Attachment A RST-INT-SOW-0078-.pdf

Effective Date: March 29, 2022

National Aeronautics and Space Administration

Goddard Space Flight Center Greenbelt, Maryland

RST-INT-SOW-0078, Revision -

Roman Space Telescope (RST), Code 448

Roman Space Telescope Vibration Isolation System (VIS)

Statement of Work (SOW)

GSFC CMO

March 29, 2022

Released

Roman Space Telescope Reviewed – Not Subject to Export Control

Roman VIS SOW RST-INT-SOW-0078, Revision -

Roman Space Telescope Vibration Isolation System (VIS) Statement of Work (SOW)

Review/Signature/Approval Page

Prepared by:

Joanne Baker

Approved by:

Doug Mc Guffey

Electronic Approval available on the Roman CM Tool i

Preface This document is a Roman Space Telescope (RST, or Roman) Configuration Management (CM)-controlled document.

Note: Prior to May 20, 2020, the project name was Wide Field Infrared Survey Telescope

(WFIRST).

For the purposes of configuration management, the prefixes “WFIRST” and “RST” are completely interchangeable. For example, RST-MGMT-PROC-0024 is the same as WFIRST-

MGMT-PROC-0024.

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

In this document, a requirement is identified by “shall,” a good practice by “should,” permission by “may” or “can,” expectation by “will,” and descriptive material by “is.”

Questions or comments concerning this document should be addressed to:

Roman Configuration Management Office Mail Stop 448 Goddard Space Flight Center Greenbelt, Maryland 20771 ii

Change History Log

Revision Effective Date Description of Changes (Reference the CCR & CCB/ERB Approval Date)

