SATPC0035230 Tab 04 4 SOW.pdf

EXHIBIT A

Statement of Work

For the

Geostationary Littoral Imaging and Monitoring Radiometer (GLIMR) Mission Access to Space (ATS)

Industry Concept Study

Version 1.0

May 21, 2024

Document Change Record

Revision Date Description of Change

0.2 10/24/2023 Preliminary version

1.0 05/21/2024 Baseline

Table of Contents 1 Introduction and Background

1.1 Introduction

1.2 Background

1.3 Study Milestone Schedule

2 Documents

2.1 Applicable Documents .................................................... Error! Bookmark not defined.

2.2 Reference Documents

2.3 Provided Models

3 Study Assumptions

3.1 Orbit

3.2 Design Life and Risk Classification

3.3 Environments

3.4 Deployments

3.5 Spacecraft to Payload Interface Assumptions

4 Work to be performed

4.1 Feasibility and Concept Studies

5 Reporting Schedule

5.1 Kickoff

5.2 Weekly Status Tag up

5.3 Check Point Review ........................................................ Error! Bookmark not defined.

5.4 Concept Study Review

6 Contract Data Requirement List (CDRL)

List of Tables

Table 1. Spacecraft to Payload Interface Assumptions Table 2. Contract Data Requirement List

1 INTRODUCTION AND BACKGROUND

1.1 Introduction

This Statement of Work (SOW) details the work to be performed by the Contractor in support of the Geostationary Littoral Imaging and Monitoring Radiometer (GLIMR) Access to Space (ATS) Concept Study. This study activity is intended to determine feasible ATS implementation approaches which enable the GLIMR Instrument to fulfill mission science requirements, assess the critical thermal, mechanical, and electrical interfaces that drive the GLIMR ATS approach, and address the development and verification approach of the GLIMR mission. This study will also assess the cost, schedule, technical performance, and risk drivers to provide the GLIMR ATS approach. The study results will help inform the technical and programmatic requirements and strategy for a potential GLIMR ATS request for proposal.

The intent of the study is to inform the government of the feasibility and risks associated with the current GLIMR ATS requirements and potential approaches to providing GLIMR ATS. Specific areas of interest include, but are not limited to:

1. How the key and driving requirements affect design, performance, cost, schedule, and risks of a potential ATS approach.

2. Analysis showing where performance and accommodation requirements can be or cannot be met.

3. Spacecraft concept, including mechanical and thermal interfaces, stowed and deployed configurations (where applicable), mass, and power.

4. Cost factors for the potential ATS approach.

5. Development plans and timeline including unique supply chain and/or long-lead procurement considerations.

No specific GLIMR ATS procurement strategy has been established and NASA is looking to industry to help shape the overall approach. NASA is not currently imposing any limitations on the potential ATS opportunities for GLIMR (e.g., hosting service; rideshare; dedicated free flyer;

other) and is looking to better understand industry opportunities and approaches to best support the GLIMR Mission.

1.2 Background

The GLIMR Mission provides transformative rapid observations of dynamic coastal zones ecosystems throughout the Gulf of Mexico (GoM) and coastal continental U.S (CONUS) to observe and monitor ocean biology, chemistry, and ecology to help protect ecosystem sustainability, improve resource management, and enhance economic activity. This includes identifying and tracking harmful algal blooms and oil spills, while also observing, quantifying, and understanding processes associated with rapid changes in phytoplankton growth.

GLIMR is classified as a Category 3 (per NPR 7120.5E, NASA Space Flight Program and Project Management Requirements) Class D mission (per NPR 8705.4, Risk Classification for NASA Payloads). The GLIMR Mission is in Phase C, Final Design and Fabrication, with instrument (payload) delivery planned for no earlier than June 2025.

The University of New Hampshire (UNH) under contract 80LARC20DA002 with NASA to provide project management, mission science requirements, mission systems engineering, science team leadership, science operations center, applications leadership, public outreach, and communications. Raytheon (RTX) is subcontracted to UNH to provide payload development, payload systems engineering, and payload safety and mission assurance.

Southwest Research Institute (SWRI) is subcontracted to UNH to provide project management support, project system engineering support, and mission safety and mission assurance.

