Abstract:Thermal protection structures (TPS) are the key component in the design and manufacture of the reusable launch vehicle. The probability of failure of TPS in an aerodynamic thermal environment during reentry is much higher than that of ordinary structures. There is an urgent need to develop a structural health monitoring (SHM) method that can achieve rapid diagnostic for TPS to realize the high reliability and maintainability of the reusable launch vehicle. Hence, this paper aims at the typical TPS made of C/C … Show more
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