitude, Gateway will inhibit reaction control system (RCS) firings while maintaining attitude control, and the S-Band Proximity Communications Link (for Orion) or the S-band Gateway to Visiting Vehicle (VV) Link (for Gateway) will be re-established.

This separation will occur at the AADA and HLS integrated lander interface or the direct HLS integrated lander interface with Gateway. After the separation, the Gateway will re-establish attitude control when the HLS integrated lander reaches a distance that provides adequate structural separation and limits HLS integrated lander plume-impingement loads on the Gateway.

A series of small backaway burns to increase the separation between the two vehicles to a safe distance will then be performed.

4.3 DESCENT

The descent segment of the mission begins with the HLS integrated lander NRD and ends with the HLS integrated lander safely touching down on the lunar surface. The descent phase consists of NRD, descent transit to LLO, descent phasing orbit loiter, and final descent. The HLS provider is responsible for determining the descent profile specific to their HLS integrated lander. DRM-H- 001b may require the HLS integrated lander to start descent operations earlier in the NRHO to get the proper alignment for the descent trajectory. Regardless of profile, the crew onboard the HLS integrated lander will remain suited until NRD is complete and will don suits again for the final descent. Other suited periods may be required during descent based on the energy and risk level of the specific dynamic event. Crew are not required to nominally don or doff suits simultaneously, but the capability for unassisted simultaneous don/doff is required for contingency scenarios where crew need protection from a compromised cabin.

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Sustained Phase Human Landing System Program Concept of Operations June 2022

4.3.1 NRHO DEPARTURE BURN (NRD)

The HLS integrated lander will perform a propulsive maneuver(s) (the NRD) to initiate departure of NRHO at the end of backaway. The timing and magnitude of this maneuver will depend on the architecture provided by each HLS provider and the intended surface destination.

4.3.2 DESCENT TRANSIT

Transits from the NRHO to either a phasing orbit or the initiation of the final descent trajectory vary in both duration and energy required. Transits between NRHO and a phasing orbit or final descent for all variations of the surface mission are expected to be at least 12 hours in duration.

The length of this transit means that the crew will likely require a rest period during the transit to have adequate performance capability to execute final descent. Nominally, the transit rest period would include nutrition, sleep, and biological waste elimination, and therefore vehicle intervention from the crew during this period should be minimal.

4.3.3 DESCENT PHASING ORBIT LOITER

A loiter in LLO may be needed for crew preparation for descent and/or navigation state updates to reduce error after the descent lunar orbit insertion (DLOI) burn. At this time the crew is expected to don IVA suits and perform final vehicle checkouts prior to initiating final descent. The provider may choose both the profile of and time spent in a phasing orbit based on the needs of their specific HLS integrated lander architecture. One possible solution to reach non-polar landing sites is to loiter longer in LLO. This may require additional delta-V for station keeping and will be provider design-specific.

4.3.4 FINAL DESCENT

For final descent, the crew will wear an IVA suit using restraints as required to operate the HLS integrated lander. The descent from the phasing orbit to the lunar surface will typically consist of four distinct sub-phases. A descent orbit insertion (DOI) burn will place the HLS integrated lander in an orbit with a perilune sufficiently low to perform powered descent initiation (PDI). The PDI and braking phase will slow the HLS integrated lander into a surface-intercepting trajectory and arrest the HLS integrated lander to a sufficiently low altitude to begin the approach phase. The approach segment typically consists of a pitch maneuver to allow for crew viewing of the landing site. The terminal descent and touchdown segment consists of the final vertical descent to the surface, achieving the desired velocity/attitude state for touchdown. The duration and profile of these phases will vary with descent trajectory design. The HLS integrated lander will perform precision navigation to achieve a safe landing within a 50-meter radius of the target site. Details of hazard detection operations will be vehicle specific.

The HLS integrated lander will have the capability to land automatically without crew on board.

For crewed landings that capability…