Attachment 1_GoSwift_test_Pod_SOW.pdf

STATEMENT OF WORK

GEORMETRY OPTIMIZATION AND SENSING WITH

INTEGRATION AND FLIGHT (GOSWIFT) AERODYNAMIC

RESEARCH TEST POD

DATE: 22 APRIL 2026

National Aeronautics and Space Administration Armstrong Flight Research Center Edwards, California

1. Background

2. Scope of Work

3. General Requirements

4. Technical Requirements

5. Manufacturing Requirements

6. Ground Handling Cart requirements

7. Deliverables

8. Quality Assurance Requirements

9.Period of Performance

Table 1 Proposed Schedule

10. Place of Performance

11. Risk Reduction Prototype

12. Configuration Management

13. Export Control

14. Reference Documents

Appendix A – Reference Geometry Diagram

Fig. 1 Conceptual Pod Image

Fig. 2 Inside View Conceptual Pod Image

Fig. 3 Conceptual Pod Drawing

Fig. 4 Ground Handling Keep out zones

Fig. 5 Ground Handling Cart Modular Needs

Appendix B – Critical Parts Definitions

Fig. 6 GEN-00611-011 Cone Rear Ring

Fig. 7 GEN-00613-001 Rear Forward Ring

Fig. 8 GEN-00612-007 & Mirror Part GEN-00612-003 Rear Forward Ring

Fig. 9 GEN-00612-015 & Mirror Part GEN-00612-007 Rear Forward Ring

Fig. 10 GEN-00612-009 Ring Front

Fig. 11 GEN-00612-011 Ring Rear

Fig. 12 GEN-00612-013 Ring Rear Middle

Fig. 13 GEN-00612-005 Ring Front Middle

Fig. 14 GEN-00612-033 Middle Backbone

1. Background The objective of this effort is to design, manufacture, and deliver an aerodynamic test pod that maintains the Outer Mold Line (OML) of a standard centerline 610-gallon external fuel tank used on the F-15D aircraft.

The pod will support aerodynamic and flight test activities while providing internal volume for instrumentation and test equipment.

GOSWIFT is a Flight Demonstration and Capabilities (FDC) Subproject and is proceeding toward Preliminary Design Review (PDR). The contractor is expected to work collaboratively with the program engineering team by attending the PDR and the Critical Design Review (CDR) to refine the design, resolve manufacturability considerations, and ensure the configuration is suitable for fabrication and flight test. Additionally, NASA anticipates additional consultations with the contractor between the PDR and CDR.

2. Scope of Work

The contractor shall provide engineering support, manufacturability analysis, fabrication, assembly, inspection, and delivery of at least one flight-ready aerodynamic test pod conforming to the detailed design provided by NASA. In addition to the test article, the contractor will design and fabricate a ground handling cart for storage, maintenance, and for upload of the test article to the F-15D. Perform a loads and stress analysis showing that the ground cart has positive structural margins.

Requirements for the test article are given in Section 3 and requirements for the ground handling cart are given in Section 6 The pod design will conform to the OML of the F-15D centerline 610-gallon fuel tank.

The contractor shall collaborate with the program engineering team to ensure the NASA produced design, which meets structural, aerodynamic, and integration requirements, remains manufacturable within schedule constraints.

The contractor shall deliver one flight-ready pod (with an option for up to two additional pods) and complete documentation packages.

3. General Requirements

3.1 The contractor shall provide engineering support for PDR and CDR, including but not limited to manufacturing feasibility assessments, fabrication strategies, tooling concepts, and inspection strategies.

3.2 The Contractor shall provide project management support for the work accomplished under this statement of work such as schedule, cost, and technical supervision.

3.3 The contractor shall provide weekly project status reports via teleconference or onsite.

The status reports shall cover important schedule updates highlighting changes to project schedule, problem reports identifying, tracking and discussing project risks and any change request in respect to the design.

