Statement of work.pdf

Effective Date: September 07, 2021 Expiration Date: September 07, 2026

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400-FORM-0002 (4/16/2014)

GSFC PACE CMO

09/07/2021 Released

PACE-GNC-SPEC-0200, Revision -

Plankton, Aerosol, Cloud, ocean Ecosystem (PACE) mission, Code 427.0

PACE Spacecraft RWA Radial Ball Bearing Specification - Myonic

GODDARD SPACE FLIGHT CENTER

GREENBELT, MD

Reviewed by the GSFC Export Control Office as not subject to export control, approved for public release

PACE Spacecraft RWA Radial Ball Bearing Specification - Myonic PACE-GNC-SPEC-0200, Revision -ii

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400-FORM-0002 (4/16/2014)

PACE Spacecraft RWA Radial Ball Bearing Specification - Myonic Signature/Approval Page

Prepared by:

Zachary Cameron

Reviewed by:

Brian Frey Matthew Shacka Michael Fritsch Frank Fried Craig Stevens

Approved by:

Carlos Duran-aviles

Electronic signatures available online at: https://ipdtdms.gsfc.nasa.gov/ iii

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400-FORM-0002 (4/16/2014)

Preface

This document is under Plankton, Aerosol, Cloud, ocean Ecosystem (PACE) mission signature-controlled document. Changes to this document require prior approval of the applicable Product Design Lead (PDL) or designee. Proposed changes shall be submitted in the PACE Technical Data Management System (TDMS) via a Signature Controlled Request (SCoRe), along with supportive material justifying the proposed change.

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400-FORM-0002 (4/16/2014)

Change History Log

Revision Effective

Date Description of Changes

(Reference the CCR & CCB/ERB Approval Date) 09/07/2021 09/07/2021 Baseline Release following the approval of PACE-SCoRe-3048 v

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400-FORM-0002 (4/16/2014)

Table of Contents

1 INTRODUCTION

1.1 Scope

1.2 PACE Mission Overview

1.3 Applicable Documents

2 REQUIREMENTS

2.1 General

2.2 Mechanical

2.3 Lubricant

2.4 Low Speed Torque Test

3 QUALITY ASSURANCE

3.1 Procedures

3.2 Identification of Product

3.3 Cleanliness

3.4 Bearing Cleanliness Inspection Requirements

3.5 Inspection

3.6 Customer Source Inspection

3.7 Lot Traceability

3.8 Acceptance

3.9 Packaging

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400-FORM-0002 (4/16/2014)

List of Figures

Figure 3-1 Bearing Dimensions

List of Tables

Table 2-1 Bearing Load Condition

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1 INTRODUCTION

1.1 Scope

This specification establishes the requirements for the fabrication, lubrication, performance, and quality assurance for a deep groove ball bearing.

Note: DIRWA (Demiseable Integrated Reaction Wheel Assembly), RWA (Reaction Wheel Assembly), and RW (Reaction Wheel) will be used interchangeably throughout this procedure but refer to the same unit.

1.2 PACE Mission Overview

The Plankton, Aerosol, Cloud, ocean Ecosystem (PACE) mission is a strategic climate continuity mission that was defined in the 2010 document Responding to the Challenge of Climate and Environmental Change: NASA’s Plan for Climate-Centric Architecture for Earth Observations and Applications from Space (referred to as the “Climate Initiative”). The Climate Initiative complements NASA’s implementation of the National Research Council’s Decadal Survey of Earth Science at NASA, NOAA, and USGS, entitled Earth Science and Applications from Space: National Imperatives for the Next Decade and Beyond.

PACE will extend the high quality ocean ecological, ocean biogeochemical, cloud, and aerosol particle data records begun by NASA in the 1990s, building on the heritage of the Sea-Viewing Wide Field-of-View Sensor (SeaWiFS), the Moderate Resolution Imaging Spectroradiometer (MODIS), the Multi-angle Imaging SpectroRadiometer (MISR), and the Visible Infrared Imaging Radiometer Suite (VIIRS). The mission will be capable of collecting radiometric and polarimetric measurements of the ocean and atmosphere, from which these biological, biogeochemical, and physical properties will be determined. PACE data products will not only add to existing critical climate and Earth system records, but also answer new and emerging advanced science questions related to Earth’s changing climate.