The GLIMR ATS scope is anticipated to consist of the following: spacecraft; launch vehicle;

GLIMR payload to spacecraft integration and test; spacecraft to launch vehicle integration and launch; command uplink from the industry-provided Mission Operations Center (MOC); downlink of GLIMR engineering and science telemetry to the industry-allocated Ground Station(s);

delivery of error-checked GLIMR data to various mission partners; and all related tasks and support needed during the planned GLIMR Mission (i.e., pre-launch planning, launch support, in-orbit check-out, and operations).

1.3 Study Milestone Schedule

The study period of performance is for six months with the following milestones provided below.

Milestone Schedule Kickoff meeting Within two weeks of award Concept Study Review Award + 5 months

2 DOCUMENTS

2.1 Reference Documents

The following documents are for reference to support this study. These documents will be provided after contract award.

GLIMR-SE-04 GLIMR Concept of Operations Document Goddard Space Flight Center (GSFC) - Standard (STD)-1000

Goddard Technical Standard: Rules for the Design, Development, Verification, and Operation of Flight Systems

GSFC-STD-7000 General Environmental Verification Standard (GEVS) for GSFC Flight Programs and Projects

NASA Procedure Requirement (NPR) 8705.4 Risk Classification for NASA Payloads NPR 7120.5 NASA Space Flight Program and Project

Management Requirements GLIMR-06-0001 GLIMR Host Spacecraft Requirements

Document (HSRD) GLIMR-06-0002 GLIMR Host Spacecraft Interface Control

Document

Any changes to the reference documents will be passed to all study participants once the government approves the change(s).

2.2 Provided Models

The following models are for concept study analyses. They will be provided after contract award.

GLIMR-AM-04 GLIMR Payload Reduced Order Structural and

Mechanical Model with launch configuration [TBD] Payload Structural Model (NASTRAN) with on-orbit configuration [TBD] LOS Jitter Post-Processing Script with nstructions GLIMR-AM-07 GLIMR Payload Reduced Order Thermal

Model

Any changes to the reference models will be passed to all study participants once the government approves the change(s).

3 STUDY ASSUMPTIONS

This section provides mission design assumptions to support this effort. The Government will provide additional documentation after contract award including the reference documents and models stated in Section 2. The Contractor shall document any changes to these assumptions (including rationale) as part of the study effort.

3.1 Orbit

The GLIMR mission could be launched into either a geostationary transfer orbit (GTO) or directly into geostationary orbit (GEO). The GLIMR payload is designed to withstand up to six months, unpowered GTO transfer time into GEO final destination. The final GEO location shall be between 88°W to 108°W.

3.2 Design Life and Risk Classification

The GLIMR mission including ATS is classified as a Class D mission (per NPR 8705.4, Risk Classification for NASA Payloads). The mission design life is 1 year minimum, with a 2-year design life for any consumables and/or life limited items.

3.3 Environments

Environments depend on whether the approach includes the launch vehicle in a total Contractor-provided solution or utilization of a government-provided launch vehicle. If study recommends a government-provided launch vehicle, specific environmental requirements will be provided during the study that will encompass all available launch vehicles.

3.4 Deployments

Deployments for initial payload configuration are acceptable and shall be noted by the Contractor. For example, this might include protective aperture covers or release mechanisms for a system locked during launch. The Spacecraft shall retain any deployed hardware. No hardware shall be released into orbit under normal operations.

3.5 Spacecraft to Payload Interface Assumptions

Table 1 provides the assumptions that the Contractor shall use for the spacecraft to payload interfaces.

Table 1. Spacecraft to Payload Interface Assumptions

Identifier Category Spacecraft Interface Assumptions

GLIMR-1 Thermal Interface Payload Sensor Assembly is responsible for its own thermal management (survival heaters, operational heaters, thermal radiators, and thermal straps). Conductive heat transfer between sensor assembly and mounting interface may be restricted. The spacecraft must accommodate the sensor assembly radiator field of view to deep space. The payload’s power control unit (PCU) and digital encoder box (DEB) require spacecraft thermal management, see HSRD for details.

GLIMR-2 Mechanical Interface

Spacecraft will provide the mechanical interface(s) between the payload sensor assembly, PCU, and DEB that allow the payload to survive the launch environment and meet on-orbit jitter performance requirements.

GLIMR-3 Survival Heaters Spacecraft will provide dedicated, switched power feed for survival heaters from nominal 30 V DC power service(s).

