Attachment I - L10 Payload to Launch Services Interface Description Doc (LS IDD) Rev.pdf

Attachment No. I

Landsat 10 Payload to Launch Services Interface Description Document (L10-

LS IDD)

RFP 80GSFC26R0015

National Aeronautics and Space Administration Goddard Space Flight Center

Landsat 10 LS IDD L10-LS-ICD-0009 Revision B ii

Landsat 10 Launch Services Interface Description Document

(L10-LS IDD)

Signature/Approval Page Prepared by:

Electronic Signature in TDMS Approval Date in TDMS John Satrom Date Landsat 10 Launch Integration Manager NASA/GSFC, Code 472

Approved by:

Cagatay Aymergen Date Landsat 10 Deputy Project Manager / Acting Observatory Manager

NASA/GSFC, Code 426

Ross Henry Date Landsat 10 Project Manager NASA/GSFC, Code 426

Evan Webb Date Landsat 10 Mission Systems Manager NASA/GSFC, Code 533 iii

CM Foreword This document is a Landsat 10 Project Configuration Management (CM)-controlled document.

Note: Prior to February 2026, the project name was Landsat Next (LNext).

For the purposes of configuration management, the prefixes “LNEXT” and “L10” are completely interchangeable. For example, LNEXT-MGMT-PLAN-0004 is the same as L10-MGMT-PLAN- 0004.

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 10 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 10 Project Office, Code 426 Attention: Configuration Management Office Greenbelt, Maryland 20771 iv

Change History Log v

List of TBDs/TBRs Hyperlink to TBx Location Summary Ind.

Name/Org.

Due Date

TBx-1 Section 3.5.1.3

LV-IDD-125 The Contractor shall budget for particulate contamination levels deposited on all Observatory surfaces from all LV sources to less than 0.25 Percent Area Coverage (PAC) (TBC) from the start of encapsulation of the Observatory in the PLF through the completion of the LV Collision and Contamination Avoidance Maneuver (CCAM).

LSC L-2Y

TBx-2 Section 3.5.1.3

LV-IDD-126 The Contractor shall budget for molecular contamination levels deposited on all Observatory surfaces, excluding the LandIS instrument, from all LV sources to less than 0.50 μg/cm2 (50 angstroms) (TBC) from the start of encapsulation of the Observatory in the PLF through the completion of the LV CCAM.

LSC L-2Y

TBx-3 Section 3.5.1.3

LV-IDD-684 The Contractor shall budget for molecular contamination levels deposited on the LandIS instrument surfaces from all LV sources to less than 0.25 μg/cm2 (25 angstroms) (TBC) from the start of encapsulation of the Observatory in the PLF through the completion of the LV CCAM.

LSC L-2Y

TBx-4 Section 3.8.3

The LV will provide a GN2 purge to the Observatory from two interface connectors (reference Paragraph 3.3.1) that support a purge flow rate up to (TBD) l/hr (standard liters), beginning at integration of the Observatory to the LV PLA through T-0, to include during transportation from the Payload Processing Facility (PPF) to the launch facility and mating of the Observatory to the LV.

LandIS SE L-3Y vi

Table of Contents SIGNATURE/APPROVAL PAGE ................................................................................................ II CM FOREWORD ..........................................................................................................................III CHANGE HISTORY LOG .......................................................................................................... IV

LIST OF TBDS/TBRS .................................................................................................................... V

TABLE OF CONTENTS .............................................................................................................. VI LIST OF FIGURES ..................................................................................................................... VII LIST OF TABLES ....................................................................................................................... VII