Revision - March 25, 2022 Initial Release of document per RST-CCR-0522 iii

Table of Contents

1 INTRODUCTION

1.1 Purpose

1.2 Scope

1.3 Related Documentation

1.3.1 Applicable Documents

1.3.2 Reference Documents

1.4 Description of Hardware

1.4.1 System for Vibration Environmental Negation Description (Baseline)

1.4.2 Ground Vibration Isolation System Description

1.4.2.1 Ground Vibration Isolation (Option 1)

1.4.2.2 Ground Vibration Isolation System Adjustability (Option 2)

1.4.2.3 Ground Vibration Isolation System Hard Stop and Load Transfer (Option 3)

2 MANAGEMENT, REPORTING, REVIEWS, AND DOCUMENTATION

2.1 Program Management

2.2 Reporting

2.3 Advanced Notifications

2.4 Reviews and Meetings

2.4.1 Kick-off Meeting

2.4.2 Design Conformance Review (DCR)

2.4.3 Pre-Environmental Review (PER)

2.4.4 Pre-Ship Review (PSR)

2.4.5 Technical Interchange Meetings (TIM)

2.4.6 Bi-Weekly Meetings

2.5 Documentation

2.6 Reserved

2.7 Existing Documentation and Analysis

3 DESIGN AND ANALYSIS

3.1 Interface Control Documentation

3.2 Drawing Package

3.3 Computer Models

3.4 Structural Analysis Report

3.5 Structural Finite Element Model

3.5.1 Finite Element Model Requirements

3.5.1.1 FEM Model Validation Plan

3.5.1.2 As-Built Model

3.6 Thermal Analysis Report

3.7 Thermal Model and Documentation

3.7.1 Thermal Model Requirements

3.7.1.1 Thermal Model Validation Plan

3.7.1.2 Reserved

3.7.1.3 As-Built Model

3.8 Reserved

3.9 User/Instruction Manual

iv

3.9.1 Restraint Mechanisms Procedures

4 HARDWARE PROCUREMENT/MANUFACTURING

4.1 General Requirements

4.2 Vibration Isolation Systems

4.2.1 Ground Vibration Isolation System (G-VIS)

4.2.2 System for Vibration Environment Negation (SVEN)

4.3 Connector Savers

4.4 Supporting Hardware

4.5 Ground Support Equipment

4.6 Engineering Development Units

4.7 Spare Units

5 PERFORMANCE VERIFICATION AND TEST

5.1 Verification Plan

5.2 Verification Test Procedures

5.3 Verification Test Reports

6 SAFETY AND MISSION ASSURANCE

6.1 General Requirements

6.2 Configuration Management

6.3 Ground Support Equipment Interfaces

6.4 Design Verification Requirements

6.4.1 Verification Requirements

6.4.2 Analysis, Trending, and Reporting of Test Data

6.4.3 Reserved

6.5 EEE Parts Requirements

6.5.1 General

6.5.2 Reserved

6.5.3 Parts Age Control

6.5.4 Reserved

6.6 Materials, Processes Requirements

6.6.1 Materials and Processes Control

6.6.2 Reserved

6.6.3 Reserved

6.6.4 Reserved

6.6.5 Detailed Requirements

6.6.5.1 Flammability, Offgassing, and Compatibility Requirements

6.6.5.1.1 Toxic Offgassing (NASA-STD-6016A Section 4.2.1.2)

6.6.5.1.2 Fluid Compatibility (NASA-STD-6016A Section 4.2.1.3)

6.6.5.1.3 Oxygen Compatibility (NASA-STD-6016A Section 4.2.1.4)

6.6.5.1.4 Electrical Wire Insulation Materials (NASA-STD-6016A Section 4.2.1.5) 21

6.6.5.1.5 Thermal Vacuum Stability (NASA-STD-6016A Section 4.2.3.6)

6.6.5.1.6 Glycols (NASA-STD-6016A Section 4.2.3.9)

6.6.5.2 Reserved

6.6.5.3 Reserved

6.6.5.4 Special Materials Requirements

6.6.5.4.1 Fastener Installation (NASA-STD-6016A Section 4.2.6.6) v

6.6.5.4.1.1 Liquid Locking Compounds (NASA-STD-6016A Section 4.2.6.6.1) . 21

6.6.5.4.2 Silver-Plated Fasteners (NASA-STD-6016A Section 4.2.6.6.2)

6.6.5.4.3 Contamination Control (NASA-STD-6016A Section 4.2.6.7)

6.6.5.4.4 Packaging (NASA-STD-6016A Section 4.2.6.8)

6.6.5.4.5 Shelf-Life Items

6.6.5.5 Reserved

6.6.6 Materials Procurement Requirements

6.7 Contamination Control Requirements

6.7.1 Contamination Control Plan

6.7.2 Surface Cleanliness

6.7.3 Thermal Vacuum Bakeouts

7 HANDLING, STORAGE, PACKAGING, PRESERVATION, AND DELIVERY

APPENDIX A ABBREVIATIONS AND ACRONYMS

List of Figures

Figure 1. The SVEN provides isolation between the chamber Dome hardware and the OLAFS. . 3 Figure 2. Block diagram of the SVEN in relation to the TVAC facility and GSE Figure 3. TVAC Chamber Test Flow Figure 4. The GVIS provides isolation between the L-GESHA (on the chamber floor) and the

TVSS + IPA

Figure 5. Block diagram of the GVIS in relation to the TVAC facility, flight hardware, and GSE.

1 INTRODUCTION

1.1 Purpose

The Roman Space Telescope (RST or Roman) is a mission responding to the 2010 National Research Council New Worlds, New Horizons (NWNH) Astronomy and Astrophysics Decadal Survey top priority recommendation in the large space mission category. The science program includes two dedicated investigations to tackle outstanding questions in dark energy research and exoplanet exploration, and includes a substantial General Observer program to enable targeted investigations of astrophysical phenomena to advance other goals from the Decadal Survey. The system undergoes extensive testing throughout integration to ensure proper alignment before launch, including an Integrated Payload Assembly (IPA) Thermal Vacuum (TVAC) optical test.

In order to properly conduct the test, two Vibration Isolation Systems (VIS) are required. This document defines the work to be performed by the Contractor in the design, development, fabrication, and delivery for both the System for Vibration Environment Negation (SVEN) (Baseline) and the Ground Floor VIS (G-VIS) (Option 1). This document also defines the design, development, fabrication, and delivery for a leveling / alignment system (Option 2) and a rigid mount / load transfer system (Option 3) to be incorporated into the G-VIS.

1.2 Scope

The contractor shall provide the facilities, personnel, services, tools, equipment, and materials necessary to design, analyze, manufacture, test, and deliver the hardware and data in accordance with the requirements of this SOW and the documents referenced herein.

This SOW defines the contractor tasks, deliverables, responsibilities, and schedule, either within this document or by reference. More details for the Deliverable Items List and Schedule (DILS) are contained in RST-INT-LIST-0208.

The contractor shall generate a matrix listing each section in this statement of work reflecting either compliance or non-compliance. (DIL #1) Areas of non-compliance need to be addressed by the contractor showing how they plan to meet the requirement(s) or why it will remain non-compliant.

1.3 Related Documentation

In the event of a conflict between the SOW and the specification, the SOW shall take precedence.

The latest versions of all documents below shall be used unless otherwise specified in this SOW.

Roman documents can be obtained from the Roman CM Tool.

1.3.1 Applicable Documents

The following documents are referenced within this document and are directly applicable or contain policies or other directive matters that are binding for the contents of this document. In the event of conflict between an Applicable Document and the content of this document, the Roman Project Configuration Change Board has the final authority for conflict resolution.

Document Number Title RST-INT-SPEC-0315 Roman Space Telescope Vibration Isolation System (VIS)

Performance Specification (Spec) RST-INT-LIST-0208 Roman Space Telescope Vibration Isolation System (VIS)

Deliverable Items List and Schedule (DILS)

RST-SMA-REQ-0032 Roman Mission Assurance Requirements

541-PG-8072.1.2C Goddard Space Flight Center Fastener Integrity Requirements

NASA-STD-6016A Standard Materials and Processes Requirements for Spacecraft

GSFC EEE-INST-002 Instructions for EEE Parts Selection, Screening, Qualification, and Derating

GSFC-STD-1000G Rules for the Design, Development, Verification, and Operation of Flight Systems

GSFC-STD-8002 GSFC Standard Quality Assurance Requirements for the Use of Water Soluble Flux

NASA-STD-6008 NASA Fastener Procurement, Receiving Inspection, and Storage Practices for Spaceflight Hardware

1.3.2 Reference Documents

The following documents are referenced herein and amplify or clarify the information presented in this document. These documents are not binding on the content of this document.

Document Number Title

RST-SMA-LIST-0027 Roman MAR Applicability Matrix

ASTM E-595-15 Standard test method for total mass loss and collected volatile condensable materials from outgassing in a vacuum environment

MSFC-SPEC-445A Adhesive Bonding, Process and Inspection, Requirements for

NASA-STD-5005 NASA Technical Standards System

1.4 Description of Hardware

1.4.1 System for Vibration Environmental Negation Description (Baseline) The System for Vibration Environmental Negation System, henceforth known as “SVEN,” will be used to provide structural support for the Optical Large Aperture Flat System (OLAFS) and adaptor plate, and vibration isolation between the OLAFS / adaptor plate assembly and the Upper Support Frame (USF). A single unit of the SVEN assembly may be referred to as a Vibration Environment Negation Unit, or “VENU”. The SVEN shall be comprised of three

VENUs, which can consist of one or more separate pieces of hardware that provide isolation to the OLAFS, and will be mounted to the GSFC-designed adaptor plate and to the USF. The entire set shall be considered one System for Vibration Environmental Negation.

