The innovation proposed herein concerns the analysis and formulation of a test procedure for the development of an optical communications window for hypervelocity vehicles. A test facility is identified and instrumentation requirements delineated for tests to be carried out during Phase II for three different window designs. The technical approach concerns definition of window shape and candidate locations on the aircraft considering forward, side, upward, and downward look angles. Optimal locations for each predominant look-angle direction. will be determined by consideration of the shock layer flow-field aerothermal environment calculated using state-of-the-art CFD (Computational Fluid Dynamic) computer codes. Then, based on the selected locations and predicted aerodynamic heating rates at those locations, candidate window-cooling systems, where deemed necessary, will be designed, their performance assessed, and detailed local window environments determined including effects of the window-cooling system where required. In addition, based on the selection of a proven test facility that accurately simulates hypervelocity shock-layer environments, a preliminary test-model design will be developed, and test conditions, preliminary test matrices, and instrumentation requirements will be delineated. Moreover, predictions of candidate window optical performance and shock-layer aero-optical effects will be carried out using first-principle computational algorithms.
Keywords: Hypervelocity Vehicles Hypersonic Flow Optical Windows Hypervelocity Testing Optical Sensors Computers
