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HLS Sustaining Phase RF Communications Concept of Operations July 2022

HLS-CONOP-008

REVISION A

National Aeronautics and Space Administration RELEASE DATE: JULY 07, 2022

HUMAN LANDING SYSTEM (HLS) SUSTAINING

PHASE RADIO FREQUENCY (RF) COMMUNICATIONS

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-008

Release Date: July 07, 2022 Page: 2 of 74

Title: HLS Sustaining Phase RF Communications Concept Of Operations

REVISION AND HISTORY PAGE

Revision No.

Change No.

Description Release

Date

- HLS-C0216 Initial Release (Reference HCB.01.12.2022) 02/03/22

- HLS-MD-0006 Updated HLS-IRD-004 to reflect HLS-IRD-004-01 Sustaining Volume numbering.

02/22/22

A - Revision A (Reference OSB HCB.06.28.2022)

The terminology updates add the “Integrated Lander” wording consistent with the other HLS SLD documents. The definitions/glossary updates add definitions for the words used in the HLS-CONOP-008 from the SOW, HLS-CONOP- 006, or HLS-RQMT-006 in that order as appropriate. Added wording to the description of the HLS direct with Earth frequency band options to include S-band in section 4.3 HLS Frequency Selection and Spectrum Planning, bullet 1. Direct-with-Earth bi-directional Communications.

07/07/22

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TABLE OF CONTENTS

SECTION PAGE

1.0 INTRODUCTION

1.1 PURPOSE

1.2 SCOPE

1.3 CHANGE AUTHORITY/RESPONSIBILITY

1.4 APPLICABLE DOCUMENTS

1.5 REFERENCE DOCUMENTS

2.0 SUMMARY

2.1 HLS PROGRAM PHASES

3.0 DESIGN REFERENCE MISSIONS

4.0 COMMUNICATIONS SYSTEMS OVERVIEW

4.1 COMMUNICATIONS ARCHITECTURE OVERVIEW

4.2 COMMUNICATIONS PRIORITY SCHEME

Autonomous Operation and Communication Outages

4.3 HLS FREQUENCY SELECTION AND SPECTRUM PLANNING

ICSIS Communications System Interoperability Standards Lunar Spectrum / Frequency Selection

4.4 COMMUNICATIONS PRIVACY

Voice Channel Segregation, Desegregation, and Audio Loops

4.5 MOTION VIDEO IMAGERY DRIVER FOR RF LINK DATA RATES

4.6 VARIOUS TYPES OF DATA RATES USED HEREIN

4.7 TRANSPONDER POINT A VS POINT B FUNCTIONALITY

5.0 GROUND STATION USE

6.0 USE CASES

6.1 GATEWAY-BASED MISSION

Gateway Capabilities

6.2 CONTINGENCY DOCKING WITH ORION

Orion Capabilities Contingency Docking Specific Constraints

7.0 SUSTAINING PHASE LUNAR LANDING SITE SELECTION

8.0 LUNAR SURFACE MULTIPATH

8.1 BASIC MULTIPATH EFFECTS ON PARABOLIC DISH ANTENNA DIRECTIVITY

8.2 COMPARISON OF 6” DISH IN FREE SPACE AND ON LUNAR SOUTH POLE

8.3 LUNAR MULTIPATH DEGRADATION & MITIGATION

9.0 GOVERNMENT FURNISHED PROPERTY (GFP) COMPATIBILITY

10.0 WI-FI INFORMATION

11.0 DELAY TOLERANT NETWORKING (DTN)

12.0 INFORMATION SECURITY / COMMUNICATIONS SECURITY

13.0 SUSTAINING-PHASE MISSION

13.1 MISSION SEGMENTS

HLS Pre-Launch Activities and Mission Overview Transfer Element Launch and Transit Descent Element Launch and Transit Ascent Element Launch and Transit Gateway as Crew Staging Vehicle DRM Contingency Docking with Orion

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APPENDIX

APPENDIX A ACRONYMS AND ABBREVIATIONS AND GLOSSARY OF TERMS

APPENDIX B OPEN WORK

APPENDIX C RF COMM REFERENCE INFORMATION

TABLE

Table 1-1 Applicable Documents Table 1-2 Reference Documents Table 3-1 Design Reference Mission Overview Table 4-1 Recommended Frequency Bands for Communications in the Lunar Region

FIGURE

Figure 3-1 (Notional) Sustaining Phase Mission Architectures Figure 3-2 Generic sustained phase mission architecture. The three-element architecture is for reference only and represents one possible approach Figure 4-1 Communication Architecture Overview for the Sustaining Phase DRMs Figure 4-2 Illustration of various Data Rate and Symbol Rate Definitions used within Communication Systems Figure 6-1 Gateway RF Comm Configuration/Capability Figure 6-2 Gateway to HLS LS RF Link Interface Figure 6-3 Gateway to HLS VV RF Link Interface Figure 6-4 Orion to HLS Proximity Operations RF Interface Plane Figure 7-1 Lunar Landing Site Map Analysis (Example Only) Figure 7-2 Lunar Landing Site Location Analysis (Example Only) Figure 8-1 Radio frequency Multipath Degradation Overview Figure 8-2 Multipath Effect on 6” Dish Antenna Pointed horizontally in free space Figure 8-3 Multipath Effect on 6” Dish Antenna Pointed horizontally and 2m above Lunar Surface Figure 8-4 Multipath effects on 6” Parabolic Dish Antenna Pattern at X-Band – Lunar Pole (Horizontally-Pointed Dish). 1.6m above Smooth Lunar Surface Figure 13-1 HLS Sustaining Phase mission – Gateway as CSV Figure 13-2 HLS Pre-Launch Figure 13-3 Transfer Element Launch and Transit Figure 13-4 Descent Element Launch and Transit Figure 13-5 Ascent Element Launch and Transit Figure 13-6 Simultaneous Transit Figure 13-7 Transfer Vehicle Element (TVE) Arrival at NRHO Figure 13-8 Descent Element (DE) Arrival at NRHO, Docking with TE Figure 13-9 Ascent Element (AE) Arrival at NRHO, Docking with HLS Stack Figure 13-10 HLS Docks with Gateway Figure 13-11 SLS/Orion Launch and Transit, arrival in NRHO Figure 13-12 Crew Arrival, Transfer and Checkout Figure 13-13 HLS Separation from Gateway – Departing for the Moon Figure 13-14 NRHO Departure – HLS Heading to the Moon

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Figure 13-15 Low Lunar Orbit Arrival – HLS Heading to the Moon Figure 13-16 Descent, TE Disposal, and Lunar Approach Figure 13-17 HLS Approach to Lunar Touchdown Figure 13-18 HLS Surface Operations Figure 13-19 HLS Ascent Element Lunar Liftoff Figure 13-20 LLO Circularization to Departure Burn & Transfer Coast Figure 13-21 NRHO Insertion Burn Figure 13-22 Post-Mission Operations, Crew Return, and HLS Disposal Figure 13-23 Contingency Docking with Orion (MPCV) – RPOD Figure 13-24 Contingency Docking with Orion (MPCV) – Undocking and Crew Return

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1.0 INTRODUCTION

The Sustaining Phase Human Landing System (HLS) Radio Frequency (RF) Communications Concept of Operations (ConOps) describes the general communications systems concepts that will enable a sustained human lunar presence. The HLS Integrated Lander is a vehicular system that first transports lunar surface exploration logistics and mission support equipment from Earth to near-rectilinear halo orbit (NRHO), then transports crew members from a Crew Staging Vehicle (CSV) in a NRHO to the lunar surface, enables the crew to perform multiple extravehicular activities (EVAs) and access surface assets, and then safely returns the crew to the CSV for return to Earth (RTE). In addition to returning the crew to NRHO, the HLS Integrated Lander also returns lunar samples and other equipment to NRHO to enable sample RTE for scientific study.

While the HLS Integrated Lander will have the capability to communicate concurrently with ground support teams on Earth (Mission Systems), the Crew Staging Vehicle (Gateway) in a NRHO, EVA Spacesuits, and Lunar Surface Assets, when present, the specific communication needs will vary by Artemis mission segment (e.g., Ascent, RPOD, Docked Operations), and by the availability of communications assets. During all crewed mission phases, continuous communications between Earth, Gateway, Spacesuits, and Lunar Surface Assets is required. Therefore, the HLS Provider(s) must provide sufficient Ground Station and/or Relay satellite coverage such that no unplanned communications outages occur during crewed HLS operations.

1.1 PURPOSE

The primary purpose of this document is to define the RF communications concept of operations for the sustaining phase Human Landing System portion of the NASA Artemis effort to establish a sustained human presence on the Moon. This document captures the top level RF communications systems concepts for how the HLS sustaining phase Provider(s) will be expected to specify and use the HLS RF Communications and Tracking Systems in the broader NASA effort.

The HLS sustaining phase Design Reference Missions (DRMs) are included to describe the current understanding of the bounding mission types to be used in the sustaining phase of lunar exploration. The DRMs establish an operational context, descriptions of situations that will be encountered during currently available mission concepts, and top-level operational sequences with a focus on sequences involving interaction between HLS Integrated Lander and non-HLS Integrated Lander communications systems and NASA crew. The DRMs are also intended to capture communication capabilities, rather than a manifest or specific mission plan.

The three-element HLS Integrated Lander design concept provided herein is the NASA Government Reference Concept and is one of many possibilities. This design concept is provided solely as a reference and is not intended to represent any of the HLS Provider(s) design solutions.

1.2 SCOPE

This document defines the general RF communications concepts for the sustaining phase of the return to the Moon and is based on the Government reference design. While usage of RF communications is the focus of this ConOps, HLS Provider(s) are not precluded from proposing optical communications for links that are not interface-limited to RF communications.

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NASA has divided the Artemis campaign into two phases—an initial phase and a sustaining phase. This document covers the early portions of the Sustaining Phase missions that are covered by the HLS sustaining period of performance. This document is limited to the timeframe during which the HLS Integrated Lander interacts with the Orion, Gateway, NASA crew, Exploration Extra-Vehicular Activities (xEVA) system, NASA Mission Systems, Lunar Relay System, and/or pre-positioned lunar assets (sustaining habitations, pressurized rovers, and/or Lunar Terrain Vehicles). The DRMs/architecture concepts presented within this document are for reference purposes only and are not intended to represent any of the HLS Provider(s) design solutions. The specific RF communication systems architecture/ implementation of this RF Communications ConOps will be housed in future documentation.

1.3 CHANGE AUTHORITY/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 1-1 Applicable Documents

Document Number

Document Title

HLS-CONOP-006 Sustained Phase HLS Program Concept of Operations

HLS-PLAN-004 HLS Configuration and Data Management Plan

HLS-IRD-004-01 Human Landing System (HLS) Program Integrated Lander to Mission Systems (MS) Interface Requirements Document (IRD) - Sustained Phase

HLS-IRD-008 Human Landing System (HLS) Program

Integrated Lander to Lunar Surface Assets (LSA)

Interface Requirements Document (IRD) – Sustained Phase

GP-10031-01 Gateway to HLS Visiting Vehicle Interface Requirements Document

GP 10045-01 Gateway to Visiting Vehicle RF IRD - HLS Annex

GP 10046-01 Gateway to Lunar Systems RF IRD, HLS Annex

EVA-EXP-0067 xEVA Interface Requirements Control Document

HLS-RQMT-006 Human Landing System (HLS) Program Integrated Lander Requirements Document – Sustained Phase

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Table 1-1 Applicable Documents

Document Number

Document Title

HEOMD-007 HEOMD SCOPE

HEOMD-003-02 International Communications System Interoperability Standards

NASA-STD-1006 Space System Protection Standard

NPR 2810.1 Security of Information Technology

1.5 REFERENCE DOCUMENTS

The following documents contain supplemental information to guide the user in the application of this document.

Table 1-2 Reference Documents

Document Number

Document Title

AES-50007 AES Concept of Operations

GP-10027 Gateway Concept of Operations

EVA-EXP-0042 EVA OFFICE EXPLORATION EVA SYSTEM CONCEPT

OF OPERATIONS

HLS-PLAN-016 HLS Technical Management Plan

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

SPD-5 Space Policy Directive - 5

SFCG 32-2R3 Communication and Positioning, Navigation, and Timing Frequency Allocations and Sharing in the Lunar Region (December 2021)

2.0 SUMMARY

The Human Landing System Integrated Lander is a vehicular system that enables the transport of logistics and mission support equipment from Earth to an Earth-Moon L2 NRHO oriented over the southern pole with a 9:2 synodic resonance with the Moon’s orbit. The HLS Integrated Lander then transports crew members and cargo from the CSV in a NRHO to the lunar surface, provides crew habitation and EVA support on the surface, and then safely returns crew and cargo to the CSV for return to Earth. The HLS Sustaining Phase missions will require the HLS Integrated Lander to dock to Gateway, land a complement of up to four crew on the lunar surface for either a sortie mission or excursion with transfer to pre-emplace habitable lunar assets, operate for extended durations near the lunar south pole, and support eight-hour EVAs to help further the advancement of surface goals. The sustaining phase missions are characterized by two primary

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DRMs, and a non-polar DRM variant, which are described in greater detail in the following DRM section.

This document defines the general RF communication capabilities and concepts needed to support the HLS Sustaining Phase Design Reference Missions defined in the HLS-CONOP-006, Sustained Phase HLS Program ConOps.

2.1 HLS PROGRAM PHASES

The Artemis campaign is divided into two major phases - an initial and a sustaining. While the scope of this document is the sustaining phase missions, a description of the initial phase is provided for context and background. Summaries of both phases are included below.

HLS Initial Phase Mission Summary:

• Lunar South Pole Mission(s) (within 6˚ of pole)

• No pre-emplaced Assets Required

• Two (2) crew members inside HLS Integrated Lander

• Option to use Orion or Gateway as the Crew Staging Vehicle.

• 6.5-Earth-day Surface-Stay duration

HLS Sustaining Phase Mission Summary:

• Lunar South Pole Missions; however, goal capability for sortie missions to non-polar locations

• Lunar surface assets, including Sustaining Habitations, Pressurized Rover, & Lunar Terrain Vehicles

• Up to four (4) crew members inside HLS Integrated Lander

• Use of Gateway as the Crew Staging Vehicle (CSV) for primary DRMs and DRM variants.

• Longer Surface-Stay Durations

Note: The sustaining mission phase does not require that HLS Integrated Lander elements be re-used; however, the sustaining mission phase may have re-usable elements. Some DRMs of the sustaining mission phase will rely on pre-emplaced assets to carry out lunar missions.

3.0 DESIGN REFERENCE MISSIONS

The DRMs in this section are intended to serve as the bounding mission cases that drive HLS Integrated Lander system and mission design and are to be used in the sustaining phase period of performance of the Artemis lunar exploration campaign. DRM variants are intended to serve as representation of how the capability established by the primary DRM may be used in different operational contexts and external environments than would be seen during a mission represented by the primary DRM. The sustaining phase DRMs are described in greater detail within HLS-

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CONOP-006. Table 3-1 provides an overview of the sustaining phase DRMs with Gateway as the Crew Staging Vehicle (CSV).

Table 3-1 Design Reference Mission Overview

Primary DRMs DRM Variant

DRM-001

Polar Sortie

DRM-002

Polar Extended

Excursion

DRM-001b Non-Polar Sortie

Crew Staging Vehicle Gateway Gateway Gateway

Landed Crew Size 2 4 2

Surface Stay (days) 6 33 2(threshold) – 6 (goal)

Landing Location South Pole Artemis Base Camp Non-Polar

Darkness (hr) 0-40 120-192 0-40

Surface Habitation HLS Integrated

Lander HLS and Artemis

Base Camp Elements HLS Integrated Lander

Number of HLS EVAs 5 (4 planned, 1 unplanned)

2 (1 full round- trip transfer by EVA, 1 unplanned)

2 (threshold) 5 (goal)

Figure 3-1 shows a notional Sustaining Phase mission with three different architecture types.

Figure 3-1 (Notional) Sustaining Phase Mission Architectures

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For this RF ConOps, a three-element (i.e. Transfer Element (TE), Descent Element (DE), and Ascent Element (AE)) NASA reference architecture is assumed, as shown in Figure 3-2, and this architecture is one of many possible HLS Integrated Lander design solutions and is not intended to drive implementation.

For each DRM, a NRHO lunar staging orbit (LSO) is assumed for the lunar surface mission. In order to protect for the inability of the HLS Integrated Lander to dock with the Gateway upon return and transfer the crew to Orion through Gateway, the HLS Integrated Lander must have the ability to dock to Orion in a contingency case, 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 (NASA decision).

Figure 3-2 Generic sustained phase mission architecture. The three-element architecture is for reference only and represents one possible approach

For DRM-001, DRM-001b, and DRM-002, the Gateway is utilized as the Crew Staging Vehicle;

therefore, HLS Integrated Lander needs the following capabilities:

1. The capability to communicate Direct-with-Earth (DWE) and Relayed-with-Earth (Lunar Relay).

a. Note 1: HLS Integrated Lander may rely upon NASA communication relays or relays delivered by non-NASA entities, including commercial providers.

b. Note 2: The capability to communicate with the NASA SCaN-provided orbital relay or a commercial Relay will allow all Mission Objectives to be met when operating from a non-DWE landing site, and augment comm when operating from a DWE

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2. The capability to communicate directly with Gateway (Gateway Visiting Vehicle Link) when within 400 km.

3. The capability to exchange crew, payload, power, data, commands, and atmosphere with Gateway when attached.

4. The capability to communicate with Gateway when outside of 400 km via Gateway Lunar Systems Link(s) (provides non-DWE link to Earth as well as provides required HLS crew to Gateway crew communications).

a. Note that designing for compatibility with the Gateway lunar link(s) is expected to also provide compatibility with the NASA-provided Lunar Orbiting Communication Relay(s). Of course, this does not preclude the use of commercially-provided communications relay assets in addition to the Gateway and NASA relay.

5. The capability to communicate with surface assets (i.e., EVA Suits, Lunar Terrain Vehicle (LTV), Pressurized Rover (PR)) either directly or indirectly (utilizing surface repeaters/relays).

6. The capability to communicate directly with Orion when within 800 km (applicable for the contingency docking scenario).

7. The capability to communicate with Orion when outside of 800 km via an indirect communication path such as DWE, Relayed-with-Earth (RWE), and/or Gateway (applicable for the contingency docking scenario).

4.0 COMMUNICATIONS SYSTEMS OVERVIEW

4.1 COMMUNICATIONS ARCHITECTURE OVERVIEW

The diagrams in Figure 4-1 below display an overview of the communication architecture for the sustaining phase DRMs.

HLS Gateway

Cruise Phase (HLS en route to Gateway NRHO)

For the HLS-with-Earth Link(s), the HLS Provider is free to choose the Ground Station(s), number of links, and the characteristics of each link. Note that 2-way Encryption is mandatory on all links, as well as IP Encapsulation.

Although only one link is illustrated here, multiple links may be necessary.

Although not shown in the pictographs below, Gateway nominally has two Radio Frequency Communication links with Earth:

(a ) X-Band Full-Duplex (Goal: 2 Mbps downlink, 5 Mbps uplink) (b ) Ka-Band Full-Duplex (Goal: 100 Mbps downlink, 20 Mbps uplink)

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Ka Gateway

HLS

Initial HLS Rendezvous and Docking Gateway Phase: Visiting Vehicle Link / Docking (< 400 km)

Gateway s S-Band Visiting Vehicle Link is a point-to-point link that communicates with HLS during Rendezvous, Proximity Operations & Docking to exchange data and commands, and provide for radiometric ranging. Once it arrives within Visiting Vehicle range (< 400 km) of Gateway, HLS must maintain concurrent communications with both Gateway and with Earth. Relay

X -B an d w it h Ea rt h

K a-

B an d w it h

Ea rt h

HLS

Gateway

Optional Wi-Fi Link

Hardline Ethernet (via Docking Port)

HLS Docked to Gateway, and Orion Arrival Phase

Once HLS is docked to Gateway, communications will occur over hard line Ethernet, and then the S-Band Visiting Vehicle Link can be deactivated if desired. Gateway and HLS are both free to continue separate use of their Direct-with-Earth Links, and the Wi-Fi Link will remain an optio n. At least 4-5 days after HLS/ Gateway docking, Orion arrives with a Crew of four and docks to Gateway. Relay

Command, Data, Voice, Video, & Tracking (Range & Range-Rate)

2-Way Relayed-with-Earth Comm Link(s)

Note: This figure displays DRM-001 or DRM- 001b with a landed crew size of two. For DRM- 002 (Polar Extended Excursion), the landed crew size is four (not shown).

Gateway X-Band

Gateway Ka-Band

Gateway

Lunar Descent/Ascent Phases (> 400 km) HLS

*During Descent/Ascent Phases (and all lunar surface ops), HLS must maintain continuous communication with Earth, Lunar Orbiting Crew, and EVA Mobility Systems (EVA Suits, LTV, PR). The comm. with Lunar Orbiting Crew must not rely upon the HLS/Earth link, and does not have to be direct. Gateway s Lunar Systems Link(s) are designed for this purpose, and have different frequencies and signal schemes than the S-Band Visiting Vehicle Link.

Relay

**This figure d isplays DRM-001 or DRM-001b with a landed crew size of two.

For DRM-002 (Polar Extended Excursion), the landed crew size is four (not shown).

X-Band

Ka-Band

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Figure 4-1 Communication Architecture Overview for the Sustaining Phase DRMs

HLS

Lunar Surface Operations Phase

*Please see note, above, regarding continuous comm with Earth and the Lunar Orb iting Crew.

**This link represents the NASA des ire to live-stream video of HLS Ascent back to earth, as seen from the lunar surface, similar to what Apollo Program did. It does not have to be direct -to-Earth (it could use a Comm Relay, or even HLS as a Relay) and it will only be for a very short time. The system may need the capability to send camera-control commands, or command script, from Earth to control Pan, Tilt, Zoom.

***NASA desires to have at least 4, and possibly 6 or 8 live video streams sent back to Earth during Lunar Surface EVAs. Two 4 Mbit/Sec Helmet Cameras provide real-time individual situational awareness (SA), 4K/UHD Tripod or HLS -Mounted Cams provide overa ll SA, and handheld cameras may stream video or send photos for science purposes.

Gateway

X Ka

Helmet Cam 1080p30 FHD H.265 4 Mbps

Helmet Cam 1080p30 FHD H.265 4 Mbps

Hand Cam 1080p30 UHD H.265 5 Mbps

4K Tripod Cam 2160p30 UHD

H.265 10 Mbps

Wi-Fi Links

HLS Lander

9 Mbps

WAP

Portable 5 GHz 802.11ac

Wi-Fi Access Point (WAP)

Mobi le Ad-Hoc NET work

(MANET)

10 Mbps

18 Mbps

28 Mbps

5 GHz 802.11ac Wi-Fi ad-hoc mesh network

4K HLS-Mount Cam

PTZ Rem ote Control

Relay

Command, Data, Voice, Video, & Tracking (Range & Range-Rate)

2-Way Relayed-with-Earth Comm Link(s)

Note: This figure displays DRM-001 or DRM- 001b with a landed crew size of two. For DRM- 002 (Polar Extended Excursion), the landed crew size is four (not shown).