1.0 INTRODUCTION

1.1 Purpose

1.2 Scope

1.3 Related Documents

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 INTERFACE REQUIREMENTS

3.1 GENERAL

3.2 Observatory Design Constraints

3.2.1 Observatory Coordinate System

3.2.2 Observatory Structural Stiffness Requirements

3.2.3 Observatory Center of Mass (CM)

3.3 MECHANICAL

3.3.1 Mechanical Interfaces

3.3.2 Launch Vehicle Payload Fairing (PLF) Volume

3.3.3 Observatory Final Closeouts Prior to Encapsulation

3.3.4 Observatory Propellant Contingency Offloading

3.3.5 Secondary Payload Accommodations

3.4 ELECTRICAL

3.4.1 Airborne Interfaces

3.4.2 Separation Monitoring Circuits

3.4.3 Ground Interfaces

3.4.4 Observatory Electrical Bonding and Grounding

vii

3.5 ENVIRONMENTS

3.5.1 Contamination Control

3.5.1.1 Payload Processing Facility (PPF) Environment

3.5.1.2 Payload Fairing Environment

3.5.1.3 Contamination Budget Contributions from Launch Vehicle

3.5.1.4 Launch Vehicle Environmental Control System Impingement Velocity 13

3.5.2 Ground Transportation Loads

3.5.3 Flight Mechanical Environments

3.5.3.1 Design Load Factors

3.5.3.2 Payload Fairing Pressure Decay Rate

3.5.3.3 Acoustic Environment

3.5.3.4 Sine Vibration Environment

3.5.3.5 Random Vibration Environment

3.5.3.6 LV Shock Environment

3.5.4 Flight Thermal Environment

3.5.5 Electromagnetic Environment

3.5.5.1 Radiated Emissions and RF Transmissions

3.5.5.2 Radiated Susceptibility

3.6 Flight Design

3.6.1 Injection Orbit Characteristics

3.6.2 Mission Thermal Constraints

3.6.3 Spacecraft Separation

3.7 FLIGHT OPERATIONS

3.7.1 In-Flight Video Coverage of Mission Deployment Events

3.7.2 LV Telemetry

3.7.3 Spacecraft Acquisition Assistance

3.8 GROUND OPERATIONS

3.8.1 Payload Processing Facilities (PPF)

3.8.2 Ground Handling Requirements

3.8.3 Spacecraft Instrument Purge

3.9 OBSERVATORY TESTING SUPPORT

3.9.1 Environmental Testing Support

3.9.2 Flight Adapter Fit Check

APPENDIX A ABBREVIATIONS AND ACRONYMS

APPENDIX B DEFINITIONS

List of Figures Figure 2.4-1 Landsat 10 Mission Architecture

List of Tables

Table 2.4.1-1 Landsat 10 Mission Parameters Table 3.6.1-1 Landsat 10 Injection Orbit Table 3.6.3-1 LV Separation Parameters

1.0 INTRODUCTION

1.1 PURPOSE

The Landsat 10 Launch Services Interface Description Document (L10-LS IDD) establishes the general, interface requirements imposed between the Landsat 10 Observatory (Observatory) and the Government-provided launch service. The L10-LS IDD is imposed on the Contractor. This IDD will have a complimentary document known as the NASA Launch Services Program (LSP) Launch Services Interface Requirements Document (LSIRD). The LSIRD will contain the requirements used by LSP to procure the Government-provided launch service.

Following award of the Launch Service Task Order (LSTO) to the Launch Services Contractor (LSC), the LSC will be responsible for generating the Landsat 10 Launch Vehicle Interface Control Document (LVICD)(L10-LS-ICD-0008). Once approved by the Landsat 10 Project (Government and the Contractor), LSP, and the LSC, the LVICD will replace the L10-LS IDD as the document capturing the requirements and associated verifications between the Observatory and the Government-provided launch service.

1.2 SCOPE

Throughout this document references will be made to the Launch Services Contractor (LSC) or launch vehicle (LV) and the Observatory. References to the LV refer to either the “LSC” or the “LV” and apply only to the launch vehicle. References to “Landsat 10" or "Observatory" apply only to the Landsat 10 Observatory.

1.3 RELATED DOCUMENTS

1.3.1 Applicable Documents

Document Number Title Revision Section Reference

IEST-STD-CC1246 Product Cleanliness Levels - Applications, Requirements, and Determination

E 3.5.1.2, 3.8.3

MIL-PRF-27401 Propellant Pressurizing Agent, Nitrogen

H w/ Amendment 2 3.8.3

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

This document table was generated from the Landsat 10 Common Reference and Applicable Documents List (L10-MGMT-DESC-0008), DRAFT Rev F.

1.3.2 Reference Documents

Document Number Title Revision ISO 14644-1 Cleanrooms and associated controlled environments - Part 1: Classification of air cleanliness by particle concentration

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

1.3.3 Project Reference Documents

Document Number Title L10-LV-ICD-0008 Landsat 10 Launch Vehicle Interface Control Document (LVICD) L10-OBSV-REQ-0031 Landsat 10 Observatory Environmental Requirements Document

(ObsERD) L10-SC-REQ-0011 Landsat 10 Spacecraft Requirements Document (SRD) In this document, citations are assumed to be the latest version unless otherwise noted.

2.0 MISSION OVERVIEW

2.1 MISSION STATEMENT

Landsat 10, consistent with United States (U.S.) law and government policy, will continue the Landsat program's acquisition, archival, and distribution of multi-spectral imagery, thereby 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 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. This investigation 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. Landsat Next subsequently passed its Mission Concept Review (MCR) and Key Decision Point-A (KDP-A) reviews in 2022. In March 2026, the Landsat Next mission was re-architected and re-designated Landsat 10 as a single observatory mission.

The goal of Landsat 10 is to continue the acquisition, archival, and distribution of multi-spectral imagery, thereby 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 10 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.

2.3 MISSION OBJECTIVES

Landsat 10 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 10 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 10 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 10 data products to the public freely on a nondiscriminatory basis.

