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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2021, Vol. 42 ›› Issue (2): 623989-623989.doi: 10.7527/S1000-6893.2020.23989

• Special Topic of Aerodynamic Design of Advanced Space Transportation Sytem • Previous Articles     Next Articles

Heat transfer limit characteristics of integrated dredging thermal protection structure

AI Bangcheng1,2, CHEN Siyuan1,2, HAN Haitao1,2, HU Longfei1,2, LU Qin1,2, CHU Min1,2, DENG Daiying1,2, YU Jijun1,2   

  1. 1. China Academy of Aerospace Aerodynamics, Beijing 100074, China;
    2. Laboratory of Aero-Thermal Protection Technology for Aerospace Vehicles, China Aerospace Science and Technology Corporation, Beijing 100048, China
  • Received:2020-03-17 Revised:2020-04-09 Published:2020-04-30

Abstract: Through phase change and transportation of internal working medium, the integrated dredging thermal protection structure can efficiently deliver heat from stagnation point to other larger areas, achieving non-ablative heat shielding for sharp leading edges of advanced vehicles. Nevertheless, the back-flow of the liquid medium relies on the capillary force in the capillary structure, which will be affected by overloading during the flight. A ground test was carried out and the overload characteristic of the integrated dredging thermal protection structure was obtained. The isothermal condition was significantly influenced by overload larger than 4g, and the thermal dredging performance recovered immediately after the overload decreased. The study is instructional for the estimation and design of integrated dredging thermal protection structures of leading edges.

Key words: dredging thermal protection structure, sharp leading edge, high temperature, heat pipe, overloading

CLC Number: