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中文摘要：
基于热气动弹性的特点，采用松耦合方法建立气动弹性仿真模型。将该问题的求解分解成四步，即气动热的计算、结构的温度分布计算、热结构计算和气动弹性计算。研究了给定温度分布热效应下的气动弹性问题。运用非耦合热-结构分析方法，考虑热应力引起的附加刚度，得到热环境下的结构分析有限元分析模型，并计算了两种典型高超音速翼面的热结构。运用基于CFD技术的当地流活塞理论计算高超音速非定常气动力。在时间域内实现了高超音速热气动弹性的仿真。分析了温度和结构支持方式对热气动弹性系统的不同影响。
英文摘要：
Based on the characteristics of aerothermoelasticity, the loose coupling method is used to establish the aeroelastic model. The analysis consists of the following four steps： aerodynamic heating computation, structure＇s temperature distribution computation, thermal-vibration analysis and aeroelasticity analysis. The aeroelasticity involving thermal effect of the given temperature distribution is analyzed. With the uncoupled thermal-structure analysis method and the consideration of the additional stiffness caused by thermal stress, a finite element model for thermal-vibration analysis is obtained and two typical hypersonic wing structures are studied. Using local piston theory based on CFD to solve hypersonic unsteady aerodynamic loads, the hypersonic aerothermoelasticity is simulated in time domain. The influences of temperature and the structure＇s supporting conditions on aerothermoelastic systems are analyzed.
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