Abstract
This paper studies the mechanism of combinational active thermal protection system (CA-TPS) of the hypersonic vehicles by numerical method. Unlike the traditional configuration, the nozzle is fixed on the spike, and the directions of lateral jet and hypersonic free stream are perpendicular to each other. The CA-TPS has significantly weaker reattachment shock wave than traditional spiked blunt body. Furthermore, the low temperature gas ejected from the nozzle flows downstream to reduce the aeroheating directly. For the blunt body, the peak and total heat fluxes of CA-TPS are 37.34% and 23.97% lower than that of traditional spiked blunt body, respectively. In addition, this paper conducts the analysis of influencing factors of the CA-TPS. As the total-pressure-ratio of nozzle and the length of spike increase, the reattachment shock wave intensity gradually weakens, and more low temperature gas can be ejected to increase the thermal protection efficiency of the CA-TPS. As the nozzle moves downstream, the reattachment shock wave intensity gradually increases, thus reducing the thermal protection efficiency. The effects of the above influencing factors on the flow field and change rate of thermal protection efficiency of CA-TPS are also studied in this paper.
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