LNEXT-SC-ICD-0007 Rev B LNext SC-GND IRD 20250124.pdf

DOORS EXPORT

National Aeronautics and Space Administration

Goddard Space Flight Center Greenbelt, Maryland

LNEXT-SC-ICD-0007, Revision B

Landsat Next, Code 426

Landsat Next Spacecraft to Ground Interface Requirements Document (SC-GND IRD)

LNext Reviewed – Not Subject to Export Control

1/24/2025

SC-GND IRD LNEXT-SC-ICD-0007 Revision B ii Use or disclosure of data contained on this page is subject to the restriction(s) on the title page of this document.

Landsat Next Spacecraft to Ground Interface Requirements Document (SC-GND IRD) Signature/Approval Page

Prepared by:

Electronic Signature in TDMS Approval Date in TDMS Bryan Mattfeld Date Landsat Next Spacecraft Systems Engineer NASA/GSFC, Code 560

Approved by:

Cagatay Aymergen Date Acting Landsat Next Project Manager / Landsat Next Deputy Project Manager

NASA/GSFC, Code 426

Cagatay Aymergen Date Acting Landsat Next Observatory Manager NASA/GSFC, Code 426

Evan Webb Date Landsat Next Mission System Manager NASA/GSFC, Code 599 iii Use or disclosure of data contained on this page is subject to the restriction(s) on the title page of this document.

CM Foreword This document is a Landsat Next Project Configuration Management (CM)-controlled document.

Changes to this document require prior approval of the applicable Configuration Control Board (CCB) Chairperson or designee. Proposed changes shall be submitted to the Landsat Next CM Office (CMO), along with supportive material justifying the proposed change. Changes to this document will be made by complete revision.

Questions or comments concerning this document should be addressed to:

NASA/Goddard Space Flight Center Landsat Next Project Office, Code 426 Attention: Configuration Management Office Greenbelt, Maryland 20771 iv Use or disclosure of data contained on this page is subject to the restriction(s) on the title page of this document.

Change History Log

Revision Effective Date Description of Changes (Reference the CCR/SCoRe Approval Date)

- 04/09/2024 LNEXT-CCR-0022 – Initial Release A 11/12/2024 LNEXT-CCR-0090 – Update for draft SC RFP B 01/23/2025 LNEXT-CCR-0112 – Updated to include the latest versions of the Landsat Next Common Boilerplate, LNEXT-MGMT- DESC-0005 Rev D and Landsat Next Common Mission Architecture Diagram, LNEXT-SYS-DESC-0022 Rev A.

v Use or disclosure of data contained on this page is subject to the restriction(s) on the title page of this document.

Table of Contents SIGNATURE/APPROVAL PAGE ................................................................................................ II

CM FOREWORD ..........................................................................................................................III

CHANGE HISTORY LOG .......................................................................................................... IV

TABLE OF CONTENTS ................................................................................................................ V

LIST OF FIGURES ........................................................................................................................ V

LIST OF TABLES ........................................................................................................................ VI

1.0 INTRODUCTION

1.1 Purpose

1.2 Scope

1.3 RELATED DOCUMENTATION

1.3.1 Applicable Documents

1.3.2 Reference Documents

1.3.3 Project Reference Documents

2.0 MISSION OVERVIEW

2.1 Mission Statement

2.2 Mission Background

2.3 Mission Objectives

2.4 Mission Implementation

2.4.1 Space Segment

2.4.2 Ground Segment

2.4.3 Launch Segment

3.0 SPACE TO GROUND AND IN-SPACE COMMUNICATION INTERFACES

4.0 NARROWBAND

4.1 Narrowband Interface Parameters

4.2 Narrowband Protocols

4.3 Narrowband Performance

5.0 WIDEBAND

5.1 Wideband Interface Parameters

5.2 Wideband Protocols

5.3 Wideband Performance

APPENDIX A ABBREVIATIONS AND ACRONYMS

APPENDIX B DEFINITIONS

List of Figures Figure 2.4-1 Triplet Constellation Observatory Spacing On-Orbit Figure 2.4-2 Landsat Next Mission Architecture vi Use or disclosure of data contained on this page is subject to the restriction(s) on the title page of this document.

List of Tables Table 2.4.1-1 Mission Parameters Table 4.1-1 Narrowband (S-Band) Space to Ground Link Parameters for NASA NSN-

DTE and LGN Table 4.1-2 Space Relay (S-Band) Link Parameters Table 4.3-1 Bit Error Rate Values Table 5.1-1 Wideband Mission Data Downlink

Use or disclosure of data contained on this page is subject to the restriction(s) on the title page of this document.

1.0 INTRODUCTION

1.1 PURPOSE

The Landsat Next Spacecraft to Ground Interface Requirements Document (SC-GND IRD) establishes the general interface requirements imposed between the spacecraft (SC) and ground systems (GS).

1.2 SCOPE

Section 2 provides a mission overview to include mission objectives and implementation.

Section 3 documents general overview requirements for the space to ground interface and compliance with spectrum standards. Section 4 describes the narrowband interfaces. Section 5 describes the wideband interfaces.

The Landsat Next Interface Requirements documents (Landsat Next Spacecraft Interface Requirements Document (SCIRD), LNEXT-SC-ICD-0002, Landsat Next Spacecraft to Ground Interface Requirements Document (SC-GND IRD), LNEXT-SC-ICD-0007 are controlled and maintained by the Landsat Next Project Office. The SC-GND IRD applies to both sides of the spacecraft and ground system interface. The IRD is maintained at Level 3.