A close-up of the SVEN and surrounding hardware can be seen in the images below. The SVEN is represented with three teal boxes, suspended from the light grey USF and connected to the blue adaptor plate supporting the dark grey OLAFS.

Figure 1. The SVEN provides isolation between the chamber Dome hardware and the OLAFS.

SVEN

OLAFS

USF

Adaptor Plate

Z

X

Y

Figure 2. Block diagram of the SVEN in relation to the TVAC facility and GSE.

1.4.2 Ground Vibration Isolation System Description

The Ground Floor Vibration Isolation System, henceforth known as “Ground VIS” or “GVIS,” will be used to provide vibration isolation between the Lower GESHA and the TVSS. A single unit of the GVIS assembly may be referred to as a Ground Vibration Isolation Unit, or “GVIU”.

The GVIS shall be comprised of three GVIUs; each GVIU can consist of one or more separate pieces of hardware that provide structural support and isolation to the Unit Under Test (UUT), which consists of the Integrated Payload Assembly (IPA) and test support equipment. The entire set will be considered one Ground Vibration Isolation System.

Figure 3. TVAC Chamber Test Flow

1.4.2.1 Ground Vibration Isolation (Option 1)

The main function of the GVIS is to provide isolation to the Unit Under Test during TVAC testing. This system can consist of one or more isolator at each of three locations, as seen in Figure 4. The GVIS will minimize noise from the chamber and any outside sources during optical testing of the IPA.

1.4.2.2 Ground Vibration Isolation System Adjustability (Option 2) The GVIUs may require small adjustment capabilities in order to level the IPA. These adjustment features will be used to adjust the Unit Under Test level to gravity as needed during integration and test activities in the SES. This height adjustment feature must be in line with the isolation load path and must be capable of functioning while supporting the full load of the UUT, as adjustments may be required after transferring the UUT mass onto the isolated load path. This feature will be only procured as an add-on to Option 1, not as a separate entity.

1.4.2.3 Ground Vibration Isolation System Hard Stop and Load Transfer (Option 3) A safe harbor location is required such that the UUT can be set down in the test chamber on a rigid and stable surface, in order to facilitate test hardware preparations. This functional requirement can be achieved through several different modular packaging methods, including but not limited to a redundant isolator lockout or a separate rigid load path. The mass of the UUT must be transferrable from the rigid load path to the isolated load path in a safe, controlled, and measurable manner. This feature will only be procured as an add-on to Option 1 + Option 2, not as a separate entity.

A close-up of the GVIS and surrounding hardware can be seen in the images below. The GVIS is represented with three yellow cylinders representing the envelope of available volume, sitting on the gold L-GESHA and supporting the light grey TVSS.

Figure 4. The GVIS provides isolation between the L-GESHA (on the chamber floor) and the

TVSS + IPA.

Figure 5. Block diagram of the GVIS in relation to the TVAC facility, flight hardware, and GSE.

GVIS

L-GESHA TVSS

Z

X

Y

2 MANAGEMENT, REPORTING, REVIEWS, AND DOCUMENTATION

2.1 Program Management

The contractor shall designate a single individual who will be given full responsibility and authority to manage and administer all phases of the work specified by the contract and ensure that all objectives are accomplished within schedule constraints.

The contractor shall designate and identify by name a single individual to serve as a point of contact with the NASA/GSFC Contracting Officer’s Representative (COR) for all technical aspects of the Vibration Isolation System (VIS) contract.

The contractor shall establish and apply a program control system for managing all resources, controlling schedules, managing all engineering, manufacturing and procurement activities, configuration management, Quality Assurance, and documentation control.

2.2 Reporting

The contractor shall prepare and present to the NASA/GSFC COR bi-weekly technical status reports via telecon and a monthly written report. (DIL #2) The monthly report shall be a summary presentation of the period's progress to include topics such as schedule overview and updates since the previous status, accomplishments, technical performance measures (e.g. mass and power), status of key milestones, risks, problem areas, challenges/issues, quality assurance issues/status, and activities on-going and planned. The contractor shall generate a list of significant milestones that will enable the NASA/GSFC COR to ascertain program progress.

(DIL #3)

2.3 Advanced Notifications

The contractor shall notify the NASA/GSFC COR at least seven (7) calendar days in advance of all mandatory hardware inspections, test activities, TIM’s, and deliveries at either the contractor’s or a subcontractor’s facility to allow timely participation by the NASA/GSFC Quality Assurance representative. (DIL #4) Event specific notification requirements (such as failures, anomalies, etc.) are included in the appropriate sections.

2.4 Reviews and Meetings

2.4.1 Kick-off Meeting

The Contractor shall organize and hold a Kick-off Meeting either virtual or at the Contractor’s facility prior to any activity identified in this SOW. (DIL #5)

The Contractor shall provide to the NASA/GSFC COR a Kick-off Presentation Package and all other required deliverables. (DIL #6) The Kick-off Meeting shall address program management and quality assurance activities outlined in this SOW, as well as the performance and environmental requirements outlined in the Vibration Isolation System (VIS) specification in sufficient detail to demonstrate understanding of contract requirements. At a minimum, the presentation package should cover the following areas:

• Program Management

• Quality Assurance

• G-VIS Design Description

• SVEN Design Description

• Preliminary Interface Control Documents

• Facilities

• Qualification Verification Plan and Procedure

• Mechanical Analysis with Boundary Conditions

2.4.2 Design Conformance Review (DCR)

The contractor shall organize and present a Design Conformance Review to a GSFC Review Team at the contractor’s facility prior to the manufacturing program. (DIL #8) The contractor shall provide to the NASA/GSFC COR a Design Conformance Review Presentation Package and all other required deliverable data prior to the review. (DIL #9) The Design Conformance Review shall address all program management, design, drawings, analysis, manufacturing, test, and quality assurance activities outlined in this SOW and the Roman VIS Specification RST- INT-SPEC-0315 in sufficient detail to ensure that the proposed design conforms to all requirements and is ready to move forward with final design work. At a minimum, the design package should cover the following areas:

