ENCLOSURE BB - Representative Task Orders Final 02-06-2020-.pdf

ENCLOSURE BB

Date 02-06-2020

NASA

GODDARD SPACE FLIGHT CENTER

REPRESENTATIVE TASK ORDERS (RTO)

FOR

MECHANICAL INTEGRATED SERVICES AND TECHNOLOGIES II

(MIST II)

FOR THE

ENGINEERING AND TECHNOLOGY DIRECTORATE (ETD)

MIST II Representative Task Orders Page 1

Mechanical Integrated Services and Technologies II (MIST II) Representative Task Order (RTO) Summary GRadient, Optical, X-Ray (GROX) Mission

A set of representative task orders (RTOs) has been assembled to cover key elements of the MIST II Statement Of Work (SOW) content. The mission described in the RTOs does not represent an actual NASA mission nor does it reflect a future proposed mission. The purpose of these task orders is to provide the Contractor a sampling of the type of tasks to expect under this Indefinite Delivery/Indefinite Quantity (IDIQ) contract. Contractors shall prepare a response to each RTO and its subtasks using the specified criteria in the proposal instructions. A block diagram and tentative schedule is supplied at the end of this document.

The GROX (GRadient, Optical, X-Ray) Mission is a new Class D technology demonstration mission initiated and managed by the NASA Goddard Space Flight Center (GSFC) as a ride sharing opportunity to take advantage of additional launch capacity on a larger GSFC primary mission called PriMiss. GROX will be designed, integrated, and tested by a team comprised of GSFC Civil Servants and Commercial Contractors. The Contractor will provide engineering and technician services as described in the RTOs below. The GROX mission will be managed by GSFC systems engineers and subject matter expert (SME) discipline engineers. This team will oversee the entire mission and coordinate between secondary payload teams. All SMEs are GSFC employees unless specifically noted in a subtask.

PriMiss will be launched on a SpaceX Falcon 9 launch vehicle. The mission will be launched from Vandenburg Air Force Base into a 98° sun synchronous polar orbit at an altitude of 700km with a 09:00 local time of the ascending node.

GROX will use the Moog COMET Hosted Payload Platform (HPP) to achieve its orbit after separating from the primary payload. The Moog COMET-HPP is an Orbital Maneuvering Vehicle (OMV) based on EELV Secondary Payload Adapter (ESPA) technology. The COMET-HPP is a self-contained vehicle that is able to deliver up to four secondary payloads to a prescribed orbit.

The COMET-HPP will use a standard height 42” ESPA Grande ring with four 24” diameter secondary payload (SPL) ports. It will interface with both the launch vehicle and the primary payload using a standard EELV 62” (1575 mm) bolt circle. The COMET-HPP has its own avionics, power, propulsion, and communications systems that are configurable for the two-year GROX mission. One of the ports will contain a deployable solar array so that adequate power will be supplied for all COMET-HPP and science requirements. See attachment for a block diagram.

The COMET-HPP will be purchased directly from the vendor and its design, analysis and qualification are not a part of these RTOs. The solar array will be purchased directly from a vendor and is not a part of these RTOs. It should be assumed that the fully integrated GROX

MIST II Representative Task Orders Page 2 observatory will undergo environmental testing after the delivery of all the instrument payloads. This will include sine and acoustic vibration, separation shock, thermal vacuum, and EMI/EMC. It will also include all performance testing necessary during environmental testing.

All observatory integration and testing is outside the scope of these RTOs and happen after mission pre-environment review (MPER).

GROX is an assembly of three secondary scientific payloads together with the deployable solar array. Each scientific payload is fully independent from the other payloads. They are each Class D due to the demonstration status. The three secondary payloads make up RTOs 1 through 3. RTO 4 is work that must be performed at the GROX mission level.

RTO 1. – Tether Deployment Demonstrator (TeDD) to demonstrate spacecraft gradient stabilization capabilities and power generation

RTO 2. – X-Ray Microcalorimeter Spectrometer (XMS), a Cryo-cooled X-ray instrument RTO 3. – 3D Pushbroom Scanner (3DPS) Instrument RTO 4. – GROX mechanical interfaces, structural analysis, MGSE, materials

All three secondary scientific payloads are being developed and built in-house at GSFC.

Because of this, there is not enough civil service support available. The use of Contractor support is necessary.

An ambitious 30-month schedule must be maintained so that they will be able to fly with PriMiss. All System Requirements Reviews (SRR) have been completed and management is staffed for each payload. See attachment for tentative GROX schedule.

A “do no harm” approach shall be taken for PriMiss. Any secondary payload that is not fully qualified and delivered for integration when required by PriMiss will be replaced by a mass simulator that will fly in its place on the COMET-HPP.

Note on scheduled milestone due dates: “CDR +2 months” should be read as “CDR plus 2 months” and “CDR –2 months” should be read as “CDR minus 2 months.”