1.3 RELATED DOCUMENTATION

1.3.1 Applicable Documents

Document Number Title Revision Section Reference

NPD 2570.5 NASA Electromagnetic Spectrum Management - Revalidated 5/5/2022

E ALL

450-SNUG Space Network Users Guide

(SNUG)

11 ALL

453-NENUG Near Earth Network Users Guide

(NENUG)

5 ALL

CCSDS 131.0-B-5 TM Synchronization and Channel Coding

Recommended Standard, Issue 5

ALL

CCSDS 133.0-B-2 Space Packet Protocol Recommended Standard, Issue 2, Editorial Change 1

ALL

CCSDS 133.1-B-3 Encapsulation Packet Protocol Recommended Standard, Issue 3, Editorial Change 1

ALL

CCSDS 131.2-B-2 Flexible Advanced Coding and Modulation Scheme for High Rate Telemetry Applications

Recommended Standard, Issue 2

ALL

CCSDS 231.0-B-4 TC Synchronization and Channel Coding

Recommended Standard, Issue 4

ALL

CCSDS 232.0-B-4 TC Space Data Link Protocol Recommended Standard, Issue 4

ALL

CCSDS 232.1-B-2 Communications Operation Procedure-1

Recommended Standard, Issue 2, Technical corrigendum 1

ALL

Use or disclosure of data contained on this page is subject to the restriction(s) on the title page of this document.

Document Number Title Revision Section Reference

CCSDS 232.1-B-2 Cor. 1 Technical Corrigendum 1 to

CCSDS 232.1-B-2

Technical Corrigendum 1

ALL

CCSDS 301.0-B-4 Time Code Formats Recommended Standard, Issue 4, Editorial Change 1

ALL

CCSDS 401.0-B-32 Radio Frequency and Modulation Systems--Part 1: Earth Stations and Spacecraft

Recommended Standard, Issue 32

ALL

CCSDS 732.0-B-4 AOS Space Data Link Protocol Recommended Standard, Issue 4

ALL

ITU-R SA.1157-1 Protection criteria for deep-space research

N/A ALL

ITU-R SM.1541-6 Unwanted emissions in the out-of-band domain

N/A ALL

ITU-R SM.329-12 Unwanted emissions in the spurious domain

N/A ALL

FIPS PUB 140-3 Security Requirements for Cryptographic Modules

N/A ALL

FIPS PUB 197 Advanced Encryption Standard

(AES)

N/A ALL

NIST SP 800-38D Recommendation for Block Cipher Modes of Operation:

Galois/Counter Mode (GCM) and

GMAC

N/A ALL

NIST SP 800-38C Recommendation for Block Cipher Modes of Operation: The CCM Mode for Authentication and Confidentiality

N/A ALL

NTIA Manual Manual of Regulations and Procedures for Federal Radio Frequency Management

January 2021 Edition - January 2023 Revision

ALL

Recommendation SFCG 21- 2R5

Efficient Spectrum Utilisation for Space Research Service (Category A) and Earth Exploration-Satellite Service on Space-to-Earth Links

N/A ALL

In this document, citations are assumed to be the latest version unless otherwise noted.

This document table was generated from the Landsat Next Common Reference and Applicable Documents List (LNEXT-MGMT-DESC-0008) Rev E.

1.3.2 Reference Documents

Document Number Title Revision Public Law #105-303 Commercial Space Act of 1998, Public Law #105-303, 112 Stat., 2843., H.R. 1702, 105th Congress, Adopted October 28, 1998

N/A

Public Law #102-555 Land Remote Sensing Policy Act of 1992, Public Law #102-555, 106 Stat. 4163., H.R. 6133, 102nd Congress, Adopted October 28, 1992

N/A

In this document, citations are assumed to be the latest version unless otherwise noted.

This document table was generated from the Landsat Next Common Reference and Applicable Documents List (LNEXT-MGMT-DESC-0008) Rev E.

Use or disclosure of data contained on this page is subject to the restriction(s) on the title page of this document.

1.3.3 Project Reference Documents

Document Number Title LNEXT-MGMT-DESC-0005 Landsat Next Common Boilerplate LNEXT-MGMT-DESC-0006 Landsat Next Common Acronyms List LNEXT-MGMT-DESC-0008 Landsat Next Common Reference and Applicable

Documents List LNEXT-SC-ICD-0002 Landsat Next Spacecraft Interface Requirements

Document (SCIRD) LNEXT-SYS-DESC-0004 Landsat Next Common Lexicon LNEXT-SYS-PLAN-0007 Landsat Next Mission Operations Concept (Ops Con)

Document In this document, citations are assumed to be the latest version unless otherwise noted.

This document table was generated from the Landsat Next Common Reference and Applicable Documents List (LNEXT-MGMT-DESC-0008) Rev E.

Use or disclosure of data contained on this page is subject to the restriction(s) on the title page of this document.

2.0 MISSION OVERVIEW

2.1 MISSION STATEMENT

Landsat Next, consistent with United States (U.S.) law and government policy, will continue the Landsat program's acquisition, archival, and distribution of multi-spectral imagery, affording global, synoptic, and repetitive coverage of the Earth's land surfaces and coastal regions at a scale where natural and human-induced changes can be detected, differentiated, characterized, and monitored over time.

