Attachment_A,_WFIRST-PROP-SOW-0016-.pdf

Effective Date: May 30, 2019

National Aeronautics and Space Administration

Goddard Space Flight Center Greenbelt, Maryland

WFIRST-PROP-SOW-0016, Revision -

Wide Field Infrared Survey Telescope (WFIRST), Code 448

Latch Valve

Statement of Work (SOW)

GSFC WFIRST CMO

June 10, 2019

Released

WFIRST Latch Valve SOW WFIRST-PROP-SOW-0016, Revision -ii

Latch Valve

Statement of Work (SOW)

Review/Signature/Approval Page

Prepared by:

Dina Hoffman

Approved by:

Betsy Forsbacka iii

Preface

This document is a Wide Field Infrared Survey Telescope (WFIRST)

Configuration Management (CM)-controlled document. Changes to this document require prior approval of the applicable Configuration Control Board (CCB) Chairperson or designee.

Proposed changes shall be submitted to the WFIRST 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:

WFIRST Configuration Management Office

Mail Stop 448

Goddard Space Flight Center

Greenbelt, Maryland 20771 iv

Change History Log

Revision Effective Date Description of Changes

(Reference the CCR & CCB/ERB Approval Date)

Rev- May 30, 2019 Initial Release of document per WFIRST-CCR-0005 v

Table of TBDs/TBRs/TBSs [optional]

Item No. Location Summary Individual/

Organization

Actionee

Due Date vi

Table of Contents

1 INTRODUCTION

1.1 Purpose

1.2 Scope

1.3 Related Documentation

1.3.1 Applicable Documents [and Forms]

1.3.2 Reference Documents

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)

2.5 Documentation

2.6 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

3.6 Thermal Model and Documentation

3.7 Reliability Analysis Report

3.8 Error Analysis Report

3.9 User/Instruction Manual

4 HARDWARE PROCUREMENT/MANUFACTURING

4.1 General Requirements

4.2 Latch Valve

4.3 Connector Savers

4.4 Supporting Hardware

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 Training and Certification of Contractor Personnel