PACE is classified as a Category 2 mission, per the criteria in NASA Procedural Requirement (NPR) 7120.5E, NASA Space Flight Program and Project Management Requirements. The mission classification is C according to NPR 8705.4B, Risk Classification for NASA Payloads.

The PACE observatory is comprised of three instruments, an Ocean Color Instrument (OCI) and two polarimeters, the Hyper-Angular Rainbow Polarimeter 2 (HARP-2) and the Spectro- Polarimeter for Exploration (SPEXone). The OCI is the primary instrument on the observatory and is being developed at Goddard Space Flight Center (GSFC). The OCI is a hyper-spectral scanning (HSS) radiometer designed to measure spectral radiances from the ultraviolet to shortwave infrared (SWIR) to enable advanced ocean color and heritage cloud and aerosol particle science.

The HARP-2 and SPEXone are secondary instruments on the PACE observatory, acquired outside of GSFC. The HARP-2 is multi-spectral, wide swath (supporting atmospheric correction of OCI) and hyper angular (good for clouds). The SPEXone is narrow swath and hyperspectral, better for characterizing aerosol microphysical properties.

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400-FORM-0002 (4/16/2014)

This three-instrument PACE mission has the following multiple scientific goals:

Extending key systematic ocean biological, ecological, and biogeochemical climate data records and cloud and aerosol climate data records;

Making global measurements of ocean color data products that are essential for understanding the global carbon cycle and ocean ecosystem responses to a changing climate;

Collecting global observations of aerosol and cloud properties, focusing on reducing the largest uncertainties in climate and radiative forcing models of the Earth system; and, Improving our understanding of how aerosols influence ocean ecosystems and biogeochemical cycles and how ocean biological and photochemical processes affect the atmosphere.

The PACE satellite is planned for a launch in 2022-2023. The PACE project office at NASA’s GSFC is responsible for the satellite development, launch and operations. The mission is planned for launch into a Sun synchronous polar orbit at 676.5 km with an inclination of 98 degrees and a 1 pm local ascending node crossing time. The spacecraft bus will host the OCI, HARP-2, and SPEXone instruments. The GSFC PACE Project office will oversee the mission and the development of the satellite, launch vehicle, mission operations control center, and operations. The Headquarters Program Science will separately fund the science data processing system and competed science teams, which will include field-based vicarious calibration and data product validation efforts to support the Project science team.

NASA Headquarters has directed the mission development to be guided by a Design-to-Cost (DTC) process. All elements of the mission, other than the cost, are in the DTC trade space. At the heart of the DTC process are the mission studies, performed across all the mission elements.

The mission studies will be used to define appropriate approaches within and across elements while maximizing science capabilities at a high cost confidence. Mission baseline requirements development is also embedded within the DTC process, as these requirements were not established at the onset of the mission concept development. Baseline mission requirements will be a product of the mission studies and will be defined by the project office as part of the DTC process.

The PACE mission consists of four major segments: space segment (SS), ground segment (GS), science data segment (SDS), and the launch segment (LS).

The space segment consists of the spacecraft bus, the OCI, and two polarimeters. The spacecraft and OCI are being developed and integrated at GSFC. The polarimeters are contributed instruments. The spacecraft and instruments will be integrated as the PACE observatory at GSFC.

The GS and associated Mission Operations Center (MOC) will be developed, integrated, and operated at GSFC. The GS provides for the command and control and health and safety monitoring of the PACE observatory on-orbit, as well as ensuring the science data are accounted for and delivered to the SDS. The MOC will house the flight operations team (FOT) and is being managed by the PACE project through observatory commissioning. After commissioning, the FOT will be managed by the GSFC Earth Science Mission Operations (ESMO) project. The MOC performs all real time

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400-FORM-0002 (4/16/2014)

operations and off-line operations functions, including planning and scheduling, orbit and attitude analysis, housekeeping telemetry data processing, monitoring/managing the spacecraft and instruments, first line health/safety for the instruments, and housekeeping archiving and analysis.