2.2 MISSION BACKGROUND

Following the successful launch of Landsat 8 (formally named Landsat Data Continuity Mission, LDCM) in February 2013, and during the development of Landsat 9, the United States Geological Survey (USGS) and the National Aeronautics and Space Administration (NASA) recognized the need to assemble a team of experts from within both agencies to evaluate and inform an acquisition strategy for the Landsat mission to follow Landsat 9. The NASA-USGS Joint Agency Sustainable Land Imaging (SLI) Architecture Study Team (AST) was formed in September 2018 and was tasked with investigating how to best satisfy the diverse set of user needs collected in the USGS User Needs for the Sustainable Land Imaging Program July 2018, Release 2.0. These investigations resulted in a set of recommendations to the headquarters of both agencies, delivered in December 2019. The highest-recommended “Roadmap 1” architecture described a small constellation of “superspectral” space-based sensors that would substantially improve the spectral, spatial, and temporal capabilities of previous Landsat missions, while continuing to satisfy the primary goal of ensuring a highly calibrated data set that maintains compatibility with the legacy data of the Earth’s land surfaces and coastal regions held in the National Satellite Land Remote Sensing Data Archive at the USGS’s Earth Resources and Observation Science (EROS) Center. In April 2020 NASA/Goddard Space Flight Center (GSFC) received authorization to initiate the Landsat Next project consistent with the AST’s “Roadmap 1” recommendation.

The goal of Landsat Next is to continue the acquisition, archival, and distribution of multi-spectral imagery affording global, synoptic, and repetitive coverage of the Earth's land surfaces and coastal regions at a scale where natural and human-induced changes can be detected, differentiated, characterized, and monitored over time. This goal is in keeping with the Landsat programmatic goals stated in both the Commercial Space Act of 1998, Public Law #105-303 and the Land Remote Sensing Policy Act of 1992, Public Law #102-555. This policy requires that the Landsat Program provide data into the future that is sufficiently consistent with previous Landsat data to allow the detection and quantitative characterization of changes in or on the land surface of the globe.

Landsat Next continues the long-running partnership of NASA and the USGS, with NASA providing the space and launch segments and the USGS providing the ground system (GS), providing the longest continuous global record of the Earth’s land surface and coastal regions.

The Landsat series of satellites have continuously acquired multispectral images of the global land surface since the launch of the Earth Resources Technology Satellite (ERTS, later renamed Landsat 1) in 1972.

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2.3 MISSION OBJECTIVES

Landsat Next has these major mission objectives:

· Collect and archive moderate resolution Visible to Shortwave-Infrared (VSWIR) reflective and Thermal Infrared (TIR) emissive image data affording seasonal coverage of the global landmass for a continuous period of not less than five (5) years.

· Ensure that Landsat Next data are sufficiently consistent with data from the earlier Landsat missions in terms of relative acquisition geometry, calibration, coverage characteristics, spectral characteristics, output product quality, and data availability; all of which permit scientific studies, management of land cover and land use change, along with associated inland and coastal water resources, over multi-decadal periods.

· Ensure Landsat Next is responsive to documented emerging user needs and applications as characterized by periodic assessment, currently the User Needs for the SLI Program July 2018, Release 2.0, and identified by the operational requirements for acquisition, processing, archiving, and distribution of Earth’s image data to the United States Government and other users.

· Distribute Landsat Next data products to the public freely on a nondiscriminatory basis.

2.4 MISSION IMPLEMENTATION

The Landsat Next mission is a constellation of three identical Observatories, referred to as “triplets” with equal orbit spacing. Each observatory images the full swath required to achieve global coverage, with the use of three observatories used to reduce revisit time for any scene.

The Figure below illustrates the 120 degree separation of the Observatories.

Figure 2.4-1 Triplet Constellation Observatory Spacing On-Orbit

This selected architecture of three observatories has been endorsed by the Landsat user communities and improves all temporal, spectral, and spatial capabilities by approximately twofold, while maintaining the historical Landsat data continuity. With all three observatories operating, imaging revisit will be every six (6) days, at the equator.

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Each agency has specific responsibilities and will deliver major elements to the overall mission.

NASA will provide the Space and Launch Segments of Landsat Next and the USGS will provide the Ground System and Operations. NASA/Goddard Space Flight Center (GSFC) will provide overall Landsat Next project management, mission system engineering and mission assurance during development and will transition the mission to USGS for science operations following on-orbit commissioning. Each agency in addition to specific responsibilities, will deliver the three major segments to the overall mission.

The three segments are the Space Segment (SS), the Ground Segment (GS), and the Launch Services Segment (LSS). They are described in more detail in the following sections and shown in the Landsat Next Operations Concept below.

Figure 2.4-2 Landsat Next Mission Architecture

(Generated from Landsat Next Common Mission Architecture Diagram LNEXT-SYS-DESC-0022 Rev A)

2.4.1 Space Segment

NASA/GSFC will provide the Space Segment via competitive procurements for the science instrument suite and the spacecraft bus. The Space Segment will consist of a constellation of three observatories flying in sun-synchronous, polar orbits at 653km altitude, each with nominally identical spacecraft and instrument suites. The three observatories will be launched on a single launch vehicle with a single dispenser provided by the spacecraft bus provider. The observatories will be transitioned to their final orbit alignments during commissioning. In aggregate, they provide a six-day ground repeat period at the equator. The spacecraft and instrument will be Class C. The Mission Class B is accomplished by providing redundancy at

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the Observatory level. The overall mission parameters needed to achieve global coverage are shown below in the Mission Parameters Table.