6.4 Design Verification Requirements

vii

6.4.1 Verification Requirements

6.4.2 Analysis, Trending, and Reporting of Test Data

6.5 EEE Parts Requirements

6.5.1 General

6.5.2 Parts Age Control

6.5.3 Reuse of Parts and Materials

6.5.4 Part Notification of Failure

6.6 Materials, Processes Requirements

6.6.1 Materials and Processes Control

6.6.2 Commercial-Off-The-Shelf (COTS), Vendor-Designed and Fabricated, and Bilateral

Agreement Furnished Hardware

6.6.3 M&P Usage Documentation

6.6.4 Materials Usage Agreements (MUAs)

6.6.5 Additional Requirements

6.6.5.1 Flammability Control (NASA-STD-6016 Section 4.2.1.1)

6.6.5.2 Toxic Offgassing (NASA-STD-6016 Section 4.2.1.2)

6.6.5.3 Fluid Compatibility (NASA-STD-6016 Section 4.2.1.3)

6.6.5.4 Oxygen Compatibility (NASA-STD-6016 Section 4.2.1.4)

6.6.5.5 Electrical Wire Insulation Materials (NASA-STD-6016 Section 4.2.1.5)

6.6.5.6 Titanium (NASA-STD-6016 Section 4.2.2.3)

6.6.5.7 Tin (NASA-STD-6016 Section 4.2.2.11)

6.6.5.8 Polyvinylchloride (NASA-STD-6016 Section 4.2.3.2)

6.6.5.9 Composite Materials (NASA-STD-6016 Section 4.2.3.3)

6.6.5.10 Limited-Life Items (NASA-STD-6016 Section 4.2.3.5)

6.6.5.11 Thermal Vacuum Stability (NASA-STD-6016 Section 4.2.3.6)

6.6.5.12 External Environment Survivability (NASA-STD-6016 Section 4.2.3.7)

6.6.5.13 Glycols (NASA-STD-6016 Section 4.2.3.9)

6.6.5.14 Adhesive Bonding (NASA-STD-6016 Section 4.2.4.3)

6.6.5.15 Nondestructive Evaluation (NDE) Plan (NASA-STD-6016 Section 4.2.5.1)

6.6.5.16 Fastener Installation (NASA-STD-6016 Section 4.2.6.5)

6.6.5.17 Contamination Control (NASA-STD-6016 Section 4.2.6.6)

6.6.5.18 Packaging (NASA-STD-6016 Section 4.2.6.7)

6.6.5.19 Shelf-Life Items

6.6.5.20 Solder Flux

6.6.5.21 Fasteners with LL Longitudinal Locking Elements

6.6.5.22 Gold-Indium Intermetallic

6.6.6 Materials Procurement Requirements

6.6.7 Welding

6.7 Contamination Control Requirements

6.7.1 Contamination Control Plan

6.7.2 Surface Cleanliness

6.7.3 Material Outgassing

6.7.4 Thermal Vacuum Bakeouts

7 HANDLING, STORAGE, PACKAGING, PRESERVATION, AND DELIVERY

APPENDIX A GSFC PCB SUBMITTAL AND MATERIAL SELECTION FORMS

viii

APPENDIX B ABBREVIATIONS AND ACRONYMS

1 INTRODUCTION

1.1 Purpose

The Wide Field InfraRed Survey Telescope (WFIRST) 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. A coronagraph instrument is included in the payload for purposes of advancing the present state of the art of coronagraph technology. This document defines the work to be performed by the Contractor in the design, development, fabrication, and delivery of the Wide

Field Infrared Survey Telescope (WFIRST) Latch Valve.

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 WFIRST-PROP-LIST-0017.

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 should be used unless otherwise specified in this

SOW. WFIRST documents can be obtained from URL: https://ipdtdms.gsfc.nasa.gov.

1.3.1 Applicable Documents [and Forms]

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

WFIRST Project Configuration Change Board has the final authority for conflict resolution.

https://ipdtdms.gsfc.nasa.gov/

Document Number Title

WFIRST-PROP-SPEC-

WFIRST Latch Valve Specification

WFIRST-LIST-0017 WFIRST Latch Valve Deliverable Items List and Schedule (DILS)

WFIRST-SMA-REQ-

WFIRST 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

NASA Reference Pub

Outgassing Data for Selecting Spacecraft Materials

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

WFIRST-REF-12172 WFIRST 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

NASA-STD-5005 NASA Technical Standards System

AMS5569 REV. B Steel, Corrosion and Heat Resistant, Seamless and Welded

Hydraulic Tubing 19Cr - 9.5Ni - 0.03C max Cold Drawn, 1/8

Hard Temper

AMS5647 REV. K Steel, Corrosion-Resistant, Bars, Wire, Forgings, Mechanical

Tubing, and Rings 19Cr - 9.5Ni Solution Heat Treated

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.

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 Latch Valve 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 monthly technical status reports via telecon and a written report. (DIL #2). The report shall be a summary presentation of the period's progress to include topics such as schedule overview, 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 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 Latch Valve 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

Latch Valve Design Description

Preliminary Interface Control Documents

Flight Heritage

Facilities

Qualification Verification Plan and Procedure

Mechanical Analysis with Boundary Conditions

Manufacturing Flow

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 #7) 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 #8) The Design Conformance

Review shall address all program management, design, drawings, analysis, manufacturing, test, and quality assurance activities outlined in this SOW and the WFIRST Latch Valve Specification

WFIRST-PROP-SPEC-0052 in sufficient detail to ensure that the proposed design conforms to all requirements and is ready for fabrication to begin. At a minimum, the design package should cover the following areas:

Program Management

Quality Assurance

Interface Control Documentation

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

Reliability Analysis

Electrical Worst-Case analyses

Failure Modes Effects Criticality Analysis

Flight Heritage

Verification Matrix (per Section 6.4.1)

Acceptance Test Plan

Final Qualification Report

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 #9)

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 #10) This presentation shall demonstrate overall conformance of the requirements specified in the WFIRST Latch Valve

Specification WFIRST-PROP-SPEC-0052 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 #11) 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 #12)

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

#13) 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 #14) 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 latch valves, 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 cycles, separated by primary/redundant

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

Certificate of Conformance, with management signature

End Item Inspection Report

As-Built Configuration List

Mate/Demate log

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 #15) 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.