MIST II Representative Task Orders Page 3

RTO 1: Tether Deployment Demonstrator (TeDD)

One of the instruments on GROX is the Tether Deployment Demonstrator (TeDD). TeDD will deploy a tether to study gravity gradient stabilization and generation of electrical power. The tether will permanently deploy from the nadir port of the ESPA ring. The tether will be 1 km long. The tether will have multiple strands, so that it will not fail if a single strand is cut.

The Deployable End-Mass Payload (DEMP) will have a mass of 26 kg. The DEMP will have an internal battery. The DEMP will contain C&DH hardware to allow it to pass telemetry to the main communications system of GROX. The DEMP will contain a three-axis accelerometer to measure movement during and after deployment. The DEMP will contain a tensiometer to measure tension in the tether during and after deployment. The DEMP will contain a three-axis magnetometer for use during and after deployment. The DEMP will contain a camera to monitor the configuration of the tether during and after deployment.

The deployment will be initiated by a spring-loaded device. The deployment mechanism will use closed-loop control. The control will be sufficient to allow the residual swing angle of the tether to be less than 10 degrees from local vertical.

The tether will contain an electrical conductor from end to end to test generation of electricity by the passage of the conductor through the Earth's magnetic field. The return path for the circuit will be by ejection of electrons from one end of the tether and collection at the other end. The conductor will include provision to be disconnected from the electron ejection and collection fixtures, as a way of shutting down that circuit and ending the generation of electricity.

One (1) subtask has been identified for the TeDD.

Subtask (a): Thermal control system for TeDD

The Contractor team shall support the GSFC civil servants in the design, analysis, and verification of TeDD. All work will take place at GSFC, unless otherwise specified in a subtask.

Milestone reviews (PDR, CDR, etc.) reference the TeDD schedule.

Subtask (a): Thermal control system for TeDD The Contractor shall develop and analyze a thermal system for TeDD. The thermal system will apply both to the Deployable End-Mass Payload (DEMP) and to the deployment mechanism attached to the ESPA.

MIST II Representative Task Orders Page 4

Statement of Work for Subtask (a)

1. The Contractor shall support the design effort for the thermal system for TeDD. This task shall include evaluation of thermal and mechanical properties of possible tether materials.

2. The Contractor shall support the creation of thermal models of TeDD. The thermal models shall include the complete system, consisting of DEMP, tether, and section attached to the ESPA. The thermal models shall cover all stages of the mission, including but not limited to test, launch, on orbit before deployment, on orbit during deployment, and on orbit after deployment. The on-orbit thermal model shall allow modeling of cases both while the tether is generating electricity and while it is not. The thermal model shall be in a format compatible with SINDA and Thermal Desktop.

3. The Contractor shall support preparation of materials and presentation of the design at EPRs, at Instrument PDR and at instrument CDR.

4. The Contractor shall support thermal vacuum testing, including developing the test plan.

The test plan shall begin with component tests. The test plan shall include tests to simulate TeDD in the space environment, both before and after deployment. The Contractor shall write the post-test report.

5. The Contractor shall support the development of contamination control procedures to ensure that the radiative heat rejection properties of the DEMP are not compromised.

Government Furnished Equipment For Subtask (a):

• Mechanical CAD models in STEP format for use in creating thermal models

Milestones/Deliverables & Dates for Subtask (a):

Deliverable Due Date

1. Information for selection of tether material BOT +1 months

2. Preliminary design of thermal control system PDR –1 months

3. Presentation materials in support of PDR PDR –2 weeks

4. Thermal model, compatible with SINDA or Thermal Desktop PDR +3 months

5. Thermal vacuum test plan CDR –3 months

6. Materials in support of CDR CDR –2 weeks

7. Materials in support of PER PER –2 weeks

8. Test temperature predictions PER +1 month

9. Correlated thermal model PER +3 months

10. Post thermal vacuum test report PSR –1 month

11. Materials in support of PSR PSR –1 month

MIST II Representative Task Orders Page 5

RTO 2: X-Ray Microcalorimeter Spectrometer (XMS) Development

The XMS instrument measures energy from a single X-Ray Photon. It can simultaneously achieve both high energy resolution and high quantum efficiency while taking spectroscopic data of a spatially extended source. The instrument will aid the study of galaxy clusters by mapping the energy of the intra-cluster medium and tracing the dynamic evolution of the clusters. The instrument will also be helpful in mapping the distribution of dark matter in galaxy clusters and in determining the total mass of the clusters.

The XMS system primary characteristics are:

• Power 200 W Orbit Average Power

• Mass Not to exceed 100 kg

• Energy Range 0.3 – 6 keV

• Array Format 12 x 12

• Field Of View 15.25 cm x 15.25 cm

• X-Ray absorber Au-Bi, 6 µm thickness

• Detector Operating Temp 100 mK

• Pixel size 1600 µm x 1600 µm

• Optical Blocking Filters 4 filters, polyimide (460nm) + AL (400nm) total

Two (2) subtasks have been identified for the XMS instrument.

Subtask (a): Cryogenic Systems Design, Instrumentation and GSE Hardware Support Subtask (b): Adiabatic Demagnetization Refrigerator (ADR) Support

Work will be performed on-site at GSFC under the supervision of a lead cryogenics engineer.