Table 2.4.1-1 Mission Parameters

A single Observatory will consist of the spacecraft and imaging sensors, referred to as the Landsat Next Instrument Suite (LandIS). Each observatory operates independently, and unique coordination is conducted by the ground as the observatories do not communicate with each other directly.

The LandIS instrument suite is a whiskbroom scanner which provides 26 spectral bands with a maximum ground sampling distance of 10m-60m dependent on the spectral band, covering a swath on the ground of approximately 164km on a ground track defined by a world-wide reference system known as WRS-3. The instrument suite will be capable of acquiring raw detector data for all spectral bands within 15 second to minimize the illumination changes within the observations. Data will be generated at a rate no greater than 1.8 Gbps. The LandIS provides internal calibration sources such as blackbody, a space port, stim lamps and solar diffuser. LandIS instrument suite provides compression prior to packaging the data for transfer to the spacecraft storage.

The Space Segment will also provide simulators for mission, ground system and interface testing during the development phase of the mission and in support of long-term maintenance of systems. Space Segment simulator types include spacecraft, instrument suite, spacecraft and the LandIS instrument suite interface, launch vehicle interface and a combination of simulators integrated to be an Observatory. These simulators will have varying fidelity and capabilities to meet the mission needs.

2.4.2 Ground Segment

The Landsat Ground Segment consists of the Ground System and its external interfaces, including NASA institutional services. The GS includes the Mission Operations Center (MOC), the Ground Network (GN), and the Data Processing and Archive System (DPAS). External

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interfaces include NASA's Near Space Network (NSN), GSFC Conjunction Assessment and Risk Analysis (CARA) and its Flight Dynamics Facility, along with other external interfaces.

The Landsat Next MOC functionality will be used for command and control, health and status monitoring, orbit and attitude maintenance, performance analysis, onboard memory management, and flight and ground software maintenance. The MOC will support onboard autonomy for mission planning and scheduling. The MOC ingests, processes and archives data delivered via the GN. The Landsat Next Flight Operations Team (FOT) located at the MOC performs these functions and is responsible for monitoring the Observatories, detecting, investigating and resolving spacecraft anomalies and monitoring the instrument image collections and special image collections.

The GN provides geographically dispersed ground station resources for mission execution; it includes the Landsat Ground Network (LGN) and a wideband data routing capability to the Landsat Cloud. The LGN provides communication capability for each observatory of the constellation for commanding and housekeeping data via the S-Band and will receive science mission data from each observatory over a Ka-band downlink. The LGN is used to transfer commands and receive telemetry from each Observatory within the constellation and deliver it to the MOC.

The DPAS ingests, processes, and archives science data returned from each satellite via the GN.

The DPAS also provides a long-term archive capability for raw data and allows the user community to query, download, and directly interact in the cloud with Landsat Next data products, via a public-facing web portal for receiving data products.

The USGS will lead overall Landsat Next GS development. The USGS will also lead integration of the GS and ensure timely completion of ground readiness testing in preparation for NASA-led mission readiness activities. The MOC will support Landsat Next mission readiness activities.

2.4.3 Launch Segment

The Launch Segment will provide the assets and services associated with the Launch Vehicle (LV) and the Mission Payload-to-LV integration. The Launch Segment will include the LV; all Launch Vehicle-Ground Support Equipment (LV-GSE), property, and facilities to integrate the Mission Payload to the LV and verify its integration; and perform prelaunch testing with ground-based functions. The launch vehicle and launch site have not been specified and will not be until closer to Mission Phase C. The three observatories comprising the Landsat Next Mission Payload, including the Observatory dispenser, will be launched together on the same launch vehicle.

The candidate launch vehicles for the launch of the Landsat Next Mission Payload are the Falcon 9 Full Thrust, the United Launch Alliance Vulcan Centaur and the Blue Origin New Glenn. This list will be updated in the future to reflect additions and deletions to the candidate launch vehicles presently available under the NASA Launch Services II Contract.

Sections 2.0-2.4.3 were generated using Landsat Next Common Boilerplate (LNEXT-MGMT- DESC-0005) Rev D

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3.0 SPACE TO GROUND AND IN-SPACE COMMUNICATION

INTERFACES

The GS includes a ground station-based capability, referred to as the GN, for communicating with the LNext constellation. The GN is comprised of the ground stations, networks, and all other data routing capabilities within the Ground System.

Key functions within the GN are to provide RF communications between each observatory and the ground for telemetry, command, and science data return. For telemetry and command the GN provides the interface between the observatories and the MOC. For science data return, the GN provides the interface between the observatories and the DPAS.

S-Band RF uplink and downlink communications are provided by the GN for MOC communications with each observatory, including telemetry and command. Ka-Band RF receive communications are provided by the GN for science data return. Science data return includes transfer of mission data files, which includes imaging sensor data and ancillary data, for science data ingest, processing, and archival. During a Ka-Band mission data downlink event, the ground station monitors the downlink and provides the MOC a status of mission data files that were successfully received by the ground following the end of the contact. The MOC uses this information to determine if retransmit commands are needed for specific science mission files.