• Program Management

• Quality Assurance

• Electrical, Mechanical, and Environmental specifications

• Parts, including stress analysis and radiation hardness assessment

• Detailed architectural block diagrams for the different deliverable units

• Fabrication, Assembly, and Inspection Flow plan

• Facilities

• Verification Test Plan (Including Performance Test Description)

• Materials and Processes

• Contamination Control (for items sensitive to contamination or with explicit surface cleanliness or outgassing requirements)

• Mechanical/Structural analyses

• Thermal Analysis

• Electrical Worst-Case analyses (if applicable)

• Failure Modes Effects Criticality Analysis

• Verification Matrix (per Section 6.4.1)

Review minutes shall be prepared and, as a minimum, include attendance, action items, action item accomplishment responsibility and agreements. All items shall be in sufficient detail to be self-explanatory. A Design Conformance Review Report shall be prepared following the review and, as a minimum, contain meeting notice, agenda, review meeting minutes described above and responses to all recommendations and action items. (DIL #10)

2.4.3 Pre-Environmental Review (PER)

The contractor shall organize and conduct a Pre-Environmental Review (PER) at the contractor’s facility before the environmental test program begins. (DIL #14) This presentation shall demonstrate overall conformance of the requirements specified in the Roman Vibration Isolation System (VIS) Specification RST-INT-SPEC-0315 and this Statement of Work for this phase of the procurement. This presentation shall cover programmatic, technical, test and verification, and quality assurance topics, and address any changes made to the Verification Matrix since DCR. (DIL #15). This review shall also provide an opportunity to review test plans and procedures and all analyses required to approve the testing of the hardware.

2.4.4 Pre-Ship Review (PSR)

The contractor shall hold a Pre-Ship Review at the contractor's facility at the completion of verification tests and prior to the shipment of each hardware item to NASA/GSFC. (DIL #16) This presentation shall demonstrate completion of all activities required for delivery of any hardware deliverable item to NASA/GSFC, and note any activities that are incomplete. In particular, the contractor shall present the completed verification matrix that shows verification of all requirements and presents actual data (results of tests or analyses) where applicable. (DIL #17). Any requirements that are not met shall be identified in the Deviations/Waivers etc. list and discussed with NASA/GSFC during the review.

An End Item Data Package (EIDP) shall be made available for review during pre-ship reviews for each of the different hardware deliverables. (DIL #18) This package shall also be delivered with each end item with the level of detail required of that item. The package should be comprised of, but not limited to, the following data:

• The deliverable item name, serial number, part number, and classification status (e.g., flight, non-flight, ground support).

• Appropriate approval signatures (e.g., contractor’s quality representative, product design lead, government Representative)

• Work orders for the final assembly and associated tests

• As-Built vs. As Designed Parts List, (EEE parts, includes serialization/revisions)

• As-Built Final Drawing Package (including rework instructions, if any)

• Problem/anomaly reporting (complete copies of report)

• Deviations/Waivers/shortages/open items/non-conformances and their dispositions, with supporting rationale

• Status of all action items from previous reviews

• Class I MRBs (complete copies of reports)

• List of As-Built Materials and Processes used

• Achieved surface cleanliness and outgassing rate data (when applicable)

• Log of total operating time and failure-free operation, separated by primary/redundant sides, if any

• List and status of all identified Life-Limited Items

• Trended Critical Parameters Data (when applicable)

• Verification matrix (including environmental), test data and reports

• Photograph Documentation (Pre and Post conformal coating, Pre-Closure and Closed)

• Certificate of Conformance, with management signature

• End Item Inspection Report

• As-Built Configuration List

• Mate/Demate log

• Printed circuit board coupon results (when applicable)

• Storage and Transportation Plans and Requirements

2.4.5 Technical Interchange Meetings (TIM)

The contractor shall plan for and facilitate up to three (3) informal, face-to-face technical interchange meetings to be held at the contractor facilities. (DIL #19) These TIMs shall support review and coordination of technical issues including, but not limited to, parts, test plans, test procedures, software changes, design modifications, and design analyses.

2.4.6 Bi-Weekly Meetings

The Contractor shall report technical and programmatic progress in bi-weekly meetings with the

NASA/GSFC COR.

2.5 Documentation

The contractor shall ensure the generation and delivery of all documentation as called for in the contract (Section B Table) and listed in the DILS document, RST-INT-LIST-0208.

In addition to that documentation specifically called for in the contract, upon request by the NASA/GSFC COR, the contractor shall make available a copy of any document or data generated during this contract performance for review by GSFC at either the contractor's facility or via the internet. This includes, but is not limited to, technical reports and memorandums, drawings, schematics, studies, analyses, parts and materials data, test data, alerts, etc.

2.6 Reserved

2.7 Existing Documentation and Analysis

If analysis or documentation exists already for the unit that satisfies the requirements within the VIS Specification, RST-INT-SPEC-0315, and the descriptions in Section 3, then the analysis or documentation may not need to be redone, and the requirement can be satisfied by similarity and with the delivery of the previous analysis/documentation to the NASA/GSFC COR.

3 DESIGN AND ANALYSIS

The contractor shall perform analyses of the technical and environmental requirements specified in the Roman VIS Specification (RST-INT-SPEC-0315) to ensure compliance of the hardware fabrication and to assemble the documentation necessary to ensure its usability by NASA/GSFC users. Previous analyses may be submitted for the items below per Section 2.7.

3.1 Interface Control Documentation

The Contractor shall provide the following documents (DIL #20):

• Mechanical Interface Control Document (MICD), including physical characteristics, mounting interface, outline drawing, thermal coatings on surfaces.