2.5 Documentation

The contractor shall ensure the generation and delivery of all documentation as called for in the contract and listed in the DILS document, WFIRST-PROP-LIST-0017.

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 Existing Documentation and Analysis

If analysis or documentation exists already for the flight unit that satisfies the requirements within the Latch Valve Specification, WFIRST-PROP-SPEC-0052, 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 WFIRST Latch Valve Specification (WFIRST-PROP-SPEC-0052) 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 2.6.

3.1 Interface Control Documentation

The Contractor shall provide document(s) and/or drawing(s) that define, in detail, all electrical, thermal, and mechanical interfaces, including the center of mass relative to an external reference, subject to review and approval by the NASA/GSFC COR (DIL #16).

3.2 Drawing Package

The contractor shall provide a complete drawing package, including mechanical and electrical drawings at a minimum, available for review at the contractor’s facility for DCR (DIL #17).

3.3 Computer Models

The contractor shall deliver the following computer models (DIL #18):

1. A Computer-Aided Design (CAD) file of the latch valve

2. Mechanical Model in STEP file format

3. Thermal Model (See Section 3.6)

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 flight hardware by assessing the size and location of applied loads, load paths, and critical failure modes. A Structural Analysis shall be provided for the Flight Unit structure to ensure the capability to withstand and survive launch and ascent loads. (DIL #19) The analysis shall also address loads on any lift points as well. For metallic elements whose strengths are to be qualified by analysis (rather than by test, subject to NASA/GSFC approval), margins of safety will be 2.0 on yield and 2.6 on ultimate. Beryllium and composite materials shall not be qualified by analysis alone. The effects of any thermal inputs shall be reflected in the analyses as appropriate. This analysis shall include a Venting analyses for applicable flight 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 launch. 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 (per WFIRST-PROP-SPEC-0052, Section 5.2) and model documentation that describes the following: (DIL #20)

1. The version of the model, including date of creation

2. A list of element, node, property, and material identification (ID) numbers

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 of satisfying 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, overconstraints, 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 deployed on-orbit 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. In their unconstrained condition, the stowed dynamics and thermal distortion models should have six rigid body modes with frequencies below 0.001 Hz, with a goal of 0.0001 Hz.

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 (if required): 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 (per WFIRST-PROP-SPEC-0052, Section 5.2) 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"

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

Frequency and mode shapes shall be correlated with the modal survey test results as described:

1. the frequency predictions agree with the modal survey results to within 5 percent for the first mode and 10 percent for all other significant modes up to 50 Hz.

2. the mode shape correlations between test and the analytical model should include a cross-orthogonality check ([T

(FEM)][MFEM][T

(test)] resulting in 0.9 or greater on diagonal and

0.1 or less on off-diagonals.

Note: Significant modes are identified by having equal to or more than 5% modal mass participation in a fixed base modal analysis of the instrument/subsystem. a mode shape geometric similarity check, and a static deflection check.

3.6 Thermal Model and Documentation

The contractor shall provide reduced Thermal Math Models (TMMs) for the latch valve with less than 50 nodes per box, in Thermal Desktop/SINDA format or another format pre-approved by the WFIRST Thermal group (DIL #22).

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 latch valve

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 Reliability Analysis Report

The contractor shall provide a numerical reliability assessment of the component, using reliability data from historical on-orbit performance, life-testing, or data books, such as MIL-

HDBK-217F. (DIL #27) The results of this analysis shall be summarized in a Contractor format

Reliability Analysis Report that will be provided to the NASA/GSFC COR for review.