Gateway

HLS

2-Way Direct-with-Earth Comm Link(s) Command, Voice (when crewed), Data, Video, & Tracking (Range & Range-Rate)

Return HLS Rendezvous and Docking Gateway Phase: Visiting Vehicle Link / Docking (< 400 km)

Gateway

HLS

2-Way Direct-with-Earth Comm Link(s) Command, Voice (when crewed), Data, Video, & Tracking (Range & Range-Rate)

Return HLS Rendezvous and Docking Gateway Phase: Visiting Vehicle Link / Docking (< 400 km)

Gateway s S-Band Visiting Vehicle Link is a point-to-point link that communicates with HLS during Rendezvous, Proximity Operations & Docking to exchange data and commands, and provide for radiometric ranging. Once it arrives within Visiting Vehicle range (< 400 km) of Gateway, HLS must maintain concurrent communications with both Gateway and with Earth. RelayRelay

**This figure displays DRM-001 or DRM- 001b with a landed crew size of two. For DRM-002 (Po lar Extended Excursion), the landed crew size is four (not shown).

Gateway

HLS Disposal Phase (> 400 km)

HLS will remain docked with Gateway until after Orion undocks and departs for Earth. HLS may then undock for disposal or reuse preparations. As element reuse is not a requirement for the sustaining phase of the HLS Pro vider(s) may choose to begin their uncrewed HLS op erations (refu el, orient to minimize boil o ff, etc.) or if they ch oose to dispose element/eq uip ment/was te of the HLS after the mission, thes e items will be dis posed in location s that will pose no harm to or in terfere with NASA lun ar orbit missions or vehicles or a ssets of his torical value an d comply with applica ble planetary protectio n regulations to ensu re a safe dispos al of the veh icle.

Relay *During the Disposal Phase, the HLS Provider is free to choose the number and type of links (Direct-with-Earth and/or Relay, including Gateway) needed to support the remaining uncrewed phase of the mission.

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4.2 COMMUNICATIONS PRIORITY SCHEME

In all HLS RF Communications Systems, the two-way priority scheme is defined as follows:

• Highest priority will be given to given to Crew Voice Communications.

• Second Highest-Priority will be Emergency, Caution & Warning (Alert) Notifications and EVA suit health and status telemetry data.

• Third Highest-Priority will be given to command data, HLS health and status telemetry data, video, and file transfers.

At a minimum, the Communications System(s) need the ability to communicate by voice conversation (10 kilobits/sec per voice channel). Alert notifications will be added if the data rates allow, and these may be prioritized based on their severity.

The current HLS ConOps is to have the capability to maintain dissimilar communication paths with Earth, Direct-with-Earth and/or Relayed-with-Earth links, and concurrently with Gateway, during all mission phases for command uplink, ranging, data, voice (when crewed), video, and status to mitigate unforeseen communications outages. For planned outages, where either the DWE and/or RWE links are not available, the Gateway can also be used as a relay with Earth.

During all crewed mission phases, continuous communications is required; thus, the HLS Provider(s) must provide sufficient ground station and/or relay satellite coverage such that no unplanned communications outages occur during crewed HLS operations. With the HLS Integrated Lander on the lunar surface, the range to Gateway (in NRHO) could be up to 70,000 km and, during descent and ascent, it can be expected to have roughly a maximum of 22,000 km distance to Gateway (in NRHO) for normal operations. Therefore, the Gateway Lunar Systems Links are designed to communicate at distances up to 70,000 km and should thus successfully close at all expected distances.

For HLS Integrated Lander/Gateway crosslink communications (at all anticipated lunar distances), higher-rate communication is possible, and the actual communication link(s) implementations details would be up to the HLS Provider(s). During surface EVA activities, the HLS Integrated Lander uses a UHF EVA Link to support astronaut voice and biomedical data links and uses an external Wi-Fi link to support high-rate communications for peripheral devices (such as Video Cameras or Science Instruments) for EVA activity.

For the contingency docking with Orion case, HLS Integrated Lander will maintain continuous communications with Orion when within 800 km (Proximity Operations) as well as a continuous Direct-with-Earth and/or Relayed-with-Earth link (Note: Gateway could also be used as a relay with Earth.).

Autonomous Operation and Communication Outages

Per HLS-CONOP-006, any uncrewed HLS Integrated Lander element operating in the lunar vicinity will do so using ground-based command and control (direct or via relay asset) and/or a combination of automation and/or autonomy. Therefore, the design of operational scenarios must consider communications latency and communications coverage when Mission Control is in the operational command and control and/or decision loop. However, this does not imply any requirements on ground-based control versus autonomous operations.

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For periods where continuous communication is not required, such as uncrewed quiescent operations (e.g. loiter within NRHO, etc.), the HLS Integrated Lander may have the opportunity of operating more autonomously during pre-planned communication coverage outages. In addition, communications coverage can also be lost for any number of reasons; therefore, it is recommended that HLS Integrated Lander should have the autonomous capability to operate for at least 12-24 hours (typically recommended) of unplanned loss of communications.

4.3 HLS FREQUENCY SELECTION AND SPECTRUM PLANNING

The HLS Integrated Lander will need to make provisions for Radio Frequency Communications utilizing the frequency bands that are allocated in the US domestic regulations and in the International Telecommunication Union (ITU) Table of Frequency allocation as specified below:

1. Direct-with-Earth bi-directional Communications:

a. X-Band is limited to spacecraft tracking, telemetry and command (TT&C) operations.

b. Ka-Band can accommodate wider bandwidths, such as 2-way telerobotic operation, science data return and, video streams while including spacecraft

TT&C.

c. S-Band, while still permitted for DWE communications, is subject to spectrum crowding and licensing restrictions. Permanent licenses for near-earth S-Band use will no longer be granted by ITU, and temporary licenses are unreliable for full HLS Mission coverage.

d. All frequency requests are subject to NASA Lunar Spectrum Manager review and completion of an interagency technical pre-coordination process prior to regulatory approval.

e. Transmit authority of the pre-coordinated spectrum uses will be subject to licensing approval through the Federal Communications Commission (FCC) and compliant with ITU filing results.