2.4 MISSION IMPLEMENTATION

The Landsat 10 mission includes a single observatory in a 653 km sun-synchronous low-earth orbit (LEO). The observatory includes a single integrated suite of sensors called LandIS (the Landsat Instrument Suite) that images the full swath required to achieve global coverage via a repeating ground track every 18 days.

The LandIS improves all spectral and spatial capabilities by approximately twofold when compared with the Operational Land Imager (OLI) and Thermal InfraRed Sensor (TIRS) instruments flown on Landsats 8 and 9, while maintaining the historical Landsat data continuity and similar temporal coverage.

Each Landsat 10 partner agency has specific responsibilities and will deliver major elements to the overall mission. NASA will provide the Space Segment (SS) and the Launch Services Segment (LSS), and the USGS will provide the Ground System (GS) and Mission Operations.

NASA/Goddard Space Flight Center (GSFC) will provide overall Landsat 10 project management, mission system engineering and mission assurance during development and will transition the mission to USGS for science operations following on-orbit commissioning.

Figure 2.4-1 Landsat 10 Mission Architecture

(Generated from Landsat 10 Common Mission Architecture Diagram L10-SYS-DESC-0022 Rev B)

2.4.1 Space Segment

NASA/GSFC provides the Space Segment via competitive procurements for the science instrument suite (LandIS) and the spacecraft bus. The Space Segment will consist of a single observatory flying in a sun-synchronous, near-polar orbit at 653 km altitude. The spacecraft, instrument, and overall Landsat 10 mission are specified as risk class C per NPR 8705.4. The overall mission parameters needed to achieve global coverage are shown below in the Mission Parameters Table.

Table 2.4.1-1 Landsat 10 Mission Parameters

LandIS is a whiskbroom scanner which provides 26 spectral bands covering a swath on the ground of approximately 164 km on a fixed ground track defined by a world-wide reference system known as WRS-3. LandIS acquires raw detector data for all spectral bands within 15 seconds to minimize band-to-band and georegistration errors, reduce classification change detection errors due to clouds, and provide simultaneous acquisitions for science applications.

LandIS then performs data compression prior to packaging the data for transfer to the spacecraft storage and subsequent downlink. LandIS also provides internal calibration sources such as blackbody, a space port, stim lamps and solar diffuser.

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. These simulators will have varying fidelity and capabilities to meet various mission needs.

2.4.2 Ground Segment

The Landsat Ground Segment (GS) 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 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 10 MOC will be used for command and control, health and status monitoring, orbit and attitude maintenance, performance analysis, onboard memory management, and flight software maintenance. The MOC will support onboard autonomy for mission planning and scheduling. The MOC ingests, processes and archives telemetry data delivered via the GN. The Landsat 10 Flight Operations Team (FOT) located at the MOC performs these functions and is responsible for monitoring the observatory, 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 to and from the observatory and MOC for commanding and housekeeping data via the S-band, and will receive science mission data from the observatory over a Ka-band downlink.

The DPAS ingests, processes, and archives science data returned from the observatory via the GN. LandIS data will be processed into data products with a ground sample distance (GSD) ranging from 10m-60m depending on the particular spectral band. 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 10 data products, via a public-facing web portal for receiving data products.

The USGS will lead overall Landsat 10 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 10 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 observatory-to-LV integration. The Launch Segment will include the LV; all

Launch Vehicle-Ground Support Equipment (LV-GSE), property, and facilities to integrate the observatory to the LV and verify its integration; and perform prelaunch testing with ground-based functions. The launch vehicle and launch site will be specified during late Mission Phase B or early Phase C.

Sections 2.0-2.4.3 were generated using Landsat 10 Common Boilerplate (L10-MGMT-DESC- 0005) Rev E

3.0 INTERFACE REQUIREMENTS

This section establishes the Observatory to LV system interface design requirements for the Landsat 10 Mission.

The LS IDD requirements to be levied on the Observatory are identified by an “LV-IDD-##” at the beginning of the requirements statement and use the word “shall” in the definition of the requirement. A portion of the requirements levied on the LSC are also included for reference and are denoted by “will” statements.

Any exceptions taken by the Contractor to the requirements in this document require prior review and approval by the Government.

3.1 GENERAL

The ground and flight environments specified in this document are maximum expected flight levels (95% probability/50% confidence level) and have been levied as design, fabrication, and test requirements on the Observatory. They do not include any test margins with regard to establishing either proto-flight or qualification test levels for Observatory hardware.

The candidate launch vehicles for the Landsat 10 mission are the SpaceX 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.

3.2 OBSERVATORY DESIGN CONSTRAINTS

3.2.1 Observatory Coordinate System

LV-IDD-24 The origin of the Observatory structural coordinate system shall be located in the Observatory to LV separation plane at the intersection with the LV longitudinal axis.