3.8 Error Analysis Report

An Error Analysis shall be performed on the Flight Unit Latch Valve Design that identifies all the factors that introduce error into the accuracy of the latch valve, and shows that the system can meet its performance requirements in spite of the errors. Errors may include, but not be limited to: Alignment error, radiation effects, electronic noise, degradation of parts, optical distortions, thermal distortions, quaternion algorithm calculations, etc. An Error Tree shall be generated documenting ALL the sources of error, along with an Error Analyses Report and provided to

NASA/GSFC COR for review. (DIL #24)

3.9 User/Instruction Manual

The contractor shall deliver procedures that describe the operation of the unit and any operational constraints to the unit. Examples of items to include in the user/instruction manuals are long term storage activities, operational constraints for voltage, temperature, number of cycles, open and close procedures, etc. (DIL #26)

4 HARDWARE PROCUREMENT/MANUFACTURING

4.1 General Requirements

The contractor shall either procure or manufacture all components required to assemble, integrate, and test the Latch Valve to support the delivery dates as called for in the contract and listed in the DILS document, WFIRST-PROP-LIST-0017.

The contractor shall assemble the quantities of latch valve 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 latch valve.

4.2 Latch Valve

The contractor shall provide the following hardware to meet the requirements of the WFIRST

Latch Valve Specification (WFIRST-PROP-SPEC-0052).

a) Eight (8) Latch Valve Flight Unit(s) (DIL #50), plus (1) spare unit (DIL #50)

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

4.3 Connector Savers

Flight Units shall be tested with connector savers to minimize mates and de-mates. Flight-like connector savers shall be delivered with each Flight Unit. (DIL #51)

4.4 Supporting Hardware

If the Contractor delivers the latch valve with a mating connecter, then the Contractor shall provide a GSE protective cap. (DIL #52)

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 WFIRST Latch Valve Specification

WFIRST-PROP-SPEC-0052 will be performed. (DIL #28) 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 Latch Valve.

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 #29)

5.2 Verification Test Procedures

The contractor shall generate Verification Test Procedures and provide them to the NASA/GSFC

COR. (DIL #30) 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 6.7.4 for the Chamber Configuration.

5.3 Verification Test Reports

The contractor shall generate Verification Test Reports. (DIL #31) 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. The

Thermal Vacuum Test Report may include the Bakeout results (see Section 6.7.4) if it can be delivered by the delivery date for Bakeout Test Results.

6 SAFETY AND MISSION ASSURANCE

6.1 General Requirements

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

0032). All corresponding deliverables shall be delivered as described in MAR Data Item

Descriptions (DIDs). Sections 1 through 4 and Sections 10 through 15 apply in their entirety.

There are some reductions in scope for Section 5, System Safety, and Section 6, Reliability, that only require support to the WFIRST Project Safety and Mission Assurance (SMA) group for component level requirements/deliverables.

The Contractor’s plan for compliance with the MAR shall be documented in the WFIRST-specific Mission Assurance Implementation Plan (MAIP) or Quality Assurance Plan. (DIL #32).

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 #33) Class I changes are defined as changes that affect form, fit, function, external interfaces, or requirements as stated within this document and the latch valve 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 #34) 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 Training and Certification of Contractor Personnel

All personnel performing work on flight hardware requiring a prerequisite set of skills and competency shall be certified as having completed the required training, appropriate to their involvement.

6.4 Design Verification Requirements

6.4.1 Verification Requirements

The contractor shall implement a program to verify all requirements specified in the WFIRST

Latch Valve Specification (WFIRST-PROP-SPEC-0052).

The contractor shall provide a verification matrix defining the method of verification for each specific requirement of the WFIRST Latch Valve Specification (WFIRST-PROP-SPEC-0052) per Section 5.1 of this SOW. (DIL #28)

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 flight worthiness and to aid in the identification and analysis of flight hardware failures and problems.

