SATPC0037536 Tab 04 4 SOW .pdf

Statement of Work (SOW) for Turtleskin T9-816 Coating w Resin

Project Title: Development and Optimization of Vectran Turtleskin Style T9-816 Fabric Coated with HRL Series 8 Low-Temp Resin

Background: The overarching goal of the NASA’s Artemis Suit Material Project conducted by the Crew and Thermal System Division Advanced Suit Team, is to develop enabling technologies and potentially a turnkey solution for suit vendors for the outer shell fabric of a lunar suit environmental protection garment (EPG). The project asserts that no existing fabric currently meets all requirements necessitating the construction of a bespoke solution designed to withstand the harsh conditions of the lunar environment.

The T-9 816A Turtleskin™ fabric, produced by Warwick Mills, has been identified by NASA as a commercially available material with several desirable characteristics for advanced applications.

One of its standout features is its exceptionally tight weave, which provides excellent performance as a dust blocker, a critical requirement for environments like the lunar surface where fine, abrasive regolith poses significant challenges. In addition to its dust-blocking properties, T-9 816A Turtleskin demonstrates strong durability, making it suitable for protective applications where wear resistance is essential. However, it is lacking several critical properties which Warwick asserts can be addressed by an advanced coating system developed in conjunction with Boeing’s HRL laboratory.

Objective:

The Vendor will collaborate with NASA to develop an advanced coated fabric system, based on the Vectran Turtleskin Style T9-816, to meet the requirements of the Advanced Suit Materials project. The fabric will be coated with the HRL-developed Series 8 low-temperature resin, applied to the fabric’s face side, to enhance performance in cryogenic conditions. This SOW builds upon previous work in which Warwick applied neat resin coatings, with and without primer, and doped the resin with Titanium Dioxide (TiO₂) to improve optical properties, as validated through testing performed by NASA.

Several key fabric requirements have been identified for the outer shell layer, including optical properties, cut and tear resistance, ESD (electrostatic discharge) properties, and flame resistance. Specific numerical targets for these properties have been outlined below for reference throughout this effort. However, a requirement for stiffness has not yet been established, despite its critical importance in designing the final fabric. Stiffness will influence the fabric's usability, durability, and performance, particularly in extreme environments. As part of this SOW, work will focus on characterizing the stiffness of a coated fabric system under both ambient and cryogenic conditions to provide data for defining this requirement. The vendor's experience in designing protective garments for abrasive environments offers valuable insight into the appropriate "hand feel" for the outer shell layer. This expertise will support the NASA team in developing a stiffness requirement that ensures functionality, comfort, and protection for the fabric’s intended application.

Period of Performance: 6 months after ATP. (e.g. January 15-July 15, 2025) The work will proceed over a defined schedule to ensure iterative feedback and final sample delivery within the required timeframe. Sample deliveries and iterations will align with NASA’s testing schedule to ensure timely feedback on each enhancement area.

Travel: No travel expenses are required/included in this TO.

Scope of Work:

The following definitions differentiate between requirements and other statements.

Shall: This is the only verb used for the binding requirements, which must be implemented and verified.

Should/May: These verbs are used for stating goals, which must be addressed by the design, but not formally verified.

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

Rationale is provided for most of the requirements. It is important to note that rationale is not binding and is only used to provide additional information or examples in order to the clarify intent of the requirement. In the event of an inconsistency between the requirement and the rationale, the requirement is binding and takes precedence.

1. Optical Properties Enhancement A. Vendor shall:

1. Optimize TiO₂ pigment concentration and application to the fabric.

2. Perform circular bend analysis of neat and coated specimens at ambient and cryo conditions.

3. Supply coated samples to NASA for solar absorptivity and emissivity testing. See “Deliverables” section.

4. Iterate if necessary to improve optics or hand feel

B. Vendor should:

1. Characterize the break-in of the fabric at both temperatures.

2. Investigate replacing TiO2 with ZnO2 and report on feasibility.

Rationale: To meet NASA’s specifications for solar absorptivity and emissivity.