Milestone reviews (PDR, CDR, etc.) reference the XMS schedule, unless otherwise specified in a subtask.

Subtask (a): Cryogenic Systems Design, Instrumentation and GSE Hardware Support

The XMS Instrument includes a X-Ray detector, which requires an active cryogenic system to achieve an operating temperature of 100 mK. The XMS Instrument cryostat, Cryocooler, and ADR is to interface with the thermal control system to provide the required heat rejection.

Work on the ADR is not part of this subtask.

Analysis will be performed using software compatible with Systems Improved Numerical Differencing Analyzer (SINDA), Thermal Synthesizer Systems (TSS), Thermal Desktop or the Thermal Model Generator (TMG) software package. Structural analysis shall be performed for

MIST II Representative Task Orders Page 6 the cryostat intermediate and cold stages support structure. The support structure shall be optimized to minimize the conductive parasitic heat loads.

The instrument requires twenty (20) sensors to provide thermometry that are spread from the COMET-HPP interface to the detector interface. The sensors shall be capable of providing accurate temperatures during the cool down process, from 300 K down to the operating temperature of 100 mK.

A Ground Support Equipment (GSE) cryogenic dewar is required for the instrument testing. The GSE will consist of a test dewar with liquid helium to 4K. Design must include the required liquid helium storage, piping manifold, and the associated control system.

Statement of Work For Subtask (a) Cryogenic Systems Design, Instrumentation and GSE Hardware Support:

1. The Contractor shall support the preliminary design study for a cryogenic system that meets the thermal requirements listed in the RTO.

2. The Contractor shall produce a report detailing the design study.

3. The Contractor shall support preparation of a cryogenic thermal design and analysis of the detector interface. The Contractor shall develop analytical mathematical models, including geometric mathematical models.

4. The Contractor shall prepare system requirements for the cryogenic system, and subsystem verification plans.

5. The Contractor shall support the procurement of a space flight qualified cryocooler and cryostat that meets the requirements of the RTO. This effort requires support for engineering requirements definition, statement of work preparation, and supplier surveillance. GSFC will perform all procurement functions not stated in this subtask.

6. The Contractor shall prepare the plan and procedures for the supplier to characterize the cryocooler and cryostat in a thermal vacuum chamber. The Contractor shall support the cryocooler and cryostat supplier in performance of this test. The Contractor shall perform pre-test cryocooler and cryostat performance modeling, post-test modeling correlations, and generate a report on the at-vender test.

7. The Contractor shall support the design and analysis of conductive pathways, selection of materials, and the design of structural components for the cryocooler and cryostat that will accommodate the required heat transfer between the detector, the cryocooler and cryostat, and its support structure. The Contractor shall generate a report of the design and analysis results.

8. The Contractor shall determine strategies for cryogenic thermometry. The Contractor shall produce a specification for the twenty (20) sensors that will be in the instrument.

The Contractor shall install the sensors into the instrument package.

9. The Contractor shall support the design of the required cryogenic GSE dewar. The Contractor shall generate a report with analysis and drawings of the design.

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10. The Contractor shall support integration of the cryocooler and cryostat into the instrument and thermal system.

11. The Contractor shall support preparation of materials and presentation of the design at EPRs, at Instrument PDR and at instrument CDR.

• All documents from the mission, spacecraft and instrument are available for use, as well as computer math models and mechanical drawings (also in electronic format).

• Ground support equipment for applicable testing.

1. Status report BOT +3 months, then monthly

2. Preliminary design report PDR –1 month

3. Cryocooler and cryostat requirements definition report PDR –1 month

4. Specification for cryogenic thermometry of the instrument

PDR

5. GSE dewar design report PDR

6. Conductive pathways analysis report CDR –1 month

7. Cryocooler and cryostat testing plan and procedure CDR

8. Cryocooler and cryostat test results report CDR +3 months

9. Installation of the cryogenic thermometry CDR +6 months

10. Supplier audit reports Visit +10 days

11. Final Report, including any drawings, analysis, parts, and materials provided at task completion

PSR

Subtask (b): Adiabatic Demagnetization Refrigerator (ADR) Support

To support the operation of the XMS, a two-stage Adiabatic Demagnetization Refrigerator (ADR) system has been selected to achieve and maintain the operational temperature. The two-stage ADR will be capable of rejection of a 0.25 µW detector load. The overall design of the system is led by GSFC. The Contractor shall be responsible for support of the design, analysis and testing.

A heat switch is required to operate the ADR. The heat switch shall operate at a 2 K operational temperature. Heat flow through the switch should be at least 10 mW/K when on and less than 5 µW/K when off. The heat switch must fit within a 50 mm x 50 mm x 200 mm envelope.

Kevlar mechanical structures are required for supporting and thermally isolating the ADR and subcomponents. Wire leads are required to transmit current to the ADR. The leads shall be

MIST II Representative Task Orders Page 8 qualified for 2 amps and shall minimize heat leak into the system. The wire leads shall be capable of operation from 0.5 K - 10 K.