3.4 For all reviews other than the weekly status updates, provide an agenda, presentation charts, and an updated schedule with task percent completion at each review.

Preliminary presentation materials shall be provided to the COR no later than 3 business days prior to each review.

4. Technical Requirements The following definitions differentiate between requirements and other statements contained in this statement of work:

Shall This is the only verb used for binding requirements.

Should/May These verbs are used for stating non-mandatory goals.

Will This verb is used for stating facts or declaration of purpose.

4.1 Critical parts defined in Appendix B shall be manufactured as one solid piece and documented with photographic evidence and provided to NASA before installation.

4.2 Primary structure shall be manufactured from aerospace-grade 7050-T3511 and 6061-

T6 aluminum and 17-4PH Stainless steel. Material traceability documentation shall be provided.

4.3 The aerodynamic test pod shall be manufactured to the final, detailed design and drawings provided by NASA. The contractor must submit requests for changes in the final design to NASA for review and approval prior to fabrication of impacted parts.

4.4 The structure shall hold conformance to the design requirements and measurements to be specified in drawings provided by NASA.

4.5 Internal provisions shall support installation of instrumentation, cabling, and mounting brackets as defined in the final configuration.

4.6 All interior surfaces shall have all sharp edges removed to prevent instrumentation damage.

4.7 All drawing numbers shall be etched on each model part in an area that is internal to the structure.

4.8 The contractor may suggest design changes for ease of manufacturability accompanied with stress report to be considered during the PDR phase.

5. Manufacturing Requirements

5.1 Manufacturing activities include fabrication of aluminum structural components, machining, assembly, installation of access features, and dimensional verification against OML requirements.

5.2 Contractor shall procure materials and hardware that are new and unused.

5.3 All test article materials including fasteners shall be Mil-spec or aerospace grade certified (e.g. NAS, AS). Data sheets and certs shall be provided for all materials and fasteners.

5.4 All fasteners shall have positive locking features.

5.5 The Contractor shall permit NASA Technical staff to have access during the manufacturing build on a non-interference basis, during pre-scheduled intervals. This requirement allows NASA technical staff to complete minor non-contract tasks as needed.

5.6 The Contractor shall provide access to NASA personnel to inspect the test article prior to and during fabrication. Depending on the design, Government Mandated Inspection Points (GMIPs) may be requested at critical points in the fabrication process.

5.7 The Contractor shall apply appropriate aircraft corrosion protection finishes, sealants, primer, and paint (interior and exterior) for the pod including any required touch-up finishing/paint.

5.8 Contractor shall adhere to the following requirements:

1. All tolerances apply to the hardware while measured shall be in an unrestrained, assembled condition

2. No shims shall be used

3. No welding shall be used

4. No filler materials shall be used on the external surface without approval from NASA

5. Step height shall not exceed 0.01 inch

6. All gaps shall be no greater than 0.03 inch

7. All interior surfaces shall have all sharp edges removed to prevent instrumentation damage

8. All drawing numbers shall be etched on each model part in an area that is not in an internal or external flow or on a sealing surface

9. Material finishes for metallic surfaces shall provide chemical conversion (anodize) for all internal aluminum surfaces and passivation for all steel surfaces (internal and external)

6. Ground Handling Cart requirements A ground handling cart is required to facilitate storage, work and maintenance, and upload of the test article to the aircraft. The model and flight test results are sensitive to minute scratches and dings that could happen during ground handling, and the handling cart should have basic design features that preclude any ground/support hardware from coming into contact with the test article. Requirements are specified below.

6.1 Contractor shall adhere to the STANDARD FOR THE DESIGN AND FABRICATION OF

THE GROUND SUPPORT. EQUIPMENT NASA-STD-5005D

6.2 The ground handling cart with test article installed shall be able to easily roll/rotate on a concrete surface

6.3 The ground handling cart shall have the ability to lock the wheels in place

6.4 The ground handling cart shall support the individual modular sections of the pod to facilitate internal installation

6.5 The ground handling cart shall be designed to avoid designated keep out zone defined in

Figure 4

6.6 The cart shall be designed to hold Nose cone, center body and aft cone separately and must connect for transport of fully integrated pod as shown in Figure 5.