3.2.2 Observatory Structural Stiffness Requirements

LV-IDD-26 The Observatory structural stiffness shall have a minimum fundamental axial mode frequency greater than 25 Hz.

LV-IDD-27 The Observatory structural stiffness shall have a minimum fundamental lateral mode frequency greater than 10 Hz.

3.2.3 Observatory Center of Mass (CM)

LV-IDD-29 The Observatory lateral center of mass (CM) offset from the Observatory longitudinal axis shall be less than or equal to 50 mm.

Note: This requirement assumes that the Observatory longitudinal axis and the LV longitudinal axis are co-aligned.

3.3 MECHANICAL

3.3.1 Mechanical Interfaces

LV-IDD-35 The mechanical interfaces between the Observatory and the LV shall consist of: a standard Marmon Clamp, mechanical mating/separation interface with separation springs; two (2) electrical umbilical In-flight Disconnect (IFD) connectors; and two (2) gaseous nitrogen (GN2) T-0 purge interfaces.

LV-IDD-37 The Observatory design shall utilize a commercially-available, separation system configuration for the Observatory to LV mechanical mating interface (i.e. diameter of 1194mm, 1575mm, or 1666mm).

The LSC will provide the Payload Adapter (PLA) and the separation system components required to safely separate the Observatory from the LV to include the separation springs and the active ring that remains with the LV post-separation.

LV-IDD-40 The Observatory design shall include the separation system passive ring interface that remains with the Observatory post-separation from the LV.

3.3.2 Launch Vehicle Payload Fairing (PLF) Volume

LV-IDD-47 The Observatory design shall be compatible with the static payload fairing

(PLF) volumes of the candidate launch vehicles listed in Section 3.1 as defined in their respective LV Payload User’s Guides.

Note: Any LV-defined stay-out zones adjacent to the Observatory to LV mating interface will be negotiated during the launch integration process.

Payload fairing static volume definitions should be verified with the Government.

3.3.3 Observatory Final Closeouts Prior to Encapsulation

The Observatory design will provide for the completion of all final closeout activities prior to encapsulation in the LV payload fairing per the Landsat 10 Spacecraft Requirements Document

(L10-SC-REQ-0011) (SRD-1088).

Note: This includes activities such as final protective/contamination cover removals and flight enable plug installations on the Observatory.

Note: The LV will not provide for accommodations for post-encapsulation access to the Observatory other than in support of emergency and/or contingency operations.

3.3.4 Observatory Propellant Contingency Offloading

Propellant offloading following mate of the Observatory to the LV will only be performed in the event a contingency offload scenario is required. The approach for contingency access accommodations will be determined following selection of the LV.

3.3.5 Secondary Payload Accommodations

The Government may manifest secondary payloads on the Landsat 10 mission based upon available excess LV performance and implementation of the required Do No Harm criteria to ensure the successful integration and launch of the Observatory.

3.4 ELECTRICAL

The LV system will provide electrical interconnection between the Observatory, the LV, and the Observatory Electrical Ground Support Equipment (EGSE) from the time of encapsulated Observatory to LV mate until separation of the Observatory in flight except as noted below.

The LV umbilical harnessing will provide for harness connections to the Observatory for:

1) Power, command, telemetry, and monitoring between the Observatory EGSE and the Observatory.

2) LV-monitored umbilical circuits to detect separation of the Observatory in flight.

The LV combined operations processing flow may involve extended periods of time when the Observatory EGSE must be disconnected from the LV umbilical to Observatory EGSE interface to allow for transit of the encapsulated Observatory and the fully integrated LV between launch processing facilities.

The Observatory design will allow for periods with the EGSE being disconnected from the LV umbilical interface following the completion of final Observatory closeout activities for up to 12 hours during combined operations activities with the LV per the Landsat 10 Spacecraft Requirements Document (L10-SC-REQ-0011) (SRD-1100).

The Observatory and EGSE harnessing design and operations will allow for the safe demate and mate of the Observatory EGSE to LV umbilical interface following the completion of final Observatory closeout activities without affecting the Observatory safety inhibit posture LV per the Landsat 10 Spacecraft Requirements Document (L10-SC-REQ-0011) (SRD-1101).

3.4.1 Airborne Interfaces

LV-IDD-73 The Observatory airborne electrical interface to the LV shall consist of two

(2), 61-pin, aft-facing IFD connectors located 180 degrees apart at the Observatory to LV separation plane.

The LSC will provide the Contractor with three (3) complete ship sets (both sides of the connector mating pairs) of flight-qualified IFD connectors for use on the Observatory and associated EGSE harnessing.

LV-IDD-77 The Observatory shall limit the current on each LV umbilical circuit to no more than 100 milliamps during the LV liftoff and Observatory to LV separation events.

LV-IDD-78 All Observatory separation detection circuits that initiate mission critical functions shall provide single-fault tolerance with a minimum sampling persistency to tolerate open circuit durations of up to 100 milliseconds simultaneously across all pins on each IFD connector.