• Electrical Interface Control Document (EICD), including connector identification, connector pinouts, detailed description of each signal, interface circuits, command description, command sequencing/timing, data (telemetry) description (Data Interface Control Document could be a part of this EICD or a standalone document).

3.2 Drawing Package

The contractor shall provide a drawing package that includes, but is not limited to: (DIL #21)

ELECTRICAL: assembly and interface drawings (board level schematics available on request) MECHANICAL: assembly and interface drawings

3.3 Computer Models

The contractor shall deliver the following computer models for both the SVEN and the G-VIS

(DIL #23).

a) A Computer-Aided Design (CAD) file

b) A Mechanical Model in STEP file format

3.4 Structural Analysis Report

The purpose of the structural analyses is to demonstrate compliance with the mechanical/structural design and test requirements. Structural analyses verify the structural integrity of the hardware by assessing the size and location of applied loads, load paths, and critical failure modes. A Structural Analysis shall be provided for the G-VIS to ensure the capability to support flight hardware, and for the SVEN to ensure the capability to support load hanging above flight hardware. (DIL #24) The analysis shall also address loads on any lift points as well. The effects of any thermal inputs shall be reflected in the analyses as appropriate. This analysis shall include venting analyses for applicable components (such as thermal blankets and contamination enclosures) susceptible to pressure loadings to verify that positive strength margins exist at loads equal to the maximum pressure differential during TVAC testing. The results of these analyses shall be summarized in a contractor format Structural Analyses Report that will be provided to the NASA/GSFC COR for review.

3.5 Structural Finite Element Model

Contractors shall submit finite element models and model documentation that describes the following: (DIL #25)

1. Full physical models including date of creation

2. A list of element, node, property, and material identification (ID) numbers; numbering range of nodes and elements shall be in the range of 37,000,001-37,499,999 for G-VIS and 37,500,001-37,999,999 for SVEN

3. A description of the nonstructural mass represented on each property card

4. A description of units

5. A description of the local reference coordinate system

6. The results demonstrating compliance to the following model validity checks

• Equilibrium/grounding: Rigid body equilibrium/grounding checks using the NASTRAN GROUNDCHECK case control statement to assess the presence of mechanisms, over-constraints, etc. for all six model degrees-of-freedom for the various constraint sets.

• Free-free dynamics (showing rigid body modes): In the unconstrained condition, the model should have six rigid body modes with frequencies below 0.005 Hz, with a goal of 0.0005 Hz, and the ratio of the lowest elastic mode frequency and the highest rigid body mode frequency should be greater than 100, with a goal of 1000.

• Unit gravity loading (each axis): With the model constrained at appropriate interfaces, and 1G inertial loadings applied separately in three orthogonal directions, the sum of constrained forces in the loading direction should be within 0.01% of the model weight. The magnitude of the sums orthogonal to the loading direction should be less than 1.0 N.

• Enforced displacement/rotation (all 6 degrees-of-freedom): Grounding forces will be determined by applying unit rigid body displacements and rotations to a stiffness matrix of the unsupported model, and determining the resultant grid point forces. Full capability of NASTRAN GROUNDCHECK case control can be used to determine grounding forces and moments. Grounding forces should be less than 1.0 N, and moments less than 0.5 N-m.

• Matrix Conditioning Checks: The maximum ratio of any diagonal term to its corresponding term of the triangular factor matrix should be less than 5.0E7. The evaluation should be performed in a static decomposition with restraints applied to remove rigid body modes. A negative value of NASTRAN Param, Bailout, and forcing program execution with near singularities will not be used.

In NASTRAN static analysis (for instance unit gravity and thermal load checks), epsilon is a measure of the error in the load predicted from the product of stiffness matrix and solution set displacement compared to the actual input load vector

. Epsilon should be less than 1.0E-8.

• Unit increase temperature: When thermal stress assessment are performed, model checks are needed to ensure proper results. Remove all rigid elements (if not assigning thermal expansion values), equate all material coefficients of thermal expansion and reference temperatures, assign a uniform temperature field and allow for expansion/contraction of the model in all 6 degree-of-freedom. Results should show minimal element force generation and uniform expansion/contraction.

7. Mass Properties (CG location, Inertias, and total model mass)

Contractors shall submit finite element models that adhere to the following:

1. Model submitted as a MacNeal Schwendler Corporation (MSC)/ NASA Structural Analysis (NASTRAN) data deck, version 2016 compatible

2. All model property and material cards have descriptive names

3. Models submission is "full" model with no symmetry assumptions made to reduce model size

4. Model includes no "Super Elements" / Craig-Bampton reductions

5. Model submission includes an explicit Single Point Constraint set

6. Until actual hardware mass properties are verified and final, the finite element model is adjusted to the allowable mass for each subsystem and component

3.5.1 Finite Element Model Requirements

3.5.1.1 FEM Model Validation Plan

The contractor shall develop and execute a FEM Model Validation Plan with concurrence from the NASA/GSFC COR (DIL #22).

3.5.1.2 As-Built Model

The contractor shall incorporate all applicable test results in an as-built model (DIL #25).

The contractor shall develop and deliver the as-built model that is validated (per the FEM Model Validation Plan, DIL #22) and calibrated from test(s), upon delivery of the G-VIS and SVEN

(DIL #25).

3.6 Thermal Analysis Report

The contractor shall provide a worst case thermal analysis that illustrates that the device and/or the electronic parts junction temperatures are within the Electrical, Electronic, and Electromechanical (EEE) EEE-INST-002 (DIL #26) de-rated operational temperature limits when subjected to the boundary conditions specified in the VIS Specification (RST-INT-SPEC- 0315). This analysis shall be performed with the components operating at their maximum expected power dissipations. All analysis results shall be summarized in a thermal analyses report, to be provided for review as per the contract schedule. This report shall contain a comprehensive list of each component’s maximum expected power dissipation, maximum case temperature, theta JC, maximum junction temperature, and de-rated operational temperature limit. This report shall also include temperature and power predictions at the environment extremes listed in the VIS Specification (RST-INT-SPEC-0315). Additionally, this report shall contain a thorough description of the computer models (or reference to the documentation required from section 3.7 (Thermal Model and Documentation) of this document) and the assumptions that were used to perform the analysis including boundary conditions, surface finish thermo-optical properties, interface conductances.