2. Orion Proximity or Gateway Visiting Vehicle Communications will be via bi-directional S-Band Link and are generally intended for direct communication between vehicles for rendezvous, proximity operations, docking and undocking (RPODU) purposes:

a. Orion: Distances up to 800 km, with radiometric ranging and data transfers.

i. Orion can support radiometric ranging out to a maximum distance of 800km. However, low-rate communication links with Orion, without ranging, are possible far beyond 800 km, subject only to link margin limitations.

b. Gateway: Distances up to 400 km, with radiometric ranging and data transfers.

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i. For distances beyond 400km, use the Gateway Lunar Systems Link(s) as described below.

c. All frequency requests are subject to NASA Lunar Spectrum Manager review and completion of an interagency technical pre-coordination process prior to regulatory approval.

d. Transmit authority of the pre-coordinated spectrum uses will be subject to licensing approval through the Federal Communications Commission (FCC) and compliant with ITU filing results.

3. Gateway Lunar Systems Link(s) for separation distances > 400km, including from the surface of the Moon:

a. Distances up to 70,000 km from Lunar South Pole to NRHO perilune.

b. Gateway Lunar Systems link(s)s are S-Band and Ka-Band, which may both be used concurrently.

c. All frequency requests are subject to NASA Lunar Spectrum Manager review and completion of an interagency technical pre-coordination process prior to regulatory approval.

d. Transmit authority of the pre-coordinated spectrum uses will be subject to licensing approval through the Federal Communications Commission (FCC) and compliant with ITU filing results.

4. Surface Wi-Fi Communications with EVA Suits (for Video, Science Data, EVA Suit Informatics, etc.), as defined in EVA-EXP-0067, HLS-xEVA System IRCD and other Wi-Fi entities, such as external or hand-held cameras and pre-positioned lunar assets (Lunar Terrain Vehicles, Pressurized Rovers, Surface Habitats, etc.):

a. EVA suits are assumed to have a maximum on-foot traverse distance of up to 2 km radius from the HLS Integrated Lander on the lunar surface. Some distances may require the use of repeaters and/or other augmentations.

b. EVA surface mobility assets, such as Lunar Terrain Vehicle or Pressurized Rover, are assumed to have a maximum traverse distance of up to 10 km radius from the HLS Integrated Lander on the lunar surface. Communications over these distances could involve the use of repeaters and/or other augmentations.

c. Wi-Fi links should have data rates sufficient to convey full-resolution video streams from multiple sources (EVA suits, handheld camera, lunar assets, etc.)

to the HLS Integrated Lander.

d. Wi-Fi Frequency band: 5 GHz Band (preferred). Per EVA-EXP-0067, the EVA suits will utilize the 5 GHz Wi-Fi band only. Use of the 2.4 GHz Wi-Fi band is an available option for other lunar surface assets.

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e. All frequency requests are subject to NASA Lunar Spectrum Manager review and completion of an interagency technical pre-coordination process prior to regulatory approval.

f. Transmit authority of the pre-coordinated spectrum uses will be subject to licensing approval through the Federal Communications Commission (FCC) and compliant with ITU filing results.

5. UHF Communications with EVA Crew Members for Astronaut Voice and Health Biometrics plus Suit Status Data & Telemetry, as defined in EVA-EXP-0067:

a. EVA suits are assumed to have a maximum on-foot traverse distance of up to 2km radius from the HLS Integrated Lander on the lunar surface. Some distances or conditions may require the use of repeaters and/or other augmentations.

b. EVA surface mobility assets, such as Lunar Terrain Vehicle or Pressurized Rover, are assumed to have a maximum traverse distance of up to 10 km radius from the HLS Integrated Lander on the lunar surface. Communications over these distances could involve the use of repeaters and/or other augmentations.

c. All frequency requests are subject to NASA Lunar Spectrum Manager review and completion of an interagency technical pre-coordination process prior to regulatory approval.

d. Transmit authority of the pre-coordinated spectrum uses will be subject to licensing approval through the Federal Communications Commission (FCC) and compliant with ITU filing results.

6. External Gateway Wi-Fi Communications for data transfer when in close proximity with the HLS Integrated Lander (in NRHO):

a. “Best Effort” 5 GHz-band service, for non-critical data and telemetry applications, such as video transfer.

b. All frequency requests are subject to NASA Lunar Spectrum Manager review and completion of an interagency technical pre-coordination process prior to regulatory approval.

c. Transmit authority of the pre-coordinated spectrum uses will be subject to licensing approval through the Federal Communications Commission (FCC) and compliant with ITU filing results.

ICSIS Communications System Interoperability Standards

NASA/HEO has baselined HEOMD-003-02 International Communications System Interoperability Standards (ICSIS), revision A document for the HLS Program. The purpose of the ICSIS revision A standard is to define the functional, interface, and performance standards necessary to support interoperable and compatible communications between human exploration space-based platforms/vehicles, ground infrastructure, and other space and surface vehicles for human exploration in cislunar space (includes space transit, lunar orbit, and lunar surface segments).

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For the HLS Provider(s), some parts of ICSIS are required to ensure communications interoperability. For example, the Consultative Committee for Space Data Systems (CCSDS) protocols & encryption algorithms for Orion and Gateway compatibility are required—see the applicable HLS Integrated Lander-to-Gateway Radio Frequency Interface Control Document(s) for the necessary details and applicable portions specific to Gateway. Other parts of the ICSIS document, such as using only specific frequency bands to communicate with Earth, are not required.

Lunar Spectrum / Frequency Selection

The lunar frequency recommendations, provided by the Space Frequency Coordination Group (SFCG), are shown in Table 4-1, below. Table 4-1 contains frequency bands that may be considered for specific mission requirements and operation in addition to those specified in Section 4.3; however, the SFCG recommendation of frequencies does not supersede NASA architecture requirements.