6.5 EEE Parts Requirements

6.5.1 General

The contractor shall implement a parts control plan (PCP) per the Level 2 requirements of GSFC

EEE-INST-002 Instruction for EEE Parts Selection, Screening, Qualification, and Derating, this also pertains to custom devices. (DIL #39/MAR DID 10-1) For critical applications and known single point failures, the contractor shall use Level 1 Parts per GSFC EEE-INST-002 via the

Parts Control Board (PCB) review and approval process.

The contractor shall establish a PCB that is responsible for the planning, management, and coordination of the selection, application, and procurement requirements of EEE parts. The

WFIRST parts engineer and Chief Safety and Mission Assurance Officer shall be voting members of the PCB.

The contractor shall identify the person responsible for directing and managing the EEE parts program and interfacing with government assurance personnel.

6.5.2 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 #37) 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.

6.5.3 Reuse of Parts and Materials

EEE parts and materials that have been installed in an assembly and removed for any reason shall not be used again for flight without prior approval of the MRB. The approval shall be based on the submission of evidence that re-used devices did not degrade during the removal and re-installation process, shortening the device useful life.

6.5.4 Part Notification of Failure

The contractor shall provide failure-reporting data to NASA/GSFC COR, WFIRST Parts

Engineer and CSO within 24 hours of part failure determination. (DIL #38)

6.6 Materials, Processes Requirements

6.6.1 Materials and Processes Control

To qualify material for flight use, the material must have a satisfactory flight heritage relevant to

WFIRST requirements or meet the following applicable selection criteria as defined herein for:

Vacuum outgassing

Stress corrosion cracking (SCC)

Manufacturing process selection

Materials, processes, and lubrication approval by the WFIRST 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 Commercial-Off-The-Shelf (COTS), Vendor-Designed and Fabricated, and Bilateral

Agreement Furnished Hardware

The use of any hardware, including those listed above, for which a detailed M&P list (as defined herein) is not available and/or an M&P List is not available for review and approval will be treated as non-compliant. A Materials Usage Agreement (MUA) shall be prepared and submitted to define what measures are taken to ensure that all M&P in the hardware are acceptable for use. Supporting rationale may include documentation supporting qualification of heritage flight hardware per GSFC-STD-1000G (Rule 1.11), documentation supporting Safety and Mission Assurance (SMA) acceptance of hardware, hermetic sealing, vacuum bake-out, material changes for known non-compliant materials, etc. The disposition of the MUA will be coordinated through the MPE.

6.6.3 M&P Usage Documentation

The Materials and Processes List shall include all materials and materials-related processes, as well as a list of fasteners identified by complete part number. The list of Processes shall include those processes that ensure a repeatable/controlled process that produces a consistent and reliable product. The contractor shall review proposed materials and processes with the NASA/GSFC

COR. (DIL #40) An As-Built Materials List (ABML) shall be included as part of the end item data package. (DIL #14) Sample forms are available upon request.

The lists shall include the following information in an electronically searchable format:

Polymeric Materials and Composites Usage List – Material Identification (including full specification, manufacturer, and part number), Mix Formula, Cure, Amount, Expected

Environment, Special Reason for Selection, Outgassing Values (including reference source and test reference), Usage, MUA Number (if applicable).

Inorganic Materials and Composites Usage List – Materials Identification (including full specification), Condition, Surface Finish and/or Coating, Application, Expected

Environment, Stress Corrosion Cracking Rating, Corrosion Rating, Usage, MUA Number

(if applicable), complete fastener part number (identifying material, condition, finish, locking element).

Lubrication Usage List – Component Type, Size and Material; Component Manufacturer and Manufacturer Identification; Proposed Lubrication System and Amount of Lubricant;

Type and Number of Wear Cycles; Speed, Temperature and Atmosphere of Operation;

Type of Loads and Amount; Other Details.

Material Processes Utilization List – Process Type; Contractor Specification Number;

Military, ASTM (American Society for Testing and Materials), Federal or Other

Specification; Description of Material Processed; Application.

The Materials and Processes List shall include references to Materials Usage Agreements

(MUAs) at entries for non-compliant materials and processes (see 6.6.4).