The SDS will be located at GSFC, but managed (separately from the project) by the NASA Headquarters Earth Sciences Division. The SDS will ingest, apply calibration and science algorithms, and process the science data, provide science software development and algorithm integration, act as the science data interface to the science team, and deliver of all science data products to the NASA-assigned Distributed Active Archive Center (DAAC).

The LS is planned for a launch vehicle to be selected and procured by the NASA Launch Services Program at Kennedy Space Center (KSC).

In addition to utilizing GSFC institutional capabilities, the project will utilize the NASA/GSFC institutional capabilities such as the Flight Dynamics Facility (FDF), Near Earth Network (NEN), Ocean Biology Processing Group (OBPG), Space Network (SN), and NASA Integrated Services Network (NISN). PACE plans to generate 3.5 Terabits of science data daily. The data are downlinked from the observatory during 12-14 daily contacts via Ka-band communications to the NEN's ground stations. The observatory will also receive ground commands and transmit real-time housekeeping telemetry via an S-band 2-way link through the NEN during nominal operations. The observatory also has the capability of receiving ground commands and transmitting real-time housekeeping telemetry, via S-Band, through the SN during critical or contingency operations.

1.3 Applicable Documents

The following documents of the latest issue form a part of this specification to the extent specified herein. Where the differences occur between this specification and the following documents, the requirements of this specification shall prevail.

Military Specification

MIL-L-6085 Lubricating Oil: Instrument, Aircraft, Low Volatility

MIL-H-6875 Heat Treated Steels, Processes for

MIL-B-81937 Military Specification Grease, Instrument, Ultra Clean, Metric

Military Standards

MIL-STD-130 Military Standard Identification Marking of U.S. Military Property

MIL-STD-1246 Product Cleanliness Levels and Contamination Control Program

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MIL-STD-206 Friction Torque Testing for Ball Bearings

Federal

QQ-S-763E Steel Bars, Wires, Shapes, Forgings, Corrosion Resistant

ISO 14644 Clean Room and Work Station Requirements

NASA-STD-5017A Design and Development Requirements for Mechanisms

Others

ISO 9001 Quality Program Requirements

ISO 3290 Rolling Bearings—Balls—Dimensions & Tolerances

American Bearing Manufacturers Association, Inc.

ABMA Standards for Ball Bearings, Section 20

Industrial Standards

AMS 6444N SAE 52100 Steel Bars, Forgings, and Tubing

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2 REQUIREMENTS

2.1 General

Bearings delivered per this specification shall meet the mechanical, inspection, and quality assurance requirements of this document.

2.2 Mechanical

2.2.1 Configuration

Each bearing shall be a deep groove, two-piece loose clench crimped ribbon cage, double shielded unit. The cage shall be ball piloted. The shields shall be removable. See Figure 3-1 at the end of this document for a sketch of desired dimensions and tolerances. A mechanical drawing of the bearing shall be approved by GSFC before production begins.

2.2.2 Material

The bearing components shall be fabricated from the following materials:

Balls, Inner and AISI 52100 Double CEVM Chrome Alloy Steel

Outer Rings Bar, conforming to AMS-6444N

Cages Two-Piece, Crimped Ribbon; 305 Stainless Steel Per AMS 5514

Shields 302 Stainless Steel per AMS 5516

Snap Rings 302 Stainless Steel per ASTM A313, Class 302, Condition B

2.2.3 Hardness

The inner rings and outer rings shall be heat treated to a hardness of RH-58 minimum on the C scale in accordance with MIL-H-6875. The balls shall be heat treated to a hardness of RH-60 minimum on the C scale in accordance with MIL-H-6875.

2.2.4 Surface Roughness

2.2.4.a The surface roughness of the raceways shall not exceed 1.5 micro-inches centerline average (CLA) at 0.08mm measurement cutoff length.

2.2.4.b The roughness of the mounting surfaces and faces shall not exceed 10 micro-inches CLA.

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2.2.5 Race Roundness

2.2.5.a Inner Race: At the nominal contact angle, the rate of change in radius (dr/dq) shall be less than 5 micro-inches per 10º, measured over a 10° interval. The roundness total (RONt) shall be less than 0.000030 inches.

2.2.5.b Outer Race: At the nominal contact angle, the rate of change in radius (dr/dq) shall be less than 12.5 micro-inches per 10º, measured over a 10° interval. The roundness total (RONt) shall be less than 0.000050 inches.