3.4.2 Separation Monitoring Circuits

The LV will monitor for separation of the Observatory and will provide confirmation of separation in LV telemetry.

LV-IDD-86 The Observatory design shall provide for one (1) separation loopback circuit in each IFD umbilical connector for use by the LV in monitoring Observatory separation from the LV.

3.4.3 Ground Interfaces

The LV will provide an EGSE room(s) at the launch complex with a customer EGSE interface panel to provide connectivity to the LV umbilical for both power and commanding to, and detect sensor signals and telemetry from, the Observatory while mated to the LV. The EGSE room(s) will provide accommodations for the Observatory EGSE to include uninterruptible power if requested by the Contractor. The LV will provide Observatory EGSE accommodations at each facility where the Observatory integrated with the LV is processed during the combined operations flow.

The LSC will provide the Contractor with three complete mating sets (both sides of the connector mating pairs) of the ground umbilical interface connectors for use by the Observatory in the fabrication of the EGSE cables that will mate to the customer interface panel in the launch complex customer EGSE rooms, as well as for any other Observatory EGSE harnesses required to support Observatory to LV umbilical testing.

3.4.4 Observatory Electrical Bonding and Grounding

The Observatory to LV mechanical mating interface faying surface will have a surface bonding resistance that meets the levels listed in the Landsat 10 Spacecraft Requirements Document

(L10-SC-REQ-0011) (SRD-788).

3.5 ENVIRONMENTS

3.5.1 Contamination Control

3.5.1.1 Payload Processing Facility (PPF) Environment

The PPF operator will maintain a processing environment for the Observatory that meets or exceeds Cleanrooms and associated controlled environments - Part 1: Classification of air cleanliness by particle concentration, ISO 14644-1, Class 8 throughout the period of PPF occupancy by the Observatory.

3.5.1.2 Payload Fairing Environment

The LV will certify the surfaces of the LV payload compartment comply with the inspection criteria of Level VC-0.5-1000 + UV per Product Cleanliness Levels - Applications, Requirements, and Determination, IEST-STD-CC1246 prior to encapsulation of the Observatory.

The LV will limit the use of silicone-based materials that have the potential for cross-contamination of the Observatory. This includes both flight hardware within the payload compartment and materials used during ground processing. Where present in the LV system, appropriate mitigation techniques will be developed in coordination with the Observatory.

The LV will continuously maintain the particulate contamination environment within the PLF from encapsulation of the Observatory through launch such that it meets, at a minimum, the requirements of Cleanrooms and associated controlled environments - Part 1: Classification of air cleanliness by particle concentration, ISO 14644-1, Class 6.7 (Class 5,000).

The LV will continuously maintain the hydrocarbon environment (measured as methane gas) within the PLF from encapsulation of the Observatory through launch such that the measured levels are < 15 parts per million (ppm).

3.5.1.3 Contamination Budget Contributions from Launch Vehicle LV-IDD-125 The Contractor shall budget for particulate contamination levels deposited on all Observatory surfaces from all LV sources to less than 0.25 Percent Area Coverage (PAC) (TBC) from the start of encapsulation of the Observatory in the PLF through the completion of the LV Collision and Contamination Avoidance Maneuver (CCAM).

LV-IDD-126 The Contractor shall budget for molecular contamination levels deposited on all Observatory surfaces, excluding the LandIS instrument, from all LV sources to less than 0.50 μg/cm2 (50 angstroms) (TBC) from the start of encapsulation of the Observatory in the PLF through the completion of the

LV CCAM.

LV-IDD-684 The Contractor shall budget for molecular contamination levels deposited on the LandIS instrument surfaces from all LV sources to less than 0.25 μg/cm2 (25 angstroms) (TBC) from the start of encapsulation of the Observatory in the PLF through the completion of the LV CCAM.

3.5.1.4 Launch Vehicle Environmental Control System Impingement Velocity LV-IDD-128 The Observatory design shall show positive margins against the PLF

Environmental Control System (ECS) flow impingement velocity on all Observatory surfaces to a maximum rate of 5.0 m/sec.

3.5.2 Ground Transportation Loads

LV-IDD-130 The Observatory shall show positive margins against the loads imparted on the Observatory during integrated operations with the LV at the launch site, to include all transportation and hoisting operations, to levels not to exceed the flight environments as described in Paragraph 3.5.3.

3.5.3 Flight Mechanical Environments

3.5.3.1 Design Load Factors

The Observatory design will show positive margins against the induced load factors applied to the Observatory center of gravity to the levels listed in the Landsat 10 Observatory Environmental Requirements Document (L10-OBSV-REQ-0031) (ObsERD-1286). The margins are based on Observatory compliance with the stiffness requirements of Paragraph 3.2.2.

