ATA ENGINEERING, INC. — Department of Defense STTR Phase I: AF17A-T025

Description

The aerothermal environment for hypersonic flight vehicles is severe and can generate extremely high material temperatures. These high-temperature environments can cause intense localized heating, which may result in local pockets and/or structural instabilities, especially at vehicle leading-edge regions, and may lead to disruptions that affect vehicle performance. The aerothermal environment may also amplify the damage induced by laser irradiation. At high enough velocities, these pockets may affect either the structural integrity or trajectory or both, which can lead to disastrous consequences or even mission failure. ATA Engineering, Inc., proposes an innovative approach for predicting the effects of structural profile disruptions on high-speed vehicles that leverages 1) an existing validated multiphysics framework that enables more complete simulation of the aeroheating environment, and 2) existing detailed progressive failure damage models for advanced composite materials. The proposed effort will robustly couple the multiphysics framework with novel progressive, nonlinear damage material models that ATA has developed for carbon-carbon and ceramic matrix composite materials. Preliminary aerothermal material testing will be conducted to ensure a successful test campaign in Phase II to further validate the toolset and material models.