Table 4-1 Recommended Frequency Bands for Communications in the Lunar Region Link Frequency Earth to Lunar Orbit 2025-2110 MHz (Note 1), (Note 2)

7190-7235 MHz

22.55-23.15 GHz (Note 2)

40.0-40.5 GHz Lunar Orbit to Earth 2200-2290 MHz (Note 2)

8450-8500 MHz

25.5-27.0 GHz

37-38 GHz (Note 3) Earth to Lunar Surface 2025-2110 MHz (Note 1), (Note 2)

7190-7235 MHz

22.55-23.15 GHz Lunar Surface to Earth 2200-2290 MHz (Note 2)

8450-8500 MHz

25.5-27.0 GHz Lunar Orbit to Lunar Surface 390-405 MHz (Note 4)

2025-2110 MHz (Note 2)

23.15-23.55 GHz Lunar Surface to Lunar Orbit 435-450 MHz (Note 4)

2200-2290 MHz (Note 2)

27.0-27.5 GHz Lunar Orbit to Lunar Orbit 2025-2110 MHz (Note 2)

2200-2290 MHz (Note 2)

23.15-23.55 GHz

27.0-27.5 GHz Lunar Surface Wireless Network 390-405 MHz (Note 4)

410-420 MHz

435-450 MHz (Note 4)

2.400-2.480 GHz

2.5035-2.620 GHz

5.15-5.835 GHz (Note 6)

25.25-25.5 GHz

27.225-27.5 GHz Lunar Relay to Lunar Relay Cross Link 13.75-14 GHz

14.5-15.35 GHz

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Table 4-1 Recommended Frequency Bands for Communications in the Lunar Region Link Frequency

23.15-23.55 GHz

27.0-27.5 GHz

37-38 GHz (Note 3)

40-40.5 GHz Amateur Radio Operation, Earth-to-Lunar Orbit 144-146 MHz

435-438 MHz (Note 5)

2.4-2.45 GHz (Note 5)

5.65-5.67 GHz (Note 5) Amateur Radio Operations, Lunar Orbit-to-Earth 144-146 MHz (Note 4)

435-438 MHz (Note 4), (Note 5)

10.45-10.5 GHz (Note 5) Notes to Table 4-1

(Note 1) In making frequency assignments for uplinks in the 2025 – 2110 MHz band to missions operating in the lunar vicinity, careful frequency coordination should be performed, and measures taken to minimize interference to spacecraft operating in low-Earth orbit and L1/L2.

(Note 2) In these communication frequency bands, position and navigation information may be contained in integrated ranging signals. However broadcast signals intended for PNT in the lunar region should use the frequency bands specified in Table 2 of SFCG Rec.14-2R5.

(Note 3) 37-38 GHz band subject to SFCG Rec.14-2R5.

(Note 4) Frequencies to only be used outside the Shielded Zone of the Moon (SZM).

(Note 5) These frequencies are allocated on a secondary basis only, except 435-438 MHz is allocated primary in

Region 1 and secondary in Regions 2 and 3.

(Note 6) 5.25-5.57 GHz is allocated to Space Research Service (SRS) (active) on a primary basis; use of these frequencies for communications in the lunar region is on a non-interference and unprotected basis to SRS

(active).

To protect radio astronomy observations in the shielded zone of the moon (SZM), the following International Telecommunication Union (ITU) Radio Regulations (RR) and recommendation apply:

• ITU RR Nos. 22.22 – 22.25 prohibits emissions causing harmful interference to radio astronomy observations and other users of passive services in the SZM in the entire frequency spectrum except frequency bands allocated to space science services supporting active sensing and radio communications applications.

• ITU Recommendation: Necessary transmission in the SZM shall ensure operation in the properly allocated frequency bands and prevent harmful interference to radio astronomy observation in the SZM.

All HLS spectrum activities, including spectrum planning, coordination, and licensing, should be coordinated through the NASA Lunar Spectrum manager and the Federal Communications Commission (FCC) and ITU.

4.4 COMMUNICATIONS PRIVACY

Certain voice, video, data and/or text sessions will need to be kept private for crew medical conferences or family voice/video calls or texts, crew health data (such as EVA) This can be

Release Date: July 07, 2022 Page: 21 of 74 accomplished via encryption, via data routing, or a combination of the two. Limited privacy can be achieved by employing protected data transport at lower layers and restricting distribution. Virtual channel assignment over Consultative Committee for Space Data Systems (CCSDS) RF links is not, by itself, an effective method of ensuring privacy, although it can help with data routing.

Metadata flags, commonly used in the music industry (MPEG3 ID3V2.X), can be used for the description of voice data. These flags may be used to indicate the type of conversation (e.g., family, or medical conference).

For voice communications, the person who is speaking or listening in a voice loop must have the required access permissions (role), user ID and password to permit logging into the voice system.

If Voice over Internet Protocol (VoIP) is used, the transmission of the voice data must fulfill the same security requirements as the transmission of data in an IP network.

Voice Channel Segregation, Desegregation, and Audio Loops

All Artemis Elements (i.e., the HLS Integrated Lander, Orion, Gateway, Mission Systems) need the capability to mix (multiplex or de-multiplex) all audio streams into a single ‘Master Channel’ audio feed/loop for increased situational awareness when performing cross-program operations, such as Rendezvous, Proximity Operations, and Docking (RPOD), so that every crew member can communicate at the same time on the same voice loop. Conversely, all Artemis Elements should also have the ability to segregate audio channels, when necessary for privacy, or to aid in focusing on a particular task or duty, and/or to increase communication efficiency when needed for separate but concurrent tasks. For example, consider the case when there are seven active voice channels during a particular mission segment (such as: docked operations in lunar orbit with a 2-crew member EVA). Each of the four Astronauts has a separate voice channel, while there are three voice channels to Mission Control Center (MCC) at that particular point in time.