Statement of Work For Subtask (b) Adiabatic Demagnetization Refrigerator (ADR) Support:

1. The Contractor shall support design of a component that enables heat flow when necessary and isolation when required (heat switch or analogous technology). The Contractor shall generate a design study report.

2. The Contractor shall support the design and selection of wire for the magnet leads for the ADR. The Contractor shall generate a design report and selection summary.

3. The Contractor shall support the design and analysis of thermally isolating structures for supporting components within an ADR. The Contractor shall generate a report on the design and analysis of the structures.

4. The Contractor shall support the winding of the magnet wire for use in an ADR.

5. The Contractor shall support the growth of a chromium potassium alum salt pill for use in the ADR.

6. The Contractor shall support the prototyping of small subcomponents using machining tools, such as a mill, lathe, and a drill press.

7. The Contractor shall support the design, fabrication and integration of the cryogenic harness.

8. The Contractor shall support the design, fabrication and integration of thermal straps.

9. The Contractor shall support preparation of materials and presentation of the design at

EPRs, at Instrument PDR and at instrument CDR.

Government Furnished Equipment For Subtask (b):

• All documents from the mission, spacecraft and instrument are available for use, as well as computer math models and mechanical drawings (also in electronic format).

• Ground support equipment for applicable testing.

Milestones/Deliverables & Dates for Subtask (b):

1. Heat switch design study report PDR –1 month

2. Design and selection report for wire leads PDR –1 month

3. Design and Analysis Report for thermally isolating structures PDR –1 month

4. Presentation materials in support of PDR PDR –2 weeks

5. Presentation materials in support of CDR CDR –2 weeks

6. Deliver an ADR magnet BOT +20 months

7. Deliver a Salt Pill BOT +20 months

8. Deliver prototype components BOT +20 months

9. ADR component integration BOT +22 months

MIST II Representative Task Orders Page 9

RTO 3: 3D Pushbroom Scanner (3DPS) Instrument

The third instrument on the GROX mission is an optical scanner. The 3-D Pushbroom Scanner (3DPS) has the ability to both contiguously scan the ground, or to select a discrete target for 3-D analysis. For 3-D analysis, the unit shall be mounted with a single-axis articulation to point off-nadir ±60°, forward or trailing. Once a target is scanned in the nadir-forward position, the scanner can be articulated to re-scan the target at a new off-nadir angle, at nadir, and/or trailing-nadir viewing angles during the spacecraft flyover for a 3-D reconstruction.

The 3DPS images the cross-track scene on the ground to a linear array of 4096 pixels, which are 14 µm pixel pitch. The pixel IFOV resolution is 33 m over the 135 km wide (at nadir) field of view. The along-track scene covers 512 pixels. The along-track rows are covered by a pair of Linear Variable Filters (LVF); the first covering 430 nm to 1.1 µm, and the second covering from

1.5 – 4 µm. A key design objective is the minimization of mass and volume. The use of freeform optical figures may be considered in the design/cost/schedule trade.

Two (2) subtasks have been identified for the 3DPS:

Subtask (a): Design, Fabrication, And Verification of the 3DPS Optical System Subtask (b): The GROX Optical Scanning Mechanism (OSM) for the 3DPS

Support for these subtasks will be under the direction of the GSFC 3DPS Optical Lead with assistance from the GROX SMEs as necessary. All work will take place at GSFC, unless otherwise specified in a subtask. Milestone reviews (PDR, CDR, etc.) reference the 3DPS and OSM schedules.

The mechanical design and analysis of the instrument structure are not part of this RTO. They are being performed in parallel with the optical and mechanism designs. Any required mechanical information is assumed to be available from the mechanical team.

Subtask (a): Design, Analysis, And Verification of the 3DPS Optical System

The Contractor team shall support the GSFC civil servants in the design, analysis, and verification of the optical system. The Contractor team shall perform this work on-site at GSFC.

Statement of Work For Subtask (a)

1. Support the design and analysis for an optical subsystem that will meet the instrument imaging requirements over the lifetime of the mission.

2. The Contractor shall support preparation of materials and presentation of the design at EPRs, at Instrument PDR and at instrument CDR.

MIST II Representative Task Orders Page 10

3. Support analysis of expected performance of the optical system in terms of imaging, stray light, and predicted effects of environmental disturbances.

4. Support the identification of cleanliness requirements to prevent degradation of optical surfaces and coatings.

5. Support the development of the optical error budget for the optical subsystem integration, alignment, and test.

6. Support the development of the optical test and integration plans and procedures.

7. Support the assembly, alignment, and test of the system, including analysis of the metrology results.

8. Support imaging tests of the optical system after instrument environmental tests.

• All required government testing equipment.

