Jian-Jun Gou , Jia-Xin Hu  , Chun-Lin Gong , Bing Chen  , Liang-Xian Gu

DOI Number XXX-YYY-ZZZ

Conference Number HiSST 2018_370870

At present, the TPS of flight vehicles is designed based on the radiation equilibrium condition. The approach is conservative and is unable to consider the influence of active cooling. In this paper, a TPS design method coupling active cooling of kerosene is developed. Such a method includes the calculation of aerodynamic heat, the design of passive TPS, and the determination of design parameters of active cooling system. A reusable launch vehicle and its typical trajectory is studied. The results show that 33% weight of passive TPS can be reduced by active cooling, and the required product of mass flowrate per area and coolant temperature increase are between 2.1 and 4.9 (K·kg·m-2·s -1 ).

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In Categories: High-Speed Missions and Vehicles, HiSST 2018, Hypersonic Aerodynamics, Space Launch Vehicles, Thermal and Energy Management Systems
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