Combined High Temperature Aerothermal-Structural Physical Property Testing of Ceramic Matrix Composites; Final performance rept. 29 Mar 2004-31 Dec 2007

摘要

The objective was to integrate a mechanical test apparatus into a wind tunnel flow field capable of generating controlled multi-directional stress/strain states in flat coupons exposed to appropriate chemical, thermal, and aerodynamic shear flow environments. Displacement control enables imposition of stress/strain fields (in the flat coupons) similar to those expected in complex flight component geometries. Control and measurement of these variables and the material response in a controlled environment enables assessment of material performance for hypersonic missile and re-entry vehicle flight trajectories. Requirements for the test apparatus were developed and the apparatus was designed. Unfortunately, closure of the proposed wind tunnel facility led to increased costs and imposed a major schedule slip. The program's contract was not extended and the test apparatus was not assembled.