3.5.3.2 Payload Fairing Pressure Decay Rate

The Observatory design will show positive margins against the maximum pressure decay rate inside the PLF during LV ascent to the rate listed in the Landsat 10 Observatory Environmental Requirements Document (L10-OBSV-REQ-0031) (ObsERD-5148).

The Observatory design will show positive margins against the maximum residual atmospheric pressure inside the PLF to the pressure listed in the Landsat 10 Observatory Environmental Requirements Document (L10-OBSV-REQ-0031) (ObsERD-5585).

3.5.3.3 Acoustic Environment

The Observatory design will show positive margins against the maximum expected acoustic environment listed in the Landsat 10 Observatory Environmental Requirements Document (L10- OBSV-REQ-0031) (ObsERD-954 and ObsERD-3027).

3.5.3.4 Sine Vibration Environment

The Observatory will show positive margins against the maximum expected, low-frequency sine vibration environment listed in the Landsat 10 Observatory Environmental Requirements Document (L10-OBSV-REQ-0031) (ObsERD-3102).

3.5.3.5 Random Vibration Environment

The Observatory will show positive margins against the maximum expected, random vibration environment listed in the Landsat 10 Observatory Environmental Requirements Document (L10- OBSV-REQ-0031) (ObsERD-3041).

3.5.3.6 LV Shock Environment

The Observatory will be compatible with the maximum expected LV shock environment listed in the Landsat 10 Observatory Environmental Requirements Document (L10-OBSV-REQ-0031) (ObsERD-1091).

3.5.4 Flight Thermal Environment

The Observatory will show positive thermal margins given the free molecular heating (FMH) rate on the Observatory surfaces perpendicular to the velocity vector listed in the Landsat 10 Observatory Environmental Requirements Document (L10-OBSV-REQ-0031) (ObsERD-5177).

3.5.5 Electromagnetic Environment

LV-IDD-601 The Observatory shall demonstrate a minimum of 20 dB Electromagnetic

Interference (EMI) Safety Margin (EMISM) versus a direct current (DC) no-fire threshold for ordnance circuits.

LV-IDD-602 The Observatory shall demonstrate a minimum of 6 dB Electromagnetic

Interference (EMI) Safety Margin (EMISM) versus a DC no-fire threshold for non-ordnance circuits that are deemed safety or mission critical.

The above circuits have the potential to adversely impact the ability of the LV to successfully complete its mission.

3.5.5.1 Radiated Emissions and RF Transmissions

The Observatory will limit the maximum Observatory-generated electromagnetic field emissions, as measured at the LV to Observatory separation plane, to the levels listed in the Landsat 10 Observatory Environmental Requirements Document (L10-OBSV-REQ-0031) (ObsERD-4406).

LV-IDD-439 Following the start of combined operations with the LV and for the remainder of ground operations, telecommunications with the Observatory shall be accomplished solely through the LV umbilical hard-line connections.

LV-IDD-442 The Observatory shall not initiate radio frequency (RF) transmissions during the period beginning with final Observatory closeouts prior to PLF encapsulation and ending no earlier than 120 seconds following Observatory separation from the LV.

3.5.5.2 Radiated Susceptibility

The Observatory will maintain full functionality after exposure to the Launch Site/LV RF emissions radiated on the Observatory at the launch facility, as measured at the LV to

Observatory separation plane, to the levels listed in the Landsat 10 Observatory Environmental Requirements Document (L10-OBSV-REQ-0031) (ObsERD-4378).

Note: Frequency notches associated with the Observatory receiver frequencies will be determined during the launch integration process.

3.6 FLIGHT DESIGN

3.6.1 Injection Orbit Characteristics

The LV will provide the required performance to place the Observatory into the LV injection orbit with parameters as shown in Table 3.6.1-1 within the tolerances indicated. Parameters are provided in terms of osculating orbit elements.

Table 3.6.1-1 Landsat 10 Injection Orbit

Parameter Value Tolerance Mean Semi-major Axis 7026.33 km

(IO-1-1)

± 20 km

(IO-1-2)

Mean Apogee Radius 7045

(IO-2-1)

± 20 km

(IO-2-2)

Inclination 97.9835 °

(IO-3-1)

± 0.1 deg

(IO-3-2)

Argument of Perigee 90.0 °

(IO-4-1)

N/A

(IO-4-2)

Mean Local Time (MLT) of Descending Node 10:10

(IO-5-1)

± 1.0 minute

(IO-5-2)

This table was made from the Landsat 10 Common Orbit Injection Table L10-SYS-DESC-0036 Rev A

The Contractor’s mission design will account for the defined LV injection errors.

3.6.2 Mission Thermal Constraints

The LV will implement a Passive Thermal Control (PTC) roll maneuver about the LV longitudinal axis at a rate of 1.0 ± 0.5 deg/sec during upper stage coast periods when not in eclipse if required to maintain the Observatory within thermal limits.