1. Ray trace calculations of imaging performance over entire field of view in format compatible with CodeV or Zemax PDR – 4 months CDR – 4 months PER – 4 weeks

2. Stray light analyses in format compatible with FRED PDR – 2 weeks CDR – 3 weeks PER – 4 weeks

3. Presentation materials in support of PDR PDR – 2 weeks

4. Presentation materials in support of CDR CDR – 3 weeks

5. Report of results of evaluation of cleanliness requirements PDR

CDR

6. Inputs to error budget development CDR

7. Imaging test results report with analysis PER

8. Post environmental imaging test results with analysis PSR – 1 month

Subtask (b): The GROX Optical Scanning Mechanism (OSM) for the 3DPS

The Contractor shall develop a detailed design for the flight Optical Scanning Mechanism (OSM) that meets or exceeds the requirements listed below. The Contractor shall support the fabrication process, assembly, test, and delivery of a flight qualified OSM. Drive control electronics design and testing are not part of this task. No additional instruments or sensors are mounted on the scanner. Ground operation testing of the OSM will be performed in 1G. The OSM provides three position push broom motion in support of the GROX 3D Pushbroom Scanner Instrument Optical System.

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The 3DPS system primary characteristics are:

• Precision assembly single drive axis mechanism.

• Includes a +/- 60° 3D scanning mechanism and optics; push broom with a range of possible scanning points from +60° nadir-forward to -60° nadir-trailing.

• Coordinate system origin at COMET-HPP port 4 outer surface at center of bolt circle

• OSM operational temperature range (measured at the housing and lubricated drive components): 273 K to 303 K.

• OSM survival temperature range (measured at the housing and lubricated drive components): 253 K to 323 K.

Statement of Work For Subtask (b) for the GROX Optical Scanning Mechanism (OSM):

1. The Contractor shall support required OSM peer reviews, 3D Pushbroom Scanner (3DPS) Instrument Optical System and mission-level PDR, CDR, PER, and PSR, as well as other reviews that occur during the task period of performance.

2. The Contractor shall develop a detailed design for the OSM that meets requirements.

Produce CAD model and fabrication drawings. Provide supporting documentation.

3. The Contractor shall perform structural analysis on the OSM design and provide supporting documentation.

4. The Contractor shall develop environmental test plans and test reports for thermal and vibration testing (random and sine), and provide test support.

5. The Contractor shall support fabrication, procurement, assembly, and integration of the flight OSM in accordance with Quality Assurance (QA) protocols.

6. The Contractor shall demonstrate torque margin compliance with GEVS and provide a torque margin compliance report.

7. The Contractor shall develop a life test plan for the OSM and provide support for the life test of the OSM.

Government Furnished Equipment For Subtask (b):

• All government performance and life testing equipment

MIST II Representative Task Orders Page 12

1. OSM CAD model Initial: PDR – 1 month

Update: CDR – 1 month

2. OSM Fabrication drawings Drawings to be released periodically as needed

3. OSM Structural analysis Initial: PDR – 1 month

Update: CDR – 1 month

4. OSM Life Test Plan CDR – 1 month

5. OSM Vibration Test Plan CDR + 2 months

6. OSM Thermal Test Plan CDR + 2 months

7. OSM Vibration Test Report Test + 1 month

8. OSM Thermal Test Report Test + 1 month

9. OSM Torque Margin Compliance Report Test + 1 month

MIST II Representative Task Orders Page 13

RTO 4: GROX Mission-level Subtasks

A significant amount of contract support will be required to finish the development of the GROX observatory on time. This work will include mission-level mechanical engineering and structural analysis support for interface control documentation, mechanical ground support equipment, mechanical engineering support for mass simulators, and materials engineering support.

Five (5) subtasks have been identified.

Subtask (a): Mechanical Interface Control Documents (MICD) Subtask (b): GROX Structural Analysis Subtask (c): Development of Mass Simulators Subtask (d): GROX Transportation GSE Subtask (e): GROX Materials & Processes

Contractors shall work alongside civil servant engineers and under the direction and supervision of the GROX SMEs (unless otherwise noted) and attend regularly scheduled weekly meetings, occasional technical meetings, and reviews as needed. Contractors shall support major scheduled reviews, providing documentation ensuring that relevant mission requirements are being met. All work will be performed on-site at GSFC unless otherwise specified within the subtask. Mission milestone reviews (MPDR, MCDR, and MSIR) reference the GROX schedule.

Additional mission milestones include the MPER at BoT + 36 months and MPSR at BoT + 42 months.

Subtask (a): GROX CAD Model and Mechanical Interface Control Documents (MICD)

Contractor support shall be required to assist the GROX project in the development of mechanical systems requirements as related to interfaces between the COMET-HPP and the payloads, generate an integrated mission CAD model, generate a deployed CAD model for field-of-view studies, prepare interface control documents and drawings, provide mission-level CAD-based mass estimates, and provide assembly and integration drawings. No instrument-level work shall be performed on this task. The civil servant GROX Mission Lead Mechanical Engineer is the point of contact and technical monitor for the Contractor team and shall oversee all Contractor support.

Statement of Work For Subtask (a) GROX MICD:

1. The Contractor shall develop and maintain an integrated stowed 3D CAD model of the GROX spacecraft, compatible with STEP file format. The CAD model will consist of the

MIST II Representative Task Orders Page 14

Moog COMET-HPP, the solar array, and the instrument models. The model will be used to verify interfaces and static envelopes between the OMV and the instruments, as well as for launch vehicle envelopes. The spacecraft and instrument models shall have sufficient detail to ensure that all mechanical interface requirements are satisfied. The Moog -HPP, TeDD, XMS, and 3DPS, Solar Arrays and other subsystem CAD models shall be supplied separately.