The GN nominally provides 5-8 S-Band contacts and 10-12 Ka-band contacts per day per observatory. Like the ground network currently employed in support of Landsats 8 and 9, the LNext GN is anticipated to be a global network emphasizing use of polar stations, along with mid-latitude stations for geographic areas of interest such as the Continental United States.

Stations may include ground stations from the existing Landsat Ground Network portfolio, along with the addition of other commercial or partner providers. At launch and consistent with the spacecraft IRD, an excess of contact time will be scheduled across available stations to ensure ample margin for commissioning; however, overtime the contacts scheduled will be trimmed to optimize performance and cost.

Additionally, the GN includes a cloud-based data routing capability for the transfer of science mission data from GN stations to the DPAS. Furthermore, the GN includes secure network connectivity for the transfer of commands and telemetry between each station and the MOC / bMOC.

Ground Network stations will cache Ka-Band mission data received for at least 60-days and S- Band data received for at least 7-days to support continuity of operations, contingencies, and retransfers of data.

The NASA ACCESS Project will utilize the TDRSS network to provide low-rate telemetry and command capabilities to provide global coverage during initial deployment and during critical or contingency operations. For the initial LEO period after separation, TDRSS SSA services will be utilized to ensure the three observatories successfully transition into safe hold mode during times when GN coverage is not available. During first time critical events or during observatory major contingencies the TDRSS network will be called up (planned or critical service) to support monitoring or critical contingency commanding. After LEO the TDRSS service will be available for each observatory (subject to TDRSS constellation degradation) for proficiency or major critical anomaly support.

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SC-GND-252 RF emissions from the spacecraft shall be in compliance with the requirements of the International Telecommunications Union (ITU) including but not limited to Protection criteria for deep-space research, ITU- R SA.1157-1, Unwanted emissions in the out-of-band domain, ITU-R SM.1541-6, and Unwanted emissions in the spurious domain, ITU-R

SM.329-12.

Rationale: LNEXT must remain in compliance with ITU requirements for emissions to avoid interference with other missions.

SC-GND-253 RF emissions from the spacecraft shall be in compliance with the requirements of the National Telecommunications and Information Administration (NTIA) including but not limited to the emissions masks and limits to power flux density at the surface of the Earth specified in the Manual of Regulations & Procedures for Federal Radio Frequency Management, NTIA Manual.

Rationale: Compliance with NTIA regulations is mandated by NASA Policy Directive (NPD) NASA Electromagnetic Spectrum Management - Revalidated 5/5/2022, 2570.5.

SC-GND-254 RF emissions from the spacecraft shall be in compliance with the requirements of the Space Frequency Coordination Group (SFCG) including but not limited to Efficient Spectrum Utilisation for Space Research Service (Category A) and Earth Exploration-Satellite Service on Space-to-Earth Links, Recommendation SFCG 21-2R5.

Rationale: Compliance with SFCG recommendations is mandated by NASA Electromagnetic Spectrum Management - Revalidated 5/5/2022, NPD 2570.5.

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4.0 NARROWBAND

4.1 NARROWBAND INTERFACE PARAMETERS

SC-GND-54 The spacecraft narrowband interface to the NASA NSN-DTE and Landsat

Ground Network (LGN) shall be supported by the capabilities in Table 4.1-1 and Table 4.1-2.

Rationale: Table 4.1-1 provides a summary of expected interface parameters for S-band narrowband RF communications. Table 4.1-2 provides in-space link parameters.

Table 4.1-1 Narrowband (S-Band) Space to Ground Link Parameters for NASA NSN-

DTE and LGN

Parameter Value Link parameters Implementation loss 2.4 dB bit error rate (BER) Provided in Table 4.3-1 Network encoding Secure Socket Layer (SSL) Message format Radio Frequency and Modulation Systems--Part 1:

Earth Stations and Spacecraft, Consultive Committee for Space Data Systems (CCSDS) 401.0-B-32

Downlink S-band downlink frequency band 2200-2290 MHz Telemetry (TLM) Data Rate (Information Rate) 28 kbps (contingency, 95% spherical coverage), 3

Mbps (nominal) TLM modulation Quadrature Phase Shift Keying (QPSK)/Offset

Quadrature Phase Shift Keying (OQPSK) Selectable randomization TM Synchronization and Channel Coding, CCSDS

131.0-B-5 Error-correction coding TM Synchronization and Channel Coding, CCSDS

131.0-B-5 Uplink S-band uplink frequency band 2025-2108 MHz Swept uplink frequency range ± 80 KHz Swept uplink frequency rate 5-35 KHz/sec Command (CMD) data rates 1 ksps (contingency, 95% spherical coverage), 32 ksps, and 128 ksps CMD error correction TC Synchronization and Channel Coding, CCSDS

231.0-B-4 CMD modulation BiPhase Shift Keying (BPSK) CMD encryption AES-256 GCM or CCM Ground station Antenna aperture 7.3m (minimum) S-band gain-to-noise-temperature (G/T) receiver 18 dB/K Transmitter effective isotropic radiated power (EIRP) 54 dBW Axial ratio 1.5 dB Polarization left-hand circularly polarized (LHCP) or right-hand circularly polarized (RHCP) Minimum elevation angle 5°

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Table 4.1-2 provides the In-Space link parameters:

Table 4.1-2 Space Relay (S-Band) Link Parameters

Link Data Rate*

(ksps) Required Margin (dB)

Spherical Coverage (%)

Fwd 1.0 0 90 Rtn 4.0 0 90

8.0 0 90

16.0 0 90

32.0 0 ---

* The Forward rate is the symbol rate into the modulator. The Return rate is the symbol rate between the Command and Data Handling (C&DH) and Comm subsystems (prior to convolutional coding).

