Affiliation:
1. Harbin Engineering University
Abstract
Based on the theory and semi-empirical formulas, the surface heating flux of hypersonic flying vehicle under aerodynamic heating is calculated by using reference enthalpy method. On this basis, the thermal response of structure made of ultrahigh temperature ceramics(UHTCs) is simulated by using finite-element method. The results show that thermal stress shock is able to cause material to damage in a very short time
Publisher
Trans Tech Publications, Ltd.
Reference8 articles.
1. Hongqing Lv, Zhenqing Wang, Yongjun Wang, Cuie Zhang, Chengbin Jin, Aero-heating Analysis for Hypersonic Blunt Head Body. Journal of Dao Dan Yu Hang Tian Yun Zai Ji Shu Vol. 3(2008), pp.41-45.
2. Lv Hongqing, Wang Zhenqing, Jin Chengbin, Zhang Cuie, Wang Yongjun. Numerical Simulation for Aerodynamic Heating and Opposing Jet Thermal Protection. The 2nd International Symposium on Systems and Control in Aeronautics and Astronautics, (2008).
3. Fan Xiaoqiang, Li Hua and Ding Meng. Predicted Heating Distributions for Blunt Biconic at An Angle of Attack. ACTA ARMAMENTARII Vol. 23(1) (2002), pp.142-144.
4. Lv Lili, Zhang Weiwei and Ye Zhengmao. Numerical Study of Aeroheating Pedictions for Hypersonic Reentry Bodies. Chinese Journal of Applied Mechanics Vol. 23(2) (2006), pp.259-262.
5. Fay J A, Riddell F R. Theory of Stagnation Point Heat Transfer in Dissociated Air. Journal of the Aeronautical Science Vol25(2), (1958), pp.73-85.