For efficiency, the HLS Integrated Lander audio system should have the capability & flexibility to configure the channels and voice loops as follows (Example setup and one of many possibilities):

• Voice Loop 1: Comprised of Astronaut 1 and MCC 1, for the HLS Integrated Lander internal operations (configuring an on-board instrument)

• Voice Loop 2: Comprised of Astronaut 2 and MCC 2, for the HLS Integrated Lander internal operations (private medical conference)

• Voice Loop 3: Comprised of EVA 3 and EVA 4, and MCC 3, for the HLS Integrated Lander external EVA operations

• Voice Loop 4: Ability of a crew member inside the HLS Integrated Lander, or from Mission Systems to tie Voice Loop 1 and Voice Loop 3 together, for inside/outside communications.

With this type of communications loop functionality, it is possible to have three totally separate operations occurring concurrently yet be flexible enough to allow reconfiguration as/when needs change. This is especially true for DRM-002 which is an extended surface excursion mission that will leverage pre-placed assets at the lunar South Pole to support four crew members for a longer duration surface mission.

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4.5 MOTION VIDEO IMAGERY DRIVER FOR RF LINK DATA RATES

NASA will be providing the HLS Astronauts with one or more hand-held cameras for use during the mission. While the specific camera(s) have not been chosen, desired characteristics include being capable of recording and live-streaming high-quality stills (>20 Mega-pixels) and capable of recording and live-streaming high-quality video motion imagery (2160p30 4:2:2 UHD 4K or 1080p30 FHD, user-selectable). It is expected that both still and video imagery will be broadcasted back live from the lunar surface (and at other times, e.g., while docking/undocking). This will require a high-rate, wide-bandwidth downlink, likely using Ka-Band, from the HLS Integrated Lander to Earth. In addition, the HLS Integrated Lander should have the ability to receive uplinked video from Earth for video/medical/engineering conference use. This will require a sufficiently-high-rate uplink to convey at least one channel of video from Earth to the HLS Integrated Lander.

Motion Imagery from the lunar surface—particularly during EVA operations—is expected to be the largest communications link data rate driver, during which time the HLS Integrated Lander needs the ability to live-stream no less than two (ideally six or more) simultaneous video feeds for a crew of two (2). Example motion imagery feeds are as follows:

• EV Astronaut #1 Helmet Video Camera for real-time situational awareness

• EV Astronaut #2 Helmet Video Camera for real-time situational awareness

• EV Astronaut #3 Helmet Video Camera for real-time situational awareness

• EV Astronaut #4 Helmet Video Camera for real-time situational awareness

• HLS Integrated Lander-mounted Ladder-Cam (climb down and footsteps on Moon) or portable Tripod-Cam for later EVAs

• HLS Integrated Lander-Mounted Cam (remote-control camera mounted atop the HLS Integrated Lander for third-person viewpoint & public affairs.)

• Hand-cam video streams (or still photo uploads) to verify lighting/focus/framing (EV Astronaut #1)

• Hand-cam video streams (or still photo uploads) to verify lighting/focus/framing (EV Astronaut #2)

Note: CCSDS Framing/Formatting can use a significant amount of overhead, so link raw data speeds will need to accommodate this, in all cases. Additional data rate margin will be needed for non-video related data, such as voice and telemetry/science/engineering/health/status/command data.

4.6 VARIOUS TYPES OF DATA RATES USED HEREIN

In this CONOPs, and only if the “data rate” or “symbol rate” is not otherwise specified, uses of ‘data rate’ herein will generally refer to location B, the “framed data rate”, and ‘’symbols” will generally refer to location C, the “FEC Symbol Rate” as shown below in Figure 4-2.

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Figure 4-2 Illustration of various Data Rate and Symbol Rate Definitions used within Communication Systems

4.7 TRANSPONDER POINT A VS POINT B FUNCTIONALITY

Standard transponders operate in either ‘Point A’ mode (Standard Spacecraft User Mode) or ‘Point B’ mode (Ground Station Mode). The ‘Point B’ side of the link generates digital ranging codes, receives the ‘reflected’ codes back from the Point A user, and uses the delay & doppler to determine range and range-rate measurements. Typically, standard transponders operate in ‘Point A’ mode (Standard Spacecraft User Mode) only, while some specialized transponders can also operate in either ‘Point B’ mode or ‘Point A’ mode. Both Orion and Gateway Visiting Vehicle (VV) link transponders are capable of both ‘Point A’ and ‘Point B’ modes of operation with Orion preferring to operate in ‘Point B’ mode during RPOD operations. The Gateway Lunar System (LS) link system operates ‘Point B’ mode only.

5.0 GROUND STATION USE

The HLS Provider(s) may utilize any combination of government-provided and/or commercially-provided Ground Stations / Networks to support the sustaining Artemis mission objectives. It is desired that all high data rate communications links will, at a minimum, support the ability to transmit at least two live 2160p30 (4K UHD) video streams from the HLS Integrated Lander to Earth, and receive at least one 1080p30 live video stream from Earth to the HLS Integrated Lander, during all mission segments and with sufficient RF link margins.

Space Communication and Navigation (SCaN)

NASA's Space Communication and Navigation (SCaN) Program provides communications services that are essential to the operations of NASA's space flight missions. The two networks, Deep Space Network (DSN) and Near Space Network (NSN) provide support to over one hundred NASA and non-NASA missions. NASA’s Deep Space Network 70m and 34m diameter ground station antennas are heavily subscribed supporting current missions, so NASA’s Space Communication and Navigation (SCaN) organization does not recommend that the HLS Provider(s) rely solely upon either of those assets for nominal / routine lunar operations for sustaining lunar missions. Instead, SCaN recommends utilizing dedicated 18.3-meter diameter Lunar Exploration Ground Stations (LEGS) to support the Artemis Campaign, and designing links to close using no larger than 18.3 m assets.

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DSN 34m Ground Stations:

While heavily utilized, the Deep Space Network (DSN) ground-based 34-meter antennas provide the best value Direct with Earth (DWE) communication services for NASA missions operating in the Near Earth and Deep Space regions.