6.7 The ground handling cart shall hold the full pod weight capability of 4000 lb.

6.8 The ground handling cart shall allow for uninhibited access to three center bays as defined in Pod drawings

6.9 The ground handling cart shall have the ability to lift the test article 10 inches in the vertical direction for upload to the aircraft. Lifting equipment shall have a locking feature to prevent back travel.

6.10 All materials and fasteners shall be Mil-spec certified

6.11 The cart shall be designed avoid tipping in all configurations

6.12 Contractor shall provide operating and maintenance (e.g., inspection points and intervals) instructions for the ground handling cart for use with and without pod assembly

6.13 The Contractor shall apply appropriate aircraft corrosion protection finishes, sealants, primer, and paint (interior and exterior) for ground handling cart including any required touch-up finishing/paint.

6.14 The drawings shall also include all special process and procedure notes such as material finishing, electrical bonding, oxygen service cleanliness requirements, etc. The Contractor shall deliver to NASA any referenced process specifications that are not easily obtained by NASA in the open market. The Contractor shall deliver all drawings in either AutoCAD DXF/DWG format (preferred) or Adobe vector PDF (i.e. not bitmap) and all 3D CAD models in native and STEP formats.

The ground handling cart shall be designed using a factor of safety Factory of Safety (FS) of 3 for all frame structures and a FS of 5 for all lifting components. A simplified stress report shall be provided for the ground handling cart showing positive margins for all components.

7. Deliverables The Contractor shall deliver an electronic data package containing all data generated/required for the modification. All documents shall be legible and complete. The Contractor shall provide the Government with an unlimited rights license to use the data.

7.1 Programmatic Deliverables

1. Project Milestone Schedule (DRD-01)

2. Project Status Reports (DRD-02)

i. Agenda, presentation charts, and an updated schedule with task percent completion at each review outside of update meeting. (DRD-02)

7.2 Engineering Deliverables

1. PDR Manufacturability and Engineering Support (DRD-03)

a. Provide written concerns and recommendations 5 days after -PDR

2. CDR Manufacturability and Engineering Support (DRD-04)

a. Attend a 2-day meeting at AFRC

b. Provide written concerns and recommendations within 5 days

3. Ground Handling Cart Preliminary Design Review (DRD-05)

4. Ground Handling Cart Final Design Review (DRD-06)

5. Fabrication package (as-built) for ground cart (DRD-09)

6. CAD model of the ground handling cart in IGES, STEP, and native CAD formats (DRD-

9)

7. Loads and Stress Report (DRD-08)

Documenting the structural analysis method and margin of safety for all ground handling cart components

8. Verification and Validation Plan (DRD-10)

9. Fabrication drawings (as-built) for Pod (DRD-17)

10. Certificates of Conformance & Manufacturer’s Test Reports (MTRs) (DRD-18) for all materials and fasteners used for the test pod and the ground handling cart

11. Operating and maintenance manual ground handling cart (DRD-13) (e.g., inspection points and intervals) instructions for the ground handling cart for use with and without pod assembly.