2. The Contractor shall prepare draft versions of interface control documents and mechanical interface control drawings. Drawings shall be compliant with all GSFC and ISO requirements. All mission hardware interfaces shall be addressed, which include the mechanical interfaces and static and dynamic envelopes between the COMET-HPP and the secondary payloads and the overall GROX spacecraft and the Falcon 9 launch vehicle.

3. The Contractor shall prepare CAD drawings to be used in preparation of GROX integration/assembly.

4. The Contractor shall attend weekly meetings scheduled by the Mechanical Lead Engineer and shall be prepared to discuss the status of the mechanical design.

5. The Contractor shall support required engineering peer reviews and instrument and mission-level PDR, CDR, and PER, as well as other reviews that may occur during the task period of performance.

• 3-D Pro Creo CAD models of the COMET-HPP and the solar array in STEP format.

• 3-D Pro Creo CAD models of the TeDD, XMS and 3DPS instruments in STEP format.

• Computer workstations (non-portable) with GSFC-licensed Creo CAD/CAE software installed.

1. Mechanical interface control drawings and documents Drawings:

Initial: BOT + 4 months Updates: 2 months prior to MPDR, MCDR, MSIR, MPER, and MPSR.

Documents:

Initial: BOT + 6 months Updates: 2 months prior to MPDR, MCDR, MSIR, MPER, and MPSR.

2. Spacecraft Integrated CAD model Initial: MPDR – 1 month Updates: 1 month prior to MCDR, MSIR, MPER, as well as periodic updates as needed

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3. Released flight hardware integration/assembly drawings

Drawings to be released periodically as needed

4. Presentation data packages 1 month prior to MPDR, MCDR, MSIR, MPER, and

MPSR

Subtask (b): GROX Structural Analysis

Contractor support shall be required to develop, maintain, and update the GROX mission finite element model (FEM) and perform finite element analysis (FEA) to develop observatory loads that will be used during both structural analysis and hardware testing. No instrument-level analysis will be performed for this task. Each instrument shall provide its FEM to the Contractor for integration onto the GROX mission FEM. The civil servant GROX Mission Lead Structural Analyst is the point of contact and technical monitor for the Contractor team and shall oversee all Contractor support.

All FEA shall be performed using MSC Nastran or a compatible solver. FEA pre- and post-processing solvers shall be MSC Nastran compatible.

Statement of Work For Subtask (b) Structural Analysis Support:

1. The Contractor shall develop and maintain the GROX observatory FEM. The FEM shall be used for all observatory-level static and dynamic structural analyses. The FEM shall be constantly updated through the design process, and it must reflect the 3-D CAD model as it reaches maturity. For consistency, the Contractor is responsible for the management of the entire GROX FEM numbering, including instrument numbering and common interface grids.

2. The Contractor shall perform validity checks, prior to any FEM analysis, to ensure the mathematical accuracy of the model.

3. The Contractor shall prepare a FEM Report that documents mass distribution, numbering of elements, type of elements, validity checks, materials, normal modes, etc.

4. The Contractor shall create a Craig-Brampton model of the observatory suitable for Coupled Loads Analysis (CLA) on the Falcon 9 launch vehicle.

5. The Contractor shall perform GROX-level analyses required to develop static and sinusoidal design limit loads for the instruments. The initial analysis shall use Falcon 9 Payload Planners Guide loads. The analyses shall be updated when CLA results are obtained.

6. The Contractor shall perform observatory analyses required to prepare for sine vibration and acoustic testing of the observatory.

7. The Contractor shall write test plans in preparation for the observatory MPER for both sine vibration and acoustic testing. (Test support is not a part of this subtask.)

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8. The Contractor shall attend weekly meetings onsite at GSFC scheduled by the GROX project and shall be prepared to discuss status of the FEM and current analysis. The Contractor shall provide analysis status and/or results reports in support of these meetings.

9. The Contractor shall support required engineering peer reviews and mission-level PDR, CDR, and PER, as well as other reviews that may occur during the task period of performance. Assume all reviews will be held onsite at GSFC.

Government Furnished Equipment For Subtask (b):

• Finite Element Model of the COMET-HPP Orbital Maneuvering Vehicle.

• Finite Element Model of the three GROX instruments.

• Reduced Finite Element Model of the solar array directly from the vendor.

