摘要
The transition from blunt leading edges to sharp leading edges on re-entry aircrafts is necessary to increase both maneuverability and safety. However, the oxidation resistance of current materials is inadequate for the extreme conditions experienced by sharp leading edge re-entry vehicles. The Mo-Si-B alloy system has been utilized to design a multilayer coating that has the ability to protect from 800 to 1700 degrees C. Substrates of Mo and ZrB2-50 vol% SiC with a flat profile were coated with the MO-Si-B based coating and evaluated using arc jet testing performed at NASA Langley Research Center. Heat fluxes of 2.5 to nearly 3.5 MW/m(2) and surface temperatures of 1500-1650 degrees C were achieved during the 20-min tests. The samples presented in this study showed <3% mass loss and retention of sample shape and integrity, demonstrating the robust environmental protection under a simulated hypersonic environment offered by the Mo-Si-B based coating on refractory metals and ceramics.
- 出版日期2014-12