SC-GND-377 The spacecraft shall communicate via the narrowband link through the NSN-

DTE Network for command and telemetry in accordance with the 453- NENUG, Near Earth Network Users Guide.

SC-GND-378 The spacecraft shall communicate with the narrowband link through the

TDRSS Network for duplexed command and telemetry in accordance with the 450-SNUG, Space Network Users Guide, S-band Single Access (SSA) Telecommunications Services.

4.2 NARROWBAND PROTOCOLS

SC-GND-33 The space to ground telecommunication interfaces shall use the Consultative

Committee for Space Data Systems (CCSDS) Space Packet Protocol, CCSDS 133.0-B-2 for all command and telemetry packets.

Rationale: CCSDS standards provide for standard compatible interfaces through the protocol stack for space to ground communications and processing. CCSDS packets are standard for most NASA mission command and telemetry formatting, and a wide base of software/hardware Commercial-Off-the-Shelf (COTS) implement this protocol.

SC-GND-41 The space to ground telecommunication interfaces shall utilize single-data-source narrowband modulations consistent with Radio Frequency and Modulation Systems--Part 1: Earth Stations and Spacecraft, CCSDS 401.0- B-32, directly modulated on the main carrier.

Rationale: Modulations recommended in the CCSDS document are commonly supported standards.

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SC-GND-35 The space to ground telecommunication interfaces shall use TC Space Data Link Protocol, CCSDS 232.0-B-4 for all command data streams.

stack for space to ground communications and processing. This particular standard is low overhead for encrypted commands from the ground to the SC receiver/decrypter.

SC-GND-40 The space to ground telecommunication interfaces shall process the narrowband command uplink coded for error detection following TC Synchronization and Channel Coding, CCSDS 231.0-B-4.

Rationale: NASA NSN/NEN and LGN use CCSDS protocols.

SC-GND-258 The telecommunications interface shall implement the Automatic Repeat

Query (ARQ) protocol defined in Communications Operation Procedure-1 (COP-1), CCSDS 232.1-B-2 for each virtual channel reserved for software commands.

Rationale: Communications Operation Procedure-1, CCSDS 232.1-B-2protocol ensures sequential delivery without duplicate or missing telecommand (TC) frames.

SC-GND-255 The ground to space interface for commanding shall consist of

Communications Link Transmission Units (CLTUs) (a CLTU includes the start sequence, BCH codewords, and tail sequence) encrypted according to either Recommendation for Block Cipher Modes of Operation:

Galois/Counter Mode (GCM) and GMAC, NIST SP 800-38D (GCM) using the AES-256 cipher or Recommendation for Block Cipher Modes of Operation: The CCM Mode for Authentication and Confidentiality, NIST Special Publication 800-38C (CCM) using the AES-256 cipher.

Note: A CLTU may be segmented and transmitted in multiple encrypted and authenticated data units referred to as secured data units. Each secured data unit will also include an un-encrypted size field, nonce counter, and message authentication code (MAC) and will be prepended with a synchronization marker.

SC-GND-333 The ground to space interface for commanding shall include authentication of the CLTUs according to either Recommendation for Block Cipher Modes of Operation: Galois/Counter Mode (GCM) and GMAC, NIST SP 800-38D (GCM) using the AES-256 cipher or Recommendation for Block Cipher Modes of Operation: The CCM Mode for Authentication and Confidentiality, NIST Special Publication 800-38C (CCM) using the AES- 256 cipher.

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SC-GND-34 The space to ground telecommunication interfaces shall use AOS Space Data Link Protocol, CCSDS 732.0-B-4 for all telemetry.

stack for space to ground communications and processing. This particular standard is for standard Channel Access Data Unit (CADU) fixed sized data frames from SC narrowband.

SC-GND-38 The space to ground telecommunication interfaces shall support selectable randomization of the narrowband downlink in accordance with TM Synchronization and Channel Coding, CCSDS 131.0-B-5.

Rationale: Randomization ensures that high-bit transition density is maintained regardless of data transmitted. High-bit transition density aids reliable acquisition and tracking of the telemetry downlink.

SC-GND-39 The space to ground telecommunication interfaces shall utilize error-correction coding compliant with TM Synchronization and Channel Coding CCSDS 131.0-B-5, applicable on narrowband telemetry downlinks.

Rationale: The CCSDS recommended coding is a commonly supported standard with high coding gain, including either Reed Solomon or Low-Density Parity Check (LDPC) Forward Error Correction Codes.

4.3 NARROWBAND PERFORMANCE

SC-GND-36 For the narrowband command uplink and telemetry downlink the spacecraft shall have a narrowband BER at operational data rates, of less than or equal to 1E-6 (as provided in Table 4.3-1) after demodulation and application of all error-correction code at the end of spacecraft design life, for links to LGN stations.