12. Operating and maintenance manual for pod (DRD-15) (e.g., inspection points and intervals) instructions for pod

13. Tool Control Plan (DRD-14)

7.3 Reports

1. Verification and Validation Reports (DRD-12) for ground handling card and pod

2. Handling and installation guidance if off nominal to standard handling defined in

SUU-60 Centerline Pylon Removal and Installation 1F-15C-2-94JG-32-21 and External Fuel Tank Removal and Installation 1f-15c-2-05JG-00-15 (DRD-15)

3. Weight & Balance report (DRD-19)

4. List of Deviations (DRD-16)

5. Test Plans and Reports (DRD-12)

a. Test Plans due 15 days after award of contract

b. Test Reports due at Acceptance Review

6. Critical Parts Photos (DRD-7) Photographic evidence of machined critical parts before and after installation

7.4 Hardware Deliverables

1. One (with an option for a second) fully assembled flight-ready aerodynamic test pod(s)

2. One ground handling cart

3. Any special handling equipment designed during the process

7.5 Shipping

The test pod and ground handling cart shall be shipped to NASA Armstrong Flight Research Center (AFRC) after fabrication/assembly checks have been completed.

8. Quality Assurance Requirements

8.1 The Contractor shall establish and maintain a Quality Assurance (QA) program to ensure all work performed under this contract complies with contractual requirements, applicable regulatory requirements, and recognized aerospace industry standards. The QA program shall govern the design, fabrication, inspection, testing, documentation, and delivery of the aerodynamic test pod and all associated components and shall ensure traceability, configuration control, and verification of all hardware, materials, and processes used in manufacture and integration of the test article.

8.2 The Contractor shall provide and maintain a documented Quality Management System compliant with AS9100D.

8.3 The Contractor’s inspection program shall ensure compliance with applicable engineering specifications. The Contractor shall utilize a Quality Manual applicable to work performed under this contract and maintain quality records sufficient to provide traceability, accountability, and a historical record of design, inspection, testing, qualification, and acceptance of materials and components.

8.4 The Contractor shall implement configuration management processes to control the design, fabrication, and integration of the aerodynamic test pod. The design shall maintain the OML geometry of the standard centerline 610-gallon external fuel tank used on the F-15D aircraft to preserve aerodynamic characteristics.

8.5 Design documentation shall include engineering drawings, analyses, materials specifications, interface documentation, weight and balance information, and as-built configuration records. Deviations from approved design documentation shall not be implemented without Government approval. Following Government approval of the aircraft modification design, GMIPs will be established to allow Government inspection of selected modification and integration activities.

8.6 The Contractor shall perform inspection and testing necessary to verify that the aerodynamic test pod conforms to design requirements and aircraft interface constraints. Inspection activities shall include verification of incoming materials, in-process fabrication, dimensional conformity, structural integrity, and aircraft mounting interface compatibility.

8.7 The Contractor shall establish procedures for the identification, documentation, segregation, and disposition of nonconforming articles, materials, equipment, or services. Nonconformance includes failures, discrepancies, deficiencies, defects, anomalies, or malfunctions relative to specified requirements. Nonconforming items shall not be incorporated into deliverable hardware unless properly dispositioned and accepted by the Government when required.

8.8 The Contractor shall be responsible for quality assurance of all vendors, suppliers, and subcontractors providing materials, components, or services under this contract and shall verify supplier compliance with applicable standards.

8.9 The Contractor shall maintain a positive tool control system to ensure accountability of tools and prevent foreign object damage during work performed under this contract.

The Contractor shall also maintain an acceptable metrology and calibration recall system to ensure that tools and measurement equipment requiring calibration remain within current calibration intervals. Contractors not in compliance with this requirement shall propose an alternative method of tool control.

8.10 Government contract quality assurance, inspection, and surveillance may be performed by NASA or other Government representatives in accordance with the inspection clause of the contract and applicable NASA FAR Supplement requirements.

The Contractor shall provide access to facilities, records, documentation, and personnel necessary to support Government inspection and Oversight activities.

8.11 The Contractor shall provide quality documentation with the delivered aerodynamic test pod including certificates of conformance, material traceability documentation, inspection and test reports, as-built configuration documentation, and records associated with non-routine repairs. The Contractor shall submit warranty claims on behalf of the Government when applicable and shall pass through any supplier warranties obtained under this contract.

9.Period of Performance The period of performance begins at contract award and is expected to take 14 months.

Contractor milestones with durations referenced from contract start are show in Table 1.

NASA will provide finalized drawings 10 days after design considerations and manufacturability considerations have been analyzed for structural integrity and dynamics, approved by the NASA Structural and Dynamics teams.

Table 1 Proposed Schedule Milestones Target Dates

Kick Off meeting at Contractor Within 5 days of award of contract

Preliminary Design Review at Contractor Within 5 days of award of contract

Project Schedule 5 days after award of contract

Design Considerations/ Manufacturability assessment 5 days after PDR

Critical Design Review (face-to-face at AFRC) 60 days after PDR

Design Considerations/ Manufacturability assessment 5 days after CDR

Update meeting 5 days after final design consideration submittal

Status meeting Weekly

Ground Cart preliminary engineering drawings meeting 5 months after award of contract

Ground cart preliminary engineering drawings delivered to AFRC for ground cart 48 hrs. after meeting

Ground Cart final engineering drawings meeting 8 months after award of contract

Final Engineering drawings and CAD models delivered to AFRC for ground cart

48 hrs. after meeting

Modular ground cart final loads and stress report for delivered to

AFRC

9 months after award of contract

Test article and ground cart fabrication complete 14 months after award of contract

Pod and ground cart acceptance review 5 days before shipping

All required documents submitted for review 15 days before acceptance review

All required final documents transmitted At shipping

Test article and ground cart delivery to NASA AFRC 5 days after acceptance review

Second test pod delivery if option is activated 5 months after option is exercised

10. Place of Performance The contractor facility where work will be performed shall be located within the continental United States (CONUS).

11. Risk Reduction Prototype

11.1 The contractor may recommend fabrication of a prototype structural article or partial assembly to validate manufacturability prior to final production.

11.2 Any prototype activity shall be coordinated with and approved by the Subproject

Manager and Chief Engineer and may be used to evaluate tooling concepts, assembly approaches, and structural integration risks prior to full flight hardware fabrication.

Any additional costs associated with the risk reduction prototype require prior written approval from the Contracting Officer before they are incurred.

12. Configuration Management

12.1 The contractor shall maintain configuration control of all drawings, models, and fabrication documentation once finalized by NASA after CDR.

12.2 Any proposed design or manufacturing changes shall be reviewed and approved by the Subproject Chief Engineer and NASA engineering technical authority prior to implementation.

13. Export Control All work performed under this effort shall comply with applicable U.S. export control regulations including EAR/ITAR where applicable.

14. Reference Documents Documents to be provided upon award of contract.

1. SUU-60 centerline pylon removal and installation 1F-15C-2-94JG-32-21

2. External fuel tank removal and installation 1f-15c-2-05JG-00-15

3. STANDARD FOR THE DESIGN AND FABRICATION OF THE GROUND SUPPORT.

EQUIPMENT NASA-STD-5005D

Appendix A – Reference Geometry Diagram

Fig. 1 Conceptual Pod Image

Fig. 2 Inside View Conceptual Pod Image

Fig. 3 Conceptual Pod Drawing

Fig. 4 Ground Handling Keep out zones

Fig. 5 Ground Handling Cart Modular Needs

Appendix B – Critical Parts Definitions

Fig. 6 GEN-00611-011 Cone Rear Ring

Fig. 7 GEN-00613-001 Rear Forward Ring

Fig. 8 GEN-00612-007 & Mirror Part GEN-00612-003 Rear Forward Ring

Fig. 9 GEN-00612-015 & Mirror Part GEN-00612-007 Rear Forward Ring

Fig. 10 GEN-00612-009 Ring Front

Fig. 11 GEN-00612-011 Ring Rear

Fig. 12 GEN-00612-013 Ring Rear Middle

Fig. 13 GEN-00612-005 Ring Front Middle

Fig. 14 GEN-00612-033 Middle Backbone