2.2.5.c Cross Race Curvature: Within ±10º of nominal contact angle for a 10 pound thrust load, the cross race surface shall deviate from true curvature no more than ±0.000020 inches.

2.2.6 Ring Serialization

The outer ring for each bearing shall be individually serialized by a permanent marking method.

The serial number of the outer race shall become the serial number for the assembled bearing.

2.2.7 Balls

The balls diameter shall be 7/32” and shall be Grade 5 or better in accordance with ISO 3290 Standard for Balls. The number of balls per bearing row shall be 7.

2.2.8 Tolerances

The tolerances shall be those of ABEC-7 class or better in accordance with ABMA Standards for Ball Bearings, Section 20.

2.2.9 Radial Play

The radial play shall be 0.0005 inches minimum to 0.0008 inches maximum.

2.2.10 Raceway Curvature

2.2.10.a Inner Ring: The inner raceway shall possess a curvature of 51.75 to 52.47% of the ball diameter.

2.2.10.b Outer Ring: The outer ring raceway shall possess a curvature of 53.6 to 54.35% of the ball diameter

2.2.11 Bearing Load Rating

The radial bearing’s mean Hertzian contact stress shall be at or below 360 ksi on both the inner and outer raceway contact regions for the load conditions present in Table 2-1. In addition to this, they shall possess a ball-raceway contact area that lies completely within the raceway as per NASA-STD-5017A for the same load condition.

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400-FORM-0002 (4/16/2014)

Table 2-1 Bearing Load Condition

Load Case Value

Static Radial 422.6 lbs.

Axial 945 lbs.

Dynamic 1300 lbs.

2.3 Lubricant

2.3.1 Oil Coating

Nye Synthetic Oil 2001 shall be used for corrosion protection of the bearing assembly. Perform low speed torque test in section 2.4 with this oil.

2.3.2 Lubrication

Each bearing shall be lubricated with Rheolube 2000 grease. Fill 25-30% of the bearing free volume with this grease. Each bearing in the lot shall have the weight of grease added recorded along with the bearing’s serial number. The list of grease weight added to each bearing shall be provided to NASA GSFC for 100% of the lot.

2.4 Low Speed Torque Test

The torque of each bearing shall be measured and recorded in the load-bearing thrust direction with a 400 gram load using the lubrication oil specified in 2.3.1. The charts shall be marked with the corresponding bearing serial number and delivered. Scale factors shall be indicated and shall be in metric units. One hundred percent inspection required.

The running torque traces shall not exhibit any noticeable spikes or repetitive spikes. A noticeable spike is a peak in the trace whose value deviates from the average running torque by ±25% of the average torque for the given direction of rotation. Average torque shall be calculated by averaging the torque readings across the entire 360 degrees of a trace in a given direction. A repetitive spike is a spike whose occurrence is periodic and repeatable along the torque trace. Any individual bearing exhibiting noticeable or repetitive torque spikes shall be re-cleaned, re-lubricated, and retested per sections 2.3, and 2.4. Any individual bearing requiring re-cleaning, re-lubrication, and re-testing shall be recorded and any initial, failed, low speed torque traces shall be provided to NASA GSFC with the final acceptable low speed torque trace for documentation. 100% of torque traces shall be provided to NASA GSFC packaged with the final, assembled bearings.

The test speed shall be performed at 2 rpm in both the clockwise and counterclockwise direction and in both orientations (serial number side up and serial number side down) per MIL-STD-206.

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3 QUALITY ASSURANCE

3.1 Procedures

The vendor’s quality assurance program shall conform to the provisions of ISO 9001. The vendor is responsible for the performance of all inspections and tests necessary to assure compliance with this specification. Copies of all part inspections performed and material certifications shall be delivered with the bearings in the end item data package. First article inspection reports are required in order to conform with ISO 9001.

3.2 Identification of Product

Full identification of each bearing shall be supplied on each package in accordance with Myonic standard packaging. All information required for full part identification and traceability will be present on bearing and packaging.