The LV will maintain the orientation of the LV during upper stage coast periods when not in eclipse, to include periods when a PTC roll is performed, such that the LV longitudinal axis is normal to the sun vector within ± 10 degrees if required to maintain the Observatory within thermal limits. This requirement does not apply to the periods required for the LV upper stage to maneuver to the thermal condition attitude or maneuver from the thermal condition attitude to the restart and/or separation attitude.

3.6.3 Spacecraft Separation

LV-IDD-652 The Observatory shall be compatible with the LV-induced separation parameters shown in Table 3.6.3-1.

Table 3.6.3-1 LV Separation Parameters

Parameter Requirement Separation Velocity Sufficient to preclude recontact between the Observatory and the LV following separation Tip-off Angular Rates Observatory Axis Worst Case Rates

(deg/sec 3-sigma) Roll 1.0 Pitch 2.0 Yaw 2.0

3.7 FLIGHT OPERATIONS

3.7.1 In-Flight Video Coverage of Mission Deployment Events

The LV will provide an in-flight video system with lighting and downlink telemetry relay services that provides coverage of the Observatory separation from the LV beginning a minimum of 30 seconds prior to issuance of the Observatory separation command and continuing for a minimum of 90 seconds.

3.7.2 LV Telemetry

The LV will provide for confirmation of Observatory separation from the LV in the LV telemetry.

3.7.3 Spacecraft Acquisition Assistance

The LV will provide the Observatory with an orbital parameters message (OPM) based upon LV upper stage telemetry data taken from the LV prior to and as close as possible to the issuance of the Observatory separation command propagated forward to the Observatory first descending node crossing.

The LV will deliver the OPM to the Landsat 10 mission operations team within 30 minutes of the Observatory separation event.

3.8 GROUND OPERATIONS

3.8.1 Payload Processing Facilities (PPF)

The Government will provide the PPF accommodations for the Observatory at the launch site for a period starting no earlier than L-60 days and continuing through L+7 days.

3.8.2 Ground Handling Requirements

LV-IDD-531 The Observatory shall accommodate mating to the LV PLA assembly in the vertical orientation with subsequent LV processing occurring in either the horizontal or vertical configuration for the remainder of LV integrated operations.

Note: All hoisting operations of the Observatory involving the use of the Observatory lifting sling will be accomplished in the vertical orientation.

3.8.3 Spacecraft Instrument Purge

The LV will provide a GN2 purge to the Observatory from two interface connectors (reference Paragraph 3.3.1) that support a purge flow rate up to (TBD) l/hr (standard liters), beginning at integration of the Observatory to the LV PLA through T-0, to include during transportation from the Payload Processing Facility (PPF) to the launch facility and mating of the Observatory to the

LV.

The GN2 provided will meet the requirements of Propellant Pressurizing Agent, Nitrogen, MIL- PRF-27401, Grade B. Specific parameters with regard to flowrate, system pressure, purge outage limitations and recovery periods will be determined during the launch integration process.

LV-IDD-557 The Observatory shall clean and certify all new GN2 Purge system components to be used during combined operations with the LV per Product Cleanliness Levels - Applications, Requirements, and Determination, IEST- STD-CC1246, Level 100A.

LV-IDD-558 The Observatory shall provide a minimum of two purge panels that control the purge interface to the Observatory to support combined operations with the LV.

3.9 OBSERVATORY TESTING SUPPORT

3.9.1 Environmental Testing Support

The LSC will provide a test PLA and separation system in support of final Observatory mechanical environmental testing (sine-vibration, acoustic, and separation shock) for a maximum duration of eight (8) weeks. The LSC will support installation of the Observatory to the PLA prior to the start of environmental testing at the Contractor’s facility. The LSC will return to perform separation-shock testing and removal of the test PLA following the completion of sine-vibration and acoustic testing.

3.9.2 Flight Adapter Fit Check

The LSC will support fit check operations between the Observatory and the LV flight PLA and separation system at the Contractor’s facility.

The fit check will include verification of the T-0 purge interfaces between the LV PLA and the Observatory.

The fit check will include verification of the LV PLA flight harnessing with the Observatory IFDs and the Observatory EGSE.

LV-IDD-567 The Observatory shall perform an electrical verification test through the LV flight PLA umbilical harnessing as a part of the LV flight umbilical fit check.

Note: The verification should be comprised of a safe-to-mate check and a functional check-out (aliveness test).