Rationale: The 1E-6 BER is consistent with a reliable RF link.

SC-GND-37 For the narrowband forward and return links to the NSN, the spacecraft shall have a narrowband BER for each of the links as defined in the table below:

Rationale: The BER for NSN links (both ground stations and relay) are measured at the Near Space Network.

Table 4.3-1 Bit Error Rate Values

Link BER Required NEN/LGN Uplink 1E-6 Uncoded NEN/LGN Downlink 1E-6 (After all error correcting code) Space Network (SN) Forward 1E-5 Uncoded SN Return 1E-5 at Viterbi Decoder Output (Prior to RS decoder) SN Return 1E-6 (After all error correcting code)

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SC-GND-379 The spacecraft shall maintain no less than 3 dB of link margin for narrowband DTE (direct to earth) transmissions to all ground stations.

Rationale: Gold Rules 1.06 identifies lower link margins at later missions phases, however Landsat Next will use 3 dB across all phases.

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5.0 WIDEBAND

5.1 WIDEBAND INTERFACE PARAMETERS

SC-GND-136 The spacecraft shall provide wideband mission data transmissions to in-view ground stations in accordance with Table 5.1-1.

Rationale: Table 5.1-1 provides a summary of expected interface parameters for the wideband Ka-band link.

Table 5.1-1 Wideband Mission Data Downlink

Parameter Value

Link Wideband carrier Single or Multiple Ka-band carrier Bandwidth 25.5- 27.0 GHz Wideband center frequency 26.25 GHz Polarizations Left-hand Circularly Polarized (LHCP), or Right-hand Circularly

Polarized (RHCP), or Dual polarization Modulation Staggered Quadrature Phase Shift Keying (SQPSK)/OQPSK or 8PSK per Radio Frequency and Modulation Systems--Part 1: Earth Stations and Spacecraft, CCSDS 401.0-B-32

Maximum Data bit rate Up to 2.6 Gbps Forward error correction rate-7/8 LDPC (8160, 7136) shortened NASA code (CCSDS 131.0-B-

5) or Serial Concatenated Convolutional Code (CCSDS 131.2-B-2) De-randomization TM Synchronization and Channel Coding, CCSDS 131.0-B-5 is supported Atmospheric (weather) availability

95%

Atmospheric losses 9.0 dB

BER 1E-12

Implementation loss 3 dB Minimum elevation angle 10°

Ground terminal Antenna aperture 7.3m (minimum) Antenna figure of merit (G/T) (without Radome)

Minimum clear-sky Ka-Band 37.5 dB/K

Axial ratio 1.0 dB Radome loss 2 dB

5.2 WIDEBAND PROTOCOLS

SC-GND-44 The space to ground telecommunication interfaces shall support randomization of the wideband downlink in accordance with TM Synchronization and Channel Coding, CCSDS 131.0-B-5.

Note: Randomization performed within the transmitter is acceptable if it is in accordance with CCSDS standards.

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Rationale: Randomization ensures that high bit transition density is maintained regardless of data transmitted. High-bit transition density aids reliable acquisition and tracking of the downlink.

SC-GND-45 The space to ground telecommunications interfaces shall utilize either rate

7/8 ((8160, 7136) Low Density Parity Check (LDPC) error-correcting coding compliant with CCSDS TM Synchronization and Channel Coding, CCSDS 131.0-B-5 Sections 7 and 8 or Serial Concatenated Convolutional Code (SCCC) compliant with CCSDS 131.2-B-2 on wideband downlinks.

Rationale: LDPC 7/8 and SCCC are low overhead FEC for transmission from LEO missions.

SC-GND-46 The space to ground telecommunications interfaces shall utilize OQPSK or

8PSK modulation on the wideband downlink consistent with Radio Frequency and Modulation Systems--Part 1: Earth Stations and Spacecraft, CCSDS 401.0-B-32.

Rationale: Required for compatible modulation/demodulation between SC and Ground station.

SC-GND-327 The Space to Ground wideband data interface shall utilize Encapsulation

Packet Protocol, CCSDS 133.1 B-3 for all data files from the spacecraft wideband data system to the ground system.

Rationale: Encapsulation packet protocol is designed for low overhead, file type transfer from the spacecraft onboard system.

SC-GND-334 The space to ground telecommunication interfaces shall use Advanced

Orbiting Systems (AOS)- Space Data Link Protocol, CCSDS 732.0-B-4 for all wideband science data.

Rationale: CCSDS standards provide for standard compatible interfaces thru the protocol stack for space to ground communications and processing. This particular standard is for standard CADU fixed sized data frames from SC wideband data.

5.3 WIDEBAND PERFORMANCE

SC-GND-380 The spacecraft shall support a wideband data rate of up to 2.6 Gbps

(information rate).

Rationale: The wideband system will be used to downlink all mission data. Mission data primarily comprises science acquisitions encompassing all land and coastal waterway imaging per WRS-3 and annotated by DRC-18. The payload imaging data rate is assumed to be approximately 1.6 Gbps and is anticipated to be compressed by the payload at an average aggregate rate of 3:1, resulting in ~15 Terabits of mission data generated per satellite per day.

The Ka-band wideband system will downlink all mission data to a ground network comprised of polar and mid-latitude stations providing approximately 100 minutes of wideband contact time per satellite per day.