Payload is responsible for providing its own survival heaters and control hardware (e.g., thermostats).

GLIMR-4 Operational Heaters

Spacecraft will provide dedicated, switched power feed for operational heaters from nominal 30 V DC power service(s). Payload is responsible for providing its own operational heater and control hardware.

GLIMR-5 Operational Power Service

Spacecraft will provide nominal 30 V DC power service(s) from spacecraft battery system, notionally 28 V to 32 V DC range of variation.

GLIMR-6 Power Service Overcurrent Protection

All switchable power services from the spacecraft will implement resettable overcurrent protection (e.g., circuit breakers)

GLIMR-7 Payload Thermal Monitoring

The payload will provide a set of spacecraft-read thermistors for thermal monitoring, regardless of the payload powered state.

GLIMR-8 Science Attitude The spacecraft will maintain a payload nadir-pointing attitude during science operations.

GLIMR-9 Science Data Management

Spacecraft will provide the data record for all payload science, and telemetry for periodic spacecraft downlinking via a spacecraft-provided RF Communication system.

GLIMR-10 Science Data Compression

Spacecraft will not implement any data compression on the instrument science data. The instruments may wish to implement data compression (lossy or lossless) algorithms prior to transfer to the spacecraft. The HSRD resource allocation are for overall data, regardless of whether it is compressed or uncompressed

GLIMR-11 Contamination Adequate precautions will be taken during Integration & Testing (I&T) to assure the on-orbit performance of the payload. Materials used will be selected to be consistent with meeting low outgassing rates. Cleaning operations will be performed as necessary. It should be assumed that the payload will be bagged when not in a Class 100,000 environment.

GLIMR-12 Electrical & Data Interfaces

Spacecraft will provide the following electrical interfaces:

1. +30 V primary power service(s) sized for payload power

2. SpaceWire data interfaces for payload command, telemetry, and science data

3. High-speed data interface sized for payload data rate (e.g., SpaceWire or RS-422)

4. Pulse Per Second (1 PPS) service(s) for time synchronization

5. Discrete commanding

6. +30 V launch lock interface

7. Survival heaters thermistor interface

GLIMR-13 Fault Protection The spacecraft provides system level monitors to safe and/or power off the payload.

GLIMR-14 Fault Isolation Faults should not propagate across the spacecraft/payload interface. Payload failure modes must be assessed both within the Payload and at this interface.

GLIMR-15 Absolute Time Sequence Commanding

The spacecraft provides an Absolute Time Sequence functionality to send pre-canned, time-tagged commands to the spacecraft and instruments. Used for time sensitive commanding or sequences that need to be executed outside of contact.

GLIMR-16 CCSDS

Compliance

The Spacecraft will be compliant with Consultative Committee on Space Data Systems (CCSDS) standards for communication from the spacecraft to the operations center.

4 WORK TO BE PERFORMED

4.1 Feasibility and Concept Studies

The following concept studies shall be performed by the Contractor and results included in the Concept Study Report Package:

1. Conduct a concept study considering different methods to achieve the defined pointing and on-orbit disturbance requirements.

a. Includes pointing accuracy, knowledge, stability, and jitter.

b. Define constraints (e.g., relative placement of inertial measurement sensors) that are required to meet requirements.

c. Define calibration methods, feasibility, and any required spacecraft functionality.

d. Perform on-orbit jitter analyses to show spacecraft disturbances at sensor assembly interface plane during:

i. Nominal science collection operations

ii. Worst case spacecraft operation mode (e.g., orbit raising, reaction wheel dumping)

2. Conduct a concept study considering different methods to achieve the defined launch environment requirements.

a. Perform spacecraft-to-payload integrated launch environment structural and dynamic analyses at all proposed spacecraft to payload interfaces to show positive margins to the structural launch environment requirements.

i. Launch vehicle environment interface specifications are either supplied by the Contractor as a full ATS approach or are supplied by the Government if the Government is providing the launch vehicle.

b. Define constraints (e.g., soft ride system, component isolators, additional support structures) that are needed to meet launch environment requirements and maintain positive structural margins.

c. Define proposed method of verifying the launch environment requirements (e.g., via analysis or test).