3.7 Thermal Model and Documentation

The contractor shall provide reduced Thermal Math Models (TMMs) for the G-VIS and SVEN with less than 50 nodes per box, in Thermal Desktop/SINDA format or another format pre-approved by the Roman Thermal group (DIL #27).

The Thermal model documentation shall include:

• Labeled figures (drawings, cross-sections, etc) in sufficient detail to show all critical components and their relative locations within the G-VIS and SVEN

• List of all critical components, their material composition and relevant properties (density, specific heat, conductivity, etc).

• Listing of other relevant modeling assumptions (boundary conditions, interface conductances, thermo-optical properties, etc)

• Listing of component thermal dissipations for all operational and survival modes over which the hardware is intended to operate

If the contractor does not have the project-compatible software to create TMMs, then the contractor shall provide sufficient detailed information such that GSFC can create the TMMs. Documentation shall be provided including detailed descriptions of all aspects of the model necessary for GSFC to run and/or recreate the TMMs.

3.7.1 Thermal Model Requirements

3.7.1.1 Thermal Model Validation Plan

The contractor shall develop and execute a Thermal Model Validation Plan with concurrence from the NASA/GSFC COR (DIL #22).

3.7.1.2 Reserved

3.7.1.3 As-Built Model

The contractor shall incorporate all applicable test results in an as-built model (DIL #27).

The contractor shall develop and deliver the as-built model that is validated (per the FEM Model Validation Plan, DIL #22) and calibrated from test(s), upon delivery of the G-VIS and SVEN

(DIL #27).

3.8 Reserved

3.9 User/Instruction Manual

3.9.1 Restraint Mechanisms Procedures

The contractor shall deliver procedures to release and re-furbish locks for the G-VIS and SVEN, if applicable. (DIL #31)

4 HARDWARE PROCUREMENT/MANUFACTURING

4.1 General Requirements

The contractor shall either procure or manufacture all components required to assemble, integrate, and test the G-VIS and SVEN to support the delivery dates as called for in the contract (Section B Table) and listed in the DILS document, RST-INT-LIST-0208.

The contractor shall assemble the quantities of G-VIS and SVEN hardware described below. The contractor shall provide a Fabrication, Assembly, and Inspection Flow plan at the DCR that includes a step-by-step procedure that describes the method of fabrication, assembly, and inspection from piece parts to the completely assembled G-VIS and SVEN.

4.2 Vibration Isolation Systems

4.2.1 Ground Vibration Isolation System (G-VIS)

The contractor shall provide the following hardware to meet the requirements of the Roman VIS Specification (RST-INT-SPEC-0315).

a) One Ground Vibration Isolation System (G-VIS) consisting of three GVIUs (DIL #49) which will isolate the Integrated Payload Assembly (IPA) Test Configuration.

The contractor shall include in the proposal the cost to purchase all hardware including all supporting hardware.

4.2.2 System for Vibration Environment Negation (SVEN)

The contractor shall provide the following hardware to meet the requirements of the Roman VIS Specification (RST-INT-SPEC-0315).

b) One System for Vibration Environment Negation (SVEN) consisting of three VENUs (DIL #50) which will isolate the Optical Large Aperture Flat System (OLAFS) and adaptor plate assembly.

The contractor shall include in the proposal the cost to purchase all hardware including all supporting hardware.

4.3 Connector Savers

GSE Unit(s) shall be tested with connector savers to minimize mates and de-mates. Connector savers shall be delivered with the Ground Vibration Isolation System (DIL #51) and the System for Vibration Environment Negation (DIL #52).

4.4 Supporting Hardware

The Contractor shall provide the following supporting hardware:

• One set of the mating half of the external connectors for each connector, plus two additional sets per contract delivery schedule for G-VIS (DIL #53) and SVEN (DIL #54)

• Electrostatic Discharge (ESD) protective caps, as applicable, for G-VIS (DIL #53) and

SVEN (DIL #54)

• Closeout caps for test connectors, as applicable, for G-VIS (DIL #53) and SVEN (DIL #54)

• Engineering development unit or engineering test unit, as applicable, for G-VIS (DIL #53) and SVEN (DIL #54)

4.5 Ground Support Equipment

Ground support equipment (GSE) required for installation and use of the G-VIS and SVEN units at GSFC shall be recommended by the Contractor and agreed to with Roman for G-VIS (DIL #55) and SVEN (DIL #56).

Such GSE may be required for:

a) Storage/Handling of G-VIS and SVEN

b) Coordination of interfaces (i.e. drill fixtures, etc.)

c) Installation of G-VIS and SVEN

d) Testing of G-VIS and SVEN

Any GSE delivered with the Roman G-VIS and SVEN units falls under DIL #55 – Ground Floor Vibration Isolation System GSE(s) – and DIL #56 – System for Vibration Environment Negation GSE(s).

4.6 Engineering Development Units

No engineering development units are requested as part of this procurement.

4.7 Spare Units

No spare units are requested as part of this procurement.

5 PERFORMANCE VERIFICATION AND TEST

5.1 Verification Plan

A Verification Plan shall be generated by the contractor to describe the details of how the analyses, inspections, and verification tests identified in the Roman Vibration Isolation System (VIS) Specification RST-INT-SPEC-0315 will be performed. (DIL #33) Verification tests shall demonstrate the item meets all of the specified performance requirements over the specified range of environments, measure performance parameters and reveal inadequacies in manufacturing and assembly such as workmanship or material problems. Any requirement that exceeds previous qualification test data shall be presented to the NASA/GSFC COR as part of the planning process for evaluation and a possible delta qualification test.