Wire, cable, and connectors shall meet the requirements of this document and be reported on the

M&P List, as well as, the PIL and ABPL. All other standard and nonstandard Electrical, Electronic, and Electromechanical (EEE) parts shall be exempt from these requirements and reporting on the Materials and Processes List. In general, items that are listed in GSFC-EEE-

INST-002 are considered standard EEE Parts.

6.6.4 Materials Usage Agreements (MUAs)

MUAs shall be submitted for all M&P that are technically acceptable but do not meet M&P requirements. (DIL #41) The MUA shall include sufficient information to demonstrate that the application is technically acceptable.

6.6.5 Additional Requirements

The last four detailed requirements identified (Sections 6.6.5.19 – 6.6.5.22 below) are requirements beyond NASA-STD-6016. The contractor shall ensure the relevant requirements are flowed to vendors.

6.6.5.1 Flammability Control (NASA-STD-6016 Section 4.2.1.1)

Flammability control shall be addressed as required per NASA-STD-6016.

6.6.5.2 Toxic Offgassing (NASA-STD-6016 Section 4.2.1.2)

NASA-STD-6016 Section 4.2.1.2 is not applicable nor required for this component.

6.6.5.3 Fluid Compatibility (NASA-STD-6016 Section 4.2.1.3)

Heritage usage may be solely considered when assessing compatibility.

6.6.5.4 Oxygen Compatibility (NASA-STD-6016 Section 4.2.1.4)

NASA-STD-6016 Section 4.2.1.4 is not applicable nor required for this component.

6.6.5.5 Electrical Wire Insulation Materials (NASA-STD-6016 Section 4.2.1.5)

In addition to being included in M&P Lists, wire insulation shall be the reviewed by the Parts

Control Board as defined in Safety and Mission Assurance’s requirements and plans.

6.6.5.6 Titanium (NASA-STD-6016 Section 4.2.2.3)

Titanium shall be procured and heat treated using active government or industry specifications such as shown in https://standards.nasa.gov.

The requirements in this section of NASA-STD-6016 are applicable as written, including those described in sections 4.2.2.3.1 through 4.2.2.3.5.

6.6.5.7 Tin (NASA-STD-6016 Section 4.2.2.11)

Pb-free tin shall not be used in any applications. Pb-free tin is defined to be pure tin or any tin alloy with <3% lead content by weight. This means that some Pb-free finishes other than pure tin, such as tin-bismuth and tin-copper, are considered to be “tin” for the purposes of this document.

The contractors shall submit uses of lead-free tin solder or surface finishes and whisker mitigation methods for approval before use. As a minimum for whisker mitigation in printed wiring assemblies, the contractor shall utilize lead tinning with a tin-lead solder and conformal coating a minimum of 0.004 inches thick for whisker mitigation.

Lot sampling is not a requirement.

https://standards.nasa.gov/

6.6.5.8 Polyvinylchloride (NASA-STD-6016 Section 4.2.3.2)

The use of polyvinylchloride (PVC) is prohibited.

6.6.5.9 Composite Materials (NASA-STD-6016 Section 4.2.3.3)

The elements of this section of NASA-STD-6016 shall be used as a guide.

6.6.5.10 Limited-Life Items (NASA-STD-6016 Section 4.2.3.5)

Limited Life Items shall be addressed as required in WFIRST-REF-12172 Section 6.12.

6.6.5.11 Thermal Vacuum Stability (NASA-STD-6016 Section 4.2.3.6)

Nonmetallic materials shall be tested per ASTM-E595, with acceptance criteria of ≤0.1 percent collected volatile condensable materials (CVCM) and ≤1.0 percent total mass loss (TML). An

MUA shall be submitted to the NASA/GSFC COR for any material that does not meet these criteria.

The outgassing database (http://outgassing.nasa.gov/) maintained by the MEB may be consulted for relevant outgassing data.

The remaining requirements in this section are not applicable.