• PriMiss Coupled Loads Analysis results that include the GROX ride share

1. Integrated GROX FEM Initial: BOT + 6 months

Updates: As required to support instrument design and analysis

2. FEM views, modal animations, and analysis results for MPDR, MCDR, and MPER

3 weeks prior to MPDR, MCDR, and

MPER

3. Craig-Bampton model for CLA Initial: MPDR + 1 months Update: MCDR + 1 months

4. FEM report Initial: MPDR – 1 month Updates: MCDR – 1 month Final: MPER – 1 month

5. Sine Vibe Test Plan MPER – 1 month

6. Acoustic Test Plan MPER – 1 month

Subtask (c): Development of Mass Simulators

Mass simulators for the TeDD, the XMS, and the 3DPS shall be required. Contractor support shall be required to design, analyze and support fabrication/procurement of mass simulators to be used if the actual flight units are not available. Fabrication will be done out-of-house, but procured through GSFC. Any assembly of the instrument mass simulators shall be done by the Contractor using GSFC facilities. Because these mass simulators may fly on the GROX mission, care must be taken to ensure all flight hardware cleanliness processes are maintained. Mass

MIST II Representative Task Orders Page 17 simulators may be used for structural testing if required by the GROX mission. Contractor shall work closely with but independently from the three instrument teams to obtain specifications/details/requirements for the implementation of the subtask. The solar array shall not be considered for this subtask because it is assumed to be a COTS procurement.

Statement of Work for Subtask (c) :

1. The Contractor shall design, create drawings, analyze, and support procurement of mass simulators for the GROX instruments. Structural analyses shall use mass acceleration curve limit loads.

2. The Contractor shall write a stress report that summarizes all stress analysis, including all margins of safety, performed on the mass models. This includes qualifying the design without testing.

3. The Contractor shall support the procurement of mass simulator parts and perform assembly/integration of the mass models of the payloads.

4. The Contractor shall support assembly, disassembly, and transportation of the mass simulators if they are used to support qualification or acceptance testing of flight hardware. These tests may include but are not limited to sine vibration and/or acoustic testing. (Assume transportation cases are available at GSFC.)

5. The Contractor shall support required engineering peer reviews and mission-level PDR, CDR, PER, and PSR, as well as other reviews that occur during the task period of

Government Furnished Equipment For Subtask (c):

• Finite Element Model of the TeDD, XMS, and 3DPS, and the Solar Array payloads

• Finite Element Model of the Moog COMET-HPP

Milestones/Deliverables & Dates for Subtask (c):

1. Mechanical Drawings for all mass simulators 2 months after final instrument PDR

2. Stress Analysis Report for all mass simulators Initial: MPDR – 1 month

Update: MCDR – 2 months Final: MPER – 1 month

3. Fabricated and assembled mass simulators MCDR + 2 months

MIST II Representative Task Orders Page 18

Subtask (d): GROX Transportation and Lifting MGSE

Transportation dollies and lift sling ground support equipment shall be required for the GROX spacecraft. These will be done at the mission level to streamline the process and possibly reduce the amount of MGSE equipment. Lift slings will be required for the spacecraft, the three individual instruments and the solar array assembly. The dollies shall be designed so that the spacecraft and instruments can be rotated 90 degrees if necessary for assembly and inspection of the spacecraft and instruments.

Statement of Work for Subtask (d) Transportation Ground Support Equipment (GSE) for the GROX Spacecraft

1) The Contractor shall design, create drawings, and support fabrication of MGSE equipment for the GROX instruments and GROX observatory in accordance with Quality Assurance (QA) protocols.

2) The Contractor shall perform structural analyses on MGSE designs and provide reports.

3) The Contractor shall write a stress report that summarizes all stress analyses performed on the MGSE, including all margins of safety.

4) The Contractor shall develop structural test plans and test reports for the MGSE dollies and slings and provide test support.

5) The Contractor shall support required peer reviews and both instrument PDRs, CDRs, PERs and PSRs as well as mission-level MPDR, MCDR, MPER. Assume all reviews will be held onsite at GSFC.

Government Furnished Equipment For Subtask (d):

• 3-D Pro Creo CAD models of the COMET-HPP and the solar array in STEP format.

• 3-D Pro Creo CAD models of the TeDD, XMS and 3DPS instruments in STEP format.

Milestones/Deliverables & Dates for Subtask (d):

1. Mechanical Drawings for MGSE dollies and slings 3 months after final instrument PDR

2. Stress Analysis Report for all MGSE dollies and slings Initial: PDR – 1 month Update: CDR – 2 months Final: PER – 1 month

3. Fabricated and Assembled MGSE MCDR + 3 months

4. Strength/Proof Test Plans MCDR + 3 months

5. Strength/Proof Test Reports Proof Tests + 4 weeks

MIST II Representative Task Orders Page 19

Subtask (e): GROX Materials & Processes

A GROX lead Materials & Processes Engineer (MPE) shall be required for this task. The Contractor MPE will lead the GROX Materials & Processes subsystem and serve as the point of contact between the GROX project and the Materials Engineering Branch Contractor lab engineers and other Contractor subject matter experts. The MPE will be required to provide technical expertise on materials selection and process development to the in support of all GROX hardware. The Contractor shall provide additional support as needed for materials engineering laboratory operations associated with the testing, evaluation, and failure analysis of materials used in space flight projects.

Statement of Work for Subtask (e) GROX Materials & Processes

1. The Contractor shall perform chemical analysis to identify contamination species, outgassing species, and chemical composition for polymeric and organic materials used in GROX hardware as needed, and provide test reports to GROX project.

