NNX17DA43P_Tab_4_SOW_V2.pdf

STATEMENT OF WORK

1. Objective/Requirements NASA requires testing of a proprietary composite wing under both static and combined bending / vibration loads. Mechanical strain measurements using Wavelength Division Multiplexing fiber Bragg Gratings (FBG) are requested along the entire wing length. Shape characterization will also be generated from this data.

2. Characteristics, Scope, and Specs

Optical fiber and FBG requirements:

• Silica fiber: SM 125 µm diameter, 9 µm core

• Fiber coating and recoat: Polyimide

• Fiber sensing length: 20 ft (6.1 m)

• Number of sensing arrays: 10 ea.

• Wavelength window / scan: 1460 nm to 1620 nm

• Number of FBG in array: 61

• FBG spacing (center to center): ≈ 4 inch (100 mm); spacing tolerance: 5 mm

• FBG reflectivity: > 50% (preferably towards 80%)

• FBG BW: 0.3 nm typical

• FBG length: 5 to 10 mm

• Lead in and lead out fiber length: ≥ 2 m (no connectors)

• FBG locations to be marked

• Proof test fiber after recoat

3. Place of Performance Testing to be conducted in Flights Loads Laboratory at NASA Armstrong Flight Research Center

4. Period of Performance Testing shall be performed during fall of 2017