6.6.5.12 External Environment Survivability (NASA-STD-6016 Section 4.2.3.7)

The requirements in this section of NASA-STD-6016 are applicable as written.

The vendor shall provide a list of materials exposed to atomic oxygen in conjunction with the delivery of M&P Lists. (DIL #42) If there are no exposed materials, this shall be indicated.

6.6.5.13 Glycols (NASA-STD-6016 Section 4.2.3.9)

NASA-STD-6016 Section 4.2.3.9 is not applicable nor required for this component.

6.6.5.14 Adhesive Bonding (NASA-STD-6016 Section 4.2.4.3)

All bonding processes should meet the intent of MSFC-SPEC-445.

All materials are reviewed against the appropriate requirements.

Processes are qualified and documented.

The shelf life of adhesives and primers are managed. Only materials with remaining shelf life are used.

Personnel are trained and certified to the materials and bonding processes.

Adhesives are handled and stored per manufacturer recommendations.

Appropriate contamination-free facilities are used for surface preparation and bonding operations.

http://outgassing.nasa.gov/

Non-destructive techniques and destructive coupon testing is performed to verify bonding operations.

Adhesive mix records should be kept by the vendor for the duration of the mission life. These should show date, planned mix ratio, measured mix ratio, cure parameters, and hardness coupon hardness.

6.6.5.15 Nondestructive Evaluation (NDE) Plan (NASA-STD-6016 Section 4.2.5.1)

As part of a fracture control plan, the contractor shall implement a nondestructive evaluation plan for the procedures and specifications used in the inspection of materials per the requirements outlined in NASA-STD-6016. (DIL #43)

The NDE Plan shall be prepared at Instrument, Spacecraft, or Project level. It shall describe the process for establishment, implementation, execution and control of NDE for fracture critical flight hardware. The plan shall meet the intent of MIL-HDBK-6870, Inspection Program

Requirements, Nondestructive for Aircraft and Missile Materials and Parts and NASA-STD-

5009, Standard NDE Guidelines and Requirements for Fracture Control Programs, as specified by NASA-STD-6016. It may be included in other deliverables associated with the fracture control plan.

If it is determined that a fracture control plan is not applicable to WFIRST hardware, then an

NDE Plan is not necessary, but this determination shall be documented.

6.6.5.16 Fastener Installation (NASA-STD-6016 Section 4.2.6.5)

The vendor shall provide hardware’s Fastener Integrity Control Plan for review at least 30 calendar days before the DCR. (DIL #44) It is recommended that it comply with 541-PG-

8072.1.2C or NASA-STD-6008. That Plan shall outline the acquisition, traceability, receiving inspection, and test requirements of the vendor to ensure fastener integrity.

The vendor shall determine if there are critical fasteners as defined by 541-PG-8072.1.2 in hardware, and provide the part number. (DIL #45) If there are no critical fasteners, this shall be indicated. 541-PG-8072.1.2C is not applicable to nonstructural electrical or electronic applications.

The requirements in this section of NASA-STD-6016 are applicable as written including those in sections 4.2.6.5.1 and 4.2.6.5.2, except as discussed above.

6.6.5.17 Contamination Control (NASA-STD-6016 Section 4.2.6.6)

Contamination Control shall be as required. In addition to the materials prohibited by NASA-

STD-6016, M&P Lists shall be screened for any materials designated as prohibited by

Contamination Control.

6.6.5.18 Packaging (NASA-STD-6016 Section 4.2.6.7)

Packaging shall be as required per NASA-STD-6016.

6.6.5.19 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, 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.

6.6.5.20 Solder Flux

Fluxes shall be identified in the M&P Lists and be as defined in Safety and Mission Assurance’s requirements and plans.

Any use of fluxes that don’t comply with Safety and Mission Assurance’s requirements and plans shall be referred to the NASA/GSFC COR, who will refer them to the Code 300 Subject

Matter Expert (SME) for disposition and waiver (as opposed to an MUA), if necessary.

6.6.5.21 Fasteners with LL Longitudinal Locking…