3. Develop ATS approaches to show that the proposed approach balances technical risk and cost while meeting the design requirements.

a. Include stowed and deployed configurations (where applicable), mass properties, power, thermal, and data rate.

b. Identify key and driving requirements, how they affect design, performance, cost, schedule, and risks.

c. Include analyses showing where performance and accommodation requirements can be or cannot be met.

d. Include different methods to achieve spectrum licensing and orbital slot authorization.

e. Define constraints (e.g., launch vehicle, required deployments, changes to requirements).

f. Include cost factors (e.g., a rough order of magnitude for the ATS approach(es)).

g. Include development plans and timeline including unique supply chain and/or long-lead procurement considerations.

5 REPORTING SCHEDULE

5.1 Kickoff

1. The Contractor shall support a Kickoff meeting within 2 weeks of the Authorization to proceed to provide a team introduction, summary of the proposed work for the study, initial identification of the key and driving requirements, and proposed study schedule.

2. The Contractor shall deliver a soft copy of the Kickoff chart package no later than 2 business days prior to the meeting. (CDRL-1)

3. The Kickoff meeting shall be conducted in-person and/or virtual for up to 4-hours duration and will be setup by the Government.

5.2 Bi-weekly Status Tag up

1. Bi-weekly teleconferences shall be scheduled to allow the Contractor to provide status, ask questions of clarification, and to request additional information. These meetings should also address any issues and open action items. (CDRL-2; CDRL-3)

2. The bi-weekly status meeting shall be conducted virtually for 30-minute duration and will be setup by the Government.

5.3 Concept Study Review

1. The Contractor shall present the results of the work performed for the concept study review. (CDRL’s 8-13)

2. The Contractor shall deliver a soft copy of the concept study review chart package no later than 5 business days prior to the meeting. (CDRL-5; CDRL-7; CDRL-8)

3. The concept study review meeting shall be conducted in-person and/or virtual for up to 8-hours duration and will be setup by the Government.

5.4 Concept Study Final Report

1. The Contractor shall deliver a detailed report capturing ATS final concept based on key and driving requirements, analysis results, cost, and schedule within 2 weeks following the Concept Study Review. (CDRL-6)

Pa ge of

C O

N

TR

A C

T D

A

TA

R

EQ

U

IR

EM

EN

T

LI

ST

(C

D R

L)

Th e

C on tra ct or s ha ll de liv er th e da ta p ro du ct s sp ec ifi ed in th e fo llo w in g ta bl e:

Ta bl e

2.

C on tr ac t D at a

R eq ui re m en t L is t

Id en tif ie r D el iv er ab le eq ui re m en t D el iv er ab le

Fo rm at

E st

. S ch ed ul e

C D

R L-

Ki ck of f P re se nt at io n

SO

W S ec tio n 5.

1.

Br ie fin g

C ha rts bu si ne ss d ay s pr io r t o

Ki ck of f

(A w ar d w ee ks

C D

R L-

Bi

-w ee kl y

St us ep or t

SO

W

S ec tio n

2.

fin g C ha rts o r em ai l Bi

-w ee kl y po

Ki ck of f M ee tin g

C D

R L-

Ac tio n

Ite m

L is t

SO

W S ec tio n

2.

Sp re ad sh ee t

Bi -w ee kl y po

Ki ck of f M ee tin g C

D R

L-

C on ce pt

S tu dy ev ie w

P re se nt at io n

SO

W S ec tio n fin g

C ha rts

An al ys es re su lts bu si ne ss d ay s pr io r t o C on ce pt

St ud y R ev w

(A w ar d m on th s)

C

D R

L-

C on ce pt

S tu dy F in al or t

SO

W S ec tio n

6.

or t

C on ce pt

S tu dy ev ie w w ee ks

R L-

R eq ui re m en ts om pl ia nc e As se ss m en t

M at rix o f t he

H os t S pa ce cr af t R eq ui re m en ts

Sp re ad sh ee t Aw ar d

W ee ks

Aw ar d

M on th s Aw ar d

M on th s

C D

R L-

Bu s

D is tu rb an a

IR

U a nd L

O S fre qu en cy re sp on se

(a m pl itu de a nd ph as e da ta ) f or e ac h bu s di st ur ba nc e so ur

[T

BD

Aw ar d

M on

R L-

IR

U P er fo rm an

IR

U p er fo rm an ce p ar am et er s

(la te nc y, s am pl in g ra te fil te rin g) oc um en t

Aw ar d

M on