The plan shall state the purpose of each test, state acceptance criteria, describe in detail the test method, set up, instrumentation, data analysis methods (if applicable), and give the sequence of the tests. The plan shall include a verification matrix summarizing how all requirements are verified (analysis, inspection, test, per the definitions in the Spec.), and listing all tests that will be performed on the G-VIS and SVEN.

This plan shall be a contractor controlled document and indicate all changes made after the initial approval by the NASA/GSFC COR. After Verification Plan approval, no changes shall be made without written NASA/GSFC COR approval.

If any individual test plans are created in addition to the master Verification Plan, such as for Thermal Vacuum testing, those plans shall also be provided. (DIL #34)

5.2 Verification Test Procedures

The contractor shall generate Verification Test Procedures and provide them to the NASA/GSFC COR. (DIL #35) The verification procedures shall be step-by-step instructions for performing tests outlined by the Verification Test Plan. The procedures shall define the environmental conditions for the tests, required equipment and facilities, test constraints, use of diagnostic or performance test software, operating conditions, tolerance on all input stimuli, data to be recorded and pass/fail limits.

Verification Test Procedures shall be contractor controlled documents and indicate all changes made after the initial release for review to NASA. The Thermal Vacuum Test Procedure shall include the contents listed in Section 6.7.3 for the Chamber Configuration.

5.3 Verification Test Reports

The contractor shall generate Verification Test Reports. (DIL #36) These reports shall document the results of each test that was performed, what test levels were achieved, what performance requirements were verified, what anomalies were seen, and how they were resolved.

6 SAFETY AND MISSION ASSURANCE

6.1 General Requirements

The Contractor shall comply with the applicable safety and mission assurance requirements documented in the Roman Mission Assurance Requirements (MAR) (RST-SMA-REQ-0032):

MAR-009, MAR-020, MAR-023, MAR-033, MAR-039, MAR-043, MAR-081, MAR-146,

MAR-149, MAR-190, MAR-191, and MAR-198. All corresponding deliverables shall be delivered as described in MAR Data Item Descriptions (DIDs) (DIL #57

The work activities and operations of the contractor, subcontractors, and suppliers are subject to evaluation, review, survey, audit, and inspection by NASA/GSFC representative.

6.2 Configuration Management

The contractor’s Configuration Management (CM) system (available for review on request) shall control the design and hardware/software by means of drawings, specifications, and other documents and ensure all applicable changes are reviewed in a systematic manner to determine the validity and impact on performance, schedule and cost. The contractor’s Configuration Management system shall have a change classification and impact assessment process that ensures Class I changes are forwarded to the CO for approval prior to release/incorporation.

(DIL #38) Class I changes are defined as changes that affect form, fit, function, external interfaces, or requirements as stated within this document and the VIS specification.

All other changes are considered to be Class II changes and shall be controlled and dispositioned by the contractor. All Class II changes shall be provided monthly to the NASA/GSFC COR for review purposes. (DIL #39) NASA/GSFC reserves the right to review all Class II changes for technical content to ensure the proper classification has been assigned. Any flight item that is found to be non-compliant with the quality, workmanship and performance requirements of the contract shall be dispositioned via a waiver or Materials Review Board (MRB), unless the affected item is reworked to restore compliance or is replaced with a fully compliant item. The contractor shall submit Waivers and MRBs to the NASA/GSFC COR for final approval.

A contractor QA representative shall be a member of the Configuration Control Board. The QA activities shall be defined in the Configuration Management Plan and described in detail in the QA Plan. Related portions of the plans shall be cross-referenced.

6.3 Ground Support Equipment Interfaces

Mechanical and electrical ground support equipment (GSE) and associated software that directly interface with flight deliverable items shall be assembled and maintained to mitigate potential risk to flight hardware. Parts and materials selection and reporting requirements are exempted as long as deliverable flight item contamination requirements are not compromised.

6.4 Design Verification Requirements

6.4.1 Verification Requirements

The contractor shall implement a program to verify all requirements specified in the Roman Vibration Isolation System (VIS) Specification (RST-INT-SPEC-0315).

The contractor shall provide a verification matrix defining the method of verification for each specific requirement of the Roman Vibration Isolation System (VIS) Specification (RST-INT- SPEC-0315), per Section 5.1 of this SOW. (DIL #33)

In-process production evaluation tests and environmental stress screening tests shall also be considered to be verification tests.

6.4.2 Analysis, Trending, and Reporting of Test Data

The contractor shall properly record, maintain and analyze test information during the normal test program to assess performance and to aid in the identification and analysis of hardware failures and problems.

6.4.3 Reserved

6.5 EEE Parts Requirements

6.5.1 General

The contractor shall meet the EEE Parts requirements per section 10 of the Roman MAR, RST-

SMA-REQ-0032.

6.5.2 Reserved

6.5.3 Parts Age Control

Parts more than 5 years old, comparing the part Lot Date Code (LDC) to the Project DCR date, require NASA/GSFC COR approval for use. (DIL #42) Parts drawn from inventory having lot date codes older than 5 years, shall be reviewed by the Government to determine the need for re-screen. Parts stored in conditions where moisture or ESD are not controlled shall not be used.

Contractors shall present justification with inspection and test requirements.

6.5.4 Reserved

6.6 Materials, Processes Requirements

6.6.1 Materials and Processes Control

Materials, processes, and lubrication approval by the Roman Materials and Processes Engineer (MPE) is required for each usage or application in spaceflight hardware with criteria, including Data Deliverables, as follows. The contractor shall ensure the relevant requirements are flowed to vendors.