3.3 Cleanliness

Each bearing shall be assembled, lubricated, tested, and packaged for delivery in a controlled area. Whenever possible, this controlled area shall meet the requirement of ISO 14644, Class ISO 5 (FED STD 209E Class 100 Equivalent) or better. At a minimum, this controlled area shall always meet the requirement of ISO 14644, Class ISO 6 (FED STD 209E Class 1,000 Equivalent) or better.

3.4 Bearing Cleanliness Inspection Requirements

Clean balls, races and retainers prior to any lubrication operation such that bearings shall pass a filter test using alcohol and a 0.45 micron filter at 30x magnification for 10 pieces to ensure no metallic debris is present.

100% of bearings in lot shall undergo cleanliness inspection at 20X magnification to ensure no general particles are present prior to packaging.

3.5 Inspection

The inspection of each lot delivered shall consist of inspection and acceptance of each bearing in meeting the requirements of this specification. Included with the delivery of the bearings, manufacturer shall report of 100% of the lot’s outer ring outer diameter measurements and inner ring bore measurement.

3.6 Customer Source Inspection

Customer source inspection shall be conducted by the customer at the source’s facility after the bearings have been torque tested and prior to lubrication of bearings with grease.

End item data package (EIDP) corresponding with items in each lot shall be reviewed by GSFC prior to shipment of said lot from the manufacturer to GSFC. This may be performed remotely or in person.

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3.7 Lot Traceability

Each item delivered under this specification shall be identified and be traceable to the manufacturer’s lot and/or control number and date of manufacture. All raw materials used shall be traceable to original receiving reports and chemical analyses. Copies of receiving reports and chemical analyses shall be delivered to GSFC with completed bearings.

3.8 Acceptance

Prior to start of manufacturing, Myonic and NASA GSFC shall hold a manufacturing readiness review. Myonic shall provide a presentation showing their ability to conform to the specification detailed in this document. At a minimum the package shall cover the following areas:

Program Management Quality Assurance Mechanical, and Environmental specifications Manufacturing flow with Government Mandatory Inspection Points Facilities Acceptance Verification Test Plan and Procedures Acceptance Verification Matrix Materials and Processes Contamination Control

All bearings received by NASA/GSFC may be subjected to an acceptance inspection or test to verify compliance with the requirements of this specification.

3.9 Packaging

Each bearing assembly shall be packaged separately in a dry argon and vacuum sealed PE bag, and then vacuum sealed in an aluminum foil coated PE bag, and placed individually with label in a PE pressure-lock bag. Multiple bearing with the above mentioned bagging shall then be packed into a labeled cardboard box. Box shall be marked with the bearing identification code, the type of lubricant, the lot number, and the date of manufacture.

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Figure 3-1 Bearing Dimensions

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Appendix A Abbreviations

DAAC Distributed Active Archive Center DIRWA Demiseable Integrated Reaction Wheel Assembly DTC Design-to-Cost ESD Electrostatic Discharge ESMO Earth Science Mission Operations ETU Engineering Test Unit FDF Flight Dynamics Facility FOT Flight Operations Team GPM Global Precipitation Measurement GS Ground Segment GSE Ground Support Equipment GSFC Goddard Space Flight Center HARP-2 Hyper-Angular Rainbow Polarimeter 2 HSS Hyper-Spectral Scanning KSC Kennedy Space Center LS Launch Segment MID Mechanical Interface Drawing MISR Multi-angle Imaging SpectroRadiometer MOC Mission Operations Center MODIS Moderate Resolution Imaging Spectroradiometer NASA National Aeronautics and Space Administration NEN Near Earth Network NISN NASA Integrated Services Network NOAA National Oceanic and Atmospheric Administration NPR NASA Procedural Document OBPG Ocean Biology Processing Group OCI Ocean Color Instrument PACE Plankton, Aerosol, Cloud, ocean Ecosystem PDL Product Design Lead RWA Reaction Wheel Assembly SCoRe Signature Control Request SDS Science Data Segment SeaWiFS Sea-viewing Wide Field-of-view Sensor SN Space Network SPEXone Spectro-Polarimeter for Exploration SS Space Segment SWIR Short Wave Infrared TDMS Technical Data Management System USGS United States Geological Survey VIIRS Visible Infrared Imaging Radiometer Suite