Appendix A Abbreviations and Acronyms Acronym Definition # Number V/m Volts per meter ACCESS Advanced Communications

Capabilities for Exploration and Science Systems

AST Architecture Study Team C Centigrade CARA Conjunction Assessment Risk

Assessment CCAM Launch vehicle Collision and

Contamination Avoidance Maneuver CG Center of Gravity CM Center of Mass cm2 Square Centimeter dB Decibels dBµV/m Decibel Microvolts per meter DC Direct Current deg Degree DPAS Data Processing and Archive System ECS Environmental Control System EGSE Electrical Ground Support

Equipment EMI Electromagnetic Interference EMISM Electromagnetic Interference (EMI)

Safety Margin EROS Earth Resources Observation and

Science ERTS Earth Resources Technology

Satellite f Frequency FDF Flight Dynamics Facility FMH Free Molecular Heating FOT Flight Operations Team GN2 Gaseous Nitrogen GN Ground Network GPS Global Positioning System Grms Root Mean Square of the

Acceleration g’s Gravitational Acceleration GS Ground System GSE Ground Support Equipment GSFC Goddard Space Flight Center Hz Hertz ICD Interface Control Document IDD Interface Design Document I/F Interface IFD in-flight disconnect in Inch ISO International Standards Organization kg Kilogram km Kilometer L1 GPS Frequency Level (L-Band

1575.42 MHz)

L2 GPS Frequency Level (L-Band

1227.60 MHz)

LandIS Landsat Instrument Suite LDCM Landsat Data Continuity Mission LGN Landsat Ground Network LNext Landsat Next LSC Launch Services Contractor LSIDD Launch Services Interface

Description Document LSIRD Launch Services Interface

Requirements Document LSP Launch Services Program LSP Launch Services Provider LSTO Launch Service Task Order LV Launch Vehicle LVICD Launch Vehicle Interface Control

Document LV-GSE Launch Vehicle-Ground Support

Equipment m Meter m2 Meters squared m/sec Meters per second MHz Megahertz MIL Military MLT Mean Local Time mm Millimeter MOC Mission Operations Center MPE Maximum Predicted Environment N/A Not Applicable NASA National Aeronautics and Space

Administration NSLRSDA National Satellite Land Remote

Sensing Data Archive NSN Near Space Network NTE Not To Exceed OPM Orbital Parameters Message PAC Percent Area Coverage PLA Payload Adapter PLF Payload Fairing PPF Payload Processing Facility ppm Parts Per Million PSD Power Spectral Density PTC Passive Thermal Control RE Radiated Emissions Rev Revision RF Radio Frequency

RV Random Vibration SC Spacecraft sec Second SI International System of Units SLI Sustainable Land Imaging SRD Spacecraft Requirements Document SRS Shock Response Spectrum SRS Software Requirements

Specification STD Standard T Time TBC To Be Confirmed TBD To Be Determined TBS To Be Scheduled/Supplied TIR Thermal Infrared TOD Time of Day UHF ultra-high frequency U.S. United States USGS United States Geological Survey V Volts V/m Volts per Meter VSWIR Visible through Short Wave Infrared W Watts WRS Worldwide Reference System WRS-3 Worldwide Reference System-3 This Acronyms List was generated from the Landsat 10 Common Acronyms List (L10-MGMT-DESC-0006) Draft Rev E.

Appendix B Definitions Term Definition Argument of Perigee The angle that specifies the location of perigee in the orbit, relative to the ascending node.

Collect To acquire, downlink, and subsequently transfer data from the observatory to the ground system.

Configuration The functional and physical characteristics of the payload and all its integral parts, assemblies and systems that are capable of fulfilling the fit, form and functional requirements defined by performance specifications and engineering drawings.

Contamination The presence of materials of molecular or particulate nature which degrade the performance of hardware.

Demonstrate To show that the current knowledge of one or more system parameters is correct and accurate by collecting and processing test data using current calibration parameters and analyzing the performance of the processed results.

Flight Hardware Hardware to be used operationally in space.

Hardware As used in this document, there are two major categories of hardware.

· Prototype Hardware (See Prototype Hardware)

· Flight Hardware (See Flight Hardware)

Housekeeping Data Data that provides information about the health and status of the unit.

Margin The amount by which software, firmware, or hardware capability exceeds requirements.

Mission Data The time-correlated data set containing Landsat 10 imaging sensor data, spacecraft and LandIS ancillary data.

Observatory The spacecraft plus LandIS, that are flown as part of the Landsat 10 mission.

Qualification See Design Qualification Tests.

Space Segment The Space Segment is the Landsat 10 Observatory.

Spectral Band An interval in the electromagnetic spectrum commonly designated by a spectral bandwidth and a center wavelength.

Swath The strip on the Earth that the instrument observes as it passes overhead.

Verification The process of ensuring mission/segment requirements are satisfied. Verification occurs using one or more of these methods: analysis, test, demonstration, or inspection.

Visible EM radiation in the range of 380-750 nm.

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

Examples of wideband data processing steps for Landsat 10 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 10 image sensor, ancillary data and stored housekeeping data.

These Definitions were generated from the Landsat 10 Common Lexicon (L10-SYS-DESC-0004) Draft Rev E.