2. The Contractor shall perform chemical analysis of cold finger and cold plate rinses to verify cleanliness of TVAC chambers that process GROX hardware during I&T, and provide test reports to GROX project.

3. The Contractor shall perform mechanical testing on parts and test specimens/coupons, including determination of mechanical properties to feed into structural analyses, and proof testing of hardware, and provide test reports to GROX project.

4. The Contractor shall perform non-destructive evaluation inspections, including X-ray scans, to detect flaws and verify construction of components and assemblies, and provide test reports to GROX project.

5. The Contractor shall perform Failure Analysis of hardware and parts to identify material-related issues that contributed to the failure. These analyses will utilize various instruments and equipment such as optical microscopes and scanning electron microscopes, and may incorporate analyses done by other lab personnel in the branch.

Results, conclusions, and recommendations of these analyses will be documented in lab reports and memos to the GROX project.

6. The Contractor shall perform Polymeric Applications such as custom mixes of flight polymerics, shelf life extensions, incoming/inspections tests of polymeric materials, cleaning of hardware, and bakeouts of parts and harnessing to meet outgassing requirements.

7. The Contractor MPE shall work with Materials Engineering Branch management to develop a Materials & Processes Control Plan for the GROX mission

8. The Contractor MPE shall compile, review, and approve Materials Identifications and Usage Lists that are developed in collaboration with payload subsystem lead engineers, as well as supporting Materials Usage Agreements that are collected from payload subsystem lead engineers.

MIST II Representative Task Orders Page 20

9. The Contractor shall support required engineering peer reviews and mission-level PDR, CDR, PER, and PSR, as well as other reviews that occur during the task period of

Government Furnished Equipment For Subtask (e):

• Computer workstations, in labs and offices

• Analytical equipment needed for all laboratory analyses

• Solvents, chemicals, and other lab consumables used in testing and analysis

• Test fixtures needed for part and specimen testing

Milestones/Deliverables & Dates for Subtask (e):

1. Mission Level Materials & Processes Control Plan Mission PDR – 3 months

2. Submit Preliminary Design Materials Identification

Usage List (MIUL) MPDR – 1 month

3. Submit As-Designed Materials Identification Usage List

(MIUL)

MCDR – 1 month

4. Approve As-Built Materials Identification Usage List (MIUL) with Material Usage Agreements (MUAs)

MPER

5. Reports on chemical analysis of hardware and materials As required by project

6. Reports on chemical analysis to verify cleanliness of

TVAC chambers Throughout Environmental Testing

7. Reports on mechanical properties testing As required by project

8. Reports on NDE inspection results As required by project

9. Memos and Reports on failure analysis As required by project

MIST II Representative Task Orders Page 21

Acronyms and Definitions

3DPS 3-D Pushbroom Scanner ADR Adiabatic Demagnetization Refrigerator BOT Beginning Of Task BRDF Bidirectional Reflectance Distribution Function C&DH Command and Data Handling CAD Computer Aided Design CAE Computer Aided Engineering CDR Critical Design Review CLA Coupled Loads Analysis cm Centimeter CODE V™ Optical Design Software by Optical Research Associates (ORA) COTS Commercial Off The Shelf DEMP Deployable End-Mass Payload EOT End of Task EPR Engineering Peer Review ESPA Expendable Launch Vehicle Secondary Payload Adapter FEA Finite Element Analysis FEM Finite Element Modeling FEMAP™ Finite Element Modeling and Post Processing FOV Field of View FRED™ Optical Software Engineering Package by Photon Engineering GEVS General Environmental Verification Standard GROX GRadient Optical X-Ray Mission GSE Ground Support Equipment HPP Hosted Payload Platform I&T Integration and Testing ICD Interface Control Document IDIQ Indefinite Delivery/Indefinite Quantity IFOV Instantaneous Field of View ISO International Organization for Standardization K Kelvin Kg Kilogram km Kilometer LVF Linear Variable Filters m Meter MGSE Mechanical Ground Support Equipment MCDR Mission Critical Design Review MICD Mechanical Interface Control Document/Drawing

MIST II Representative Task Orders Page 22

MIUL Materials Identification and Usage List MPDR Mission Preliminary Design Review MPER Mission Pre-Environmental Review mK Milli-Kelvin mm Millimeter MSIR Mission Systems Integration Review MUA Materials Usage Agreement mW Milliwatt µm Micrometer (Micron) nm Nanometer OMV Orbital Maneuvering Vehicle OSM Optical Scanning Mechanism PDR Preliminary Design Review PER Pre-Environmental Review PSR Pre-Ship Review QA Quality Assurance RTO Representative Task Order SINDA™ Systems Improved Numerical Differencing Analyzer software STEP A standardized file format for CAD and other model files STOP Structural Thermal Optical TCON™ Thermal modeling tool TCS Thermal Control Systems TeDD Tether Deployment Demonstrator TMG Thermal Model Generator TOMS Task Order Management System TSS Thermal Synthesizer Systems Vis Visible W Watt XMS X-Ray Microcalorimeter Spectrometer

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