All Materials and Processes (M&P) shall be defined by standards and specifications, and be selected from government, industry, and subcontractor specifications and standards. There is a preference for the use of active government or industry specifications.

The MPE shall be a voting member of subcontractor M&P Control Boards, if established.

6.6.2 Reserved

6.6.3 Reserved

6.6.4 Reserved

6.6.5 Detailed Requirements

Detailed Requirements in Section 4.2 of NASA-STD-6016A are applicable to all Roman flight hardware, except as specified below. The contractor shall ensure the relevant requirements are flowed to vendors.

6.6.5.1 Flammability, Offgassing, and Compatibility Requirements

6.6.5.1.1 Toxic Offgassing (NASA-STD-6016A Section 4.2.1.2)

This section is not applicable for this component.

6.6.5.1.2 Fluid Compatibility (NASA-STD-6016A Section 4.2.1.3) Heritage usage may be solely considered when assessing compatibility.

6.6.5.1.3 Oxygen Compatibility (NASA-STD-6016A Section 4.2.1.4) This section is not applicable for this component.

6.6.5.1.4 Electrical Wire Insulation Materials (NASA-STD-6016A Section 4.2.1.5) In addition to being included in M&P Lists, wire insulation will be the reviewed by the Parts Control Board as defined in Safety and Mission Assurance’s requirements and plans.

6.6.5.1.5 Thermal Vacuum Stability (NASA-STD-6016A Section 4.2.3.6) Nonmetallic materials shall meet outgassing requirements defined in the Roman MAR, Paragraph 12.2 and DID 11-3. A Contamination Control Plan shall define the approach to mitigate outgassing, as required in the Roman MAR, paragraph 12.1 and DID 12-1.

6.6.5.1.6 Glycols (NASA-STD-6016A Section 4.2.3.9)

This requirement is not applicable for this component, as glycols will not be utilized.

6.6.5.2 Reserved

6.6.5.3 Reserved

6.6.5.4 Special Materials Requirements

6.6.5.4.1 Fastener Installation (NASA-STD-6016A Section 4.2.6.6) The contractor may use NASA-STD-6008, 541-PG-8072.1.2C or a demonstrated successful contractor practice for procuring, receiving, inspecting, and storing fasteners used for spaceflight hardware with counterfeit protections. Regardless of the approach, the contractor shall provide a Fastener Integrity Control Plan at least 30 calendar days before the PDR. (DIL #45)

The contractor shall determine if there are critical fasteners as defined by 541-PG-8072.1.2C in hardware, and provide the part number at least 30 calendar days before the PDR. (DIL #46) If there are no critical fasteners, this shall be indicated.

6.6.5.4.1.1 Liquid Locking Compounds (NASA-STD-6016A Section 4.2.6.6.1) Conformance to the requirements on this Section of NASA-STD-6016A is recommended.

6.6.5.4.2 Silver-Plated Fasteners (NASA-STD-6016A Section 4.2.6.6.2) The requirements in this section of NASA-STD-6016A are not a concern to Roman.

6.6.5.4.3 Contamination Control (NASA-STD-6016A Section 4.2.6.7) Contamination Control is required, see Section 6.7. In addition to the materials prohibited by NASA-STD-6016A, M&P Lists shall be screened for any materials designated as prohibited by Contamination Control.

6.6.5.4.4 Packaging (NASA-STD-6016A Section 4.2.6.8)

The Contamination Control Plan shall define the packaging requirements for the component during shipping and storage, per Section 6.7.1.

6.6.5.4.5 Shelf-Life Items

Polymeric materials, such as adhesive films and resins, tapes, composites, o-rings, etc., have a limited shelf life. Prior to purchase, the vendor shall ensure that an appropriate storage environment (freezer, cryogenic, inert, etc.) is available for these materials. Purchased materials shall have a Certificate of Compliance (DIL #18), which includes, but is not limited to, the following information: identification of the material(s) or resin(s), lot and/or batch number, date of manufacture, date of expiration, and date of shipment, if applicable. Use of a procured material (in-house or by a vendor) that has exceeded its original shelf life shall require approval from the COR.

It is recommended that a receiving inspection be considered for items having a limited shelf life, not only to address material integrity, but also to characterize salient properties in the event a recertification (though discouraged) might be needed.

While it may be possible to recertify some materials, consideration shall be given to procuring new material as a quicker and more cost effective means to obtain flight materials.

6.6.5.5 Reserved

6.6.6 Materials Procurement Requirements

Raw materials purchased by the contractor and its developers shall be accompanied by a Certificate of Compliance (C of C) and, where applicable, the results of nondestructive, chemical and physical tests. Materials C of C shall be included as part of the EIDP. (DIL #18)

6.7 Contamination Control Requirements

6.7.1 Contamination Control Plan

The contractor shall prepare a Contamination Control Plan (CCP) that describes the procedures that will be followed to control contamination per the Roman MAR, RST-SMA-REQ-0032. The CCP shall establish the implementation and describe the methods and procedures that will be used to measure and maintain the levels of cleanliness required during each of the various phases of the item’s lifetime. The contamination potential of material and equipment used in cleaning, handling, packaging, tent enclosures, shipping containers, bagging (e.g., anti-static film materials), and purging shall be described in detail at each phase of assembly, integration, test, and launch. The CCP shall define the use of protective covers and purges, vent locations and paths, and environmental constraints. The contractor shall submit their CCP to the NASA/GSFC

COR.

6.7.2 Surface Cleanliness

All hardware cleanliness shall be verified to meet the requirements of the Roman VIS Specification, RST-INT-SPEC-0315, prior to delivery to NASA/GSFC. A Cleanliness Certification Report shall be included as part of the EIDP. (DIL #18)

6.7.3 Thermal Vacuum Bakeouts

Thermal…