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SC-GND-42 The spacecraft shall maintain 3dB of link margin for the wideband transmission to the Ground Network, in addition to all link-degrading effects (e.g., atmospheric attenuation and noise temperature contributions, and inter-symbol interference) at the end of spacecraft design life.

Rationale: Maintaining 3 dB of margin for the wideband link is necessary to ensure high data integrity and avoid needing to retransmit data.

SC-GND-43 The spacecraft shall have a wideband transmission BER of less than 1E-12 to the ground system after demodulation and application of all error correction code at the end of spacecraft design life.

Rationale: Desire is for error-free GN contact windows. Note that the FEC codes described in Table 5.1-1 have a steep drop-offs for BER performance - essentially pass/fail behavior.

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Appendix A Abbreviations and Acronyms Acronym/Abbreviation Definition % Percent ACCESS Advanced Communications Capabilities for Exploration and Science

Systems AES Advanced Encryption Standard AOS Acquisition of Signal ARQ Automatic Repeat Query AST Architecture Study Team BER Bit error rate bMOC Backup Mission Operations Center BPSK BiPhase Shift Keying C Centigrade C&DH Command and Data Handling CADU Channel Access Data Unit CARA Conjunction Assessment Risk Assessment CCSDS Consultative Committee on Space Data Systems CLTUs Communications Link Transmission Units CMD Command COP Communication Operation Procedure COTS Commercial-Off-the-Shelf dB Decibels dB/K Decibels per Kelvin dBW Decibels above 1 Watt DPAS Data Processing and Archive System DRC Design Reference Case DRC-18 Design Reference Case - 18 EIRP Equivalent Isotropic Radiated Power EROS Earth Resources Observation and Science FOT Flight Operations Team g Gravitational Acceleration Gbps Gigabits per second GCM Galois/Counter Mode GFE Government-Furnished Equipment GHz Gigahertz GN Ground Network GS Ground System GSE Ground Support Equipment GSFC Goddard Space Flight Center GSSIR Ground System to Spacecraft Integration Test Rack G/T Gain-to-Noise Temperature (dB) HGS Hallway Ground Station ICs International Cooperators ICD Interface Control Document in Inches IRD Interface Requirements Document I&T Integration and Test ITU International Telecommunication Union K Kelvin kbps Kilobits per Second

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Acronym/Abbreviation Definition LDCM Landsat Data Continuity Mission LDPC Low-Density Parity Check LEO Low Earth Orbit LGN Landsat Ground Network LHCP Left-Hand Circularly Polarized LNext Landsat Next LV Launch Vehicle LV-GSE Launch Vehicle-Ground Support Equipment Mbps Megabits per Second MHz Megahertz MOC Mission Operations Center NASA National Aeronautics and Space Administration NEN Near Earth Network NENUG Near Earth Network Users' Guide NIST National Institute for Standards and Technology No Number NPD NASA Policy Directive NSLRSDA National Satellite Land Remote Sensing Data Archive NSN Near Space Network NTIA National Telecommunications and Information Administration OQPSK Offset Quadrature Phase Shift Keying (QPSK) QPSK Quadrature Phase Shift Keying Rev Revision RF Radio Frequency RHCP Right-hand Circularly Polarized RS Reed-Solomon SA Systems Assurance SC Spacecraft SCIRD Spacecraft Interface Requirements Document SC-GND IRD Spacecraft to Ground Interface Requirements Document SDVF Software Development and Verification Facility sec Second SFCG Space Frequency Coordination Group SLE Space Link Extension SLI Sustainable Land Imaging SM Software Manager SN Space Network SNUG Space Network Users' Guide SQPSK Staggered Quadrature Phase Shift Keying (QPSK) SSA S-Band Single Access SSL Secure Socket Layer T Time TBD To Be Determined TBR To Be Resolved/Revised TC Telecommand TDRSS Tracking and Data Relay Satellite System TIR Thermal Infrared TLM Telemetry TM Test Monitor TM Torque Margin

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Acronym/Abbreviation Definition TM Technical Memorandum U.S. United States USGS United States Geological Survey VSWIR Visible through Short Wave Infrared WAN Wide-Area Network WRS Worldwide Reference System WRS-3 Worldwide Reference System-3 This Acronyms List was generated from the Landsat Next Common Acronyms List (LNEXT-MGMT-DESC-0006) DRAFT Rev D.

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Appendix B Definitions Term Definition Collect To acquire, downlink, and subsequently transfer data from the observatory to the ground system.

Constellation One or more observatories flying in formation about the orbit. For

LNext, the constellation is comprised of 3 identical observatories, flying in formation approximately equidistance around the orbit plane.

Mission Data The time-correlated data set containing Landsat Next imaging sensor data, spacecraft and LandIS ancillary data.

Observatory The spacecraft plus LandIS, that are flown as part of the Landsat Next mission. The LNext constellation is comprised of 3 identical observatories.

Wideband Data The downlinked Mission Data that have been processed and formatted for efficient data transmission.

Examples of wideband data processing steps for Landsat Next purposes include lossless compression, error detection and correction coding, and pseudo-noise encoding. Examples of wideband data formatting include packet and frame-level organization of the Landsat Next image sensor, ancillary data and stored housekeeping data.

These Definitions were generated from the Landsat Next Common Lexicon (LNEXT-SYS-DESC-0004) DRAFT 3 Rev D.