Aerothermoelastic response analysis for C/SiC panel of ceramic matrix composite shingle thermal protection system

作者：Huo, Lin; Cheng, Xing Hua; Yang, Tao^*

来源：Advances in Space Research, 2015, 55(9): 2352-2371.

DOI：10.1016/j.asr.2015.02.008

• Aerothermoelastic response
• C/SiC panel
• Hypersonic
• Self-adapting aerodynamic heating time step
• Glide trajectory

This paper presents a study of aerothermoelastic response of a C/SiC panel, which is a primary structure for ceramic matrix composite shingle thermal protection system for hypersonic vehicles. It is based on a three dimensional thermal protection shingle panel on a quasi-waverider vehicle model. Firstly, the Thin Shock Layer and piston theory are adopted to compute the aerodynamic pressure of rigid body and deformable body, and a series of engineering methods are used to compute the aerodynamic heating. Then an aerothermoelastic loosely-coupled time marching strategy and self-adapting aerodynamic heating time step are developed to analyze the aerotheimoelastic response of the panel, with an aerodynamic heating and temperature field coupling parameter selection method being adopted to increase the efficiency. Finally, a few revealing conclusions are reached by analyzing how coupling at different degrees influences the quasi-static aerothermoelastic response of the panel and how aerodynamic pressure of rigid body time step influences the quasi-static aerothermoelastic response on a glide trajectory.

• 出版日期2015-5-1
• 单位中国人民解放军国防科学技术大学