Absorptivity (ASTM E1598): Threshold <0.3; Goal <0.2 Emissivity (ASTM E408): Threshold 0.8; Goal 0.9

2. Cut Resistance Enhancement A. Vendor shall:

1. Incorporate and optimize filler particles (e.g. ceramic) into the resin and application to the fabric.

2. Perform circular bend analysis of particle filled coated specimens at ambient and cryo conditions.

3. Supply coated samples to NASA for testing using modified ASTM F2992- 23 Cut Test. See “Deliverables” section.

4. Iterate if necessary to improve cut resistance or hand feel.

B. Vendor should:

1. Characterize the break-in of the fabric at both temperatures.

2. Make recommendations of any other filler particles that should be evaluated to meet fabric cut resistance properties.

Rationale: To meet NASA’s specifications for cut resistance. ASTM F2992-23 will be followed.

Threshold: 750 gf (A2); Goal: 1850 gf (A4)

3. Tear Resistance Enhancement A. Vendor shall:

1. Apply a 1500d mesh layer to the face side of the fabric (e.g. By using a wet-marry process, followed by an overcoat of HRL resin).

2. Perform circular bend analysis of specimens with mesh at ambient and cryo conditions.

3. Supply coated samples to NASA for testing using ASTM D2261 Tear Test.

See “Deliverables” section.

4. Iterate if necessary to improve tear resistance or hand feel.

B. Vendor should:

1. Characterize the break-in of the fabric at both temperatures.

2. Make recommendations of any other fibers or construction that should be evaluated to meet fabric tear requirements.

Rationale: To meet NASA’s specifications for tear resistance. ASTM D2261 will be followed.

Threshold: 70 lbf; Goal: 100 lbf

4. Electrostatic Discharge (ESD) and Flame Resistance Enhancement A. NASA will conduct electrostatic and flame resistance testing on the provided samples from 3.A.3.

B. Vendor shall:

1. Based on NASA’s results, improve static dissipative properties (e.g. add silver plating to the mesh)

2. Based on NASA’s results, improve flame resistance using filler materials (e.g. ceramic) or additional F/R coatings

3. Supply coated samples to NASA for second round testing of electrostatic and flame resistance. See “Deliverables” section.

4. Iterate if necessary to improve ESD/flamm resistance or hand feel.

C. Vendor should:

1. Characterize the break-in of the fabric at both temperatures.

2. Make recommendations of any other fibers or construction that should be evaluated to meet fabric ESD and flammability requirements.

Rationale: To meet NASA’s specifications for surface/volume resistivity. ANSI/ESD S11.11-11.12 will be followed.

Threshold: Surf=104-11 W / Vol=105-12 W-cm Goal: Surf=106-9 W / Vol=107-10 W-cm

To meet NASA’s specifications for flame resistance. ASTM D6413 @37% O2 and

8.2 psia will be followed.

Threshold: pass the test (i.e. ≤2 sec after flame time, ≤6” char length, no melt/drip)

Deliverables:

1. Sample Production and Final Product Delivery A. Interim specimens

1. Produced during Period of Performance as part of 1, 2, 3 and 4 sections of the SOW

2. Vendor shall produce sufficient qty to complete required testing. Qty to be determined by mutual agreement between NASA and Vendor during the Period of Performance.

B. Final Deliverables

1. Vendor shall produce and deliver 20 full-up samples of 18" x 12" coated fabric sheets to NASA for final testing and verification.

2. Meetings: Vendor shall hold the following meetings:

A. Kick-off. To be held within 1 week of ATP.

B. Weekly status updates. To be held weekly during the Period of Performance.

C. Pre-fabrication review for final product approval. To be held 1 week prior to the start of manufacture of the final deliverables.

3. Final Report

A. Shall include design and manufacturing processes followed, excepting those claimed by Vendor prior to ATP to be intellectual property.

B. Shall include results of testing.

C. Shall include itemized list of elements and quantities utilized in final deliverables.

D. Should include insight into fabric stiffness and break in.

E. Should include lessons learned and recommendation of future work.