To solve the problem of heat barrier which a hypersonic vehicle would encounter during its mission,the idea that thermal protection system design should be integrated with thermal control system design was described. It was concluded that the airframe structure design should be coupled with design of thermal protection system, thermal control system and propulsion system. It was regarded as an effective solution to heat barrier problem. Considerations of thermal protection and control concepts for hypersonic vehicles which had different missions were put forward. Properties of some thermal protection materials were introduced and principles to select thermal protection materials in a design were addressed. Optimization of integrated thermal protection and thermal control system was discussed. Key technologies concerning the integrated design methodology were put forward. An example was put forth to illustrate the essential approach of the integrated design methodology.
Xia Gang, Liu Xinjian, Cheng Wenke, et al. Numerical simulation of coupled aeroheating and solid heat penetration for a hypersonic blunt body[J]. Journal of National University of Defense Technology, 2005, 25(1):35-39(in Chinese)