空间再入飞行器热气动弹性数值研究进展  

A Review of Aerothermoelastic Numerical Research on Space Reentry Vehicles

作　　者：张章[1] 黄伟[1] 唐明章[1] 王伟志[1] 

机构地区：[1]北京空间机电研究所,北京100094

出　　处：《航天返回与遥感》2016年第1期10-21,共12页Spacecraft Recovery & Remote Sensing

基　　金：载人航天预研项目

摘　　要：热气动弹性分析关系到空间再入飞行器的气动性能、结构安全和振动特性。文章对空间再入飞行器热气动弹性研究的数值方法和研究进展进行了回顾;总结了热气动弹性数值的模拟内容、气/固/热多物理场耦合方法和高超声速气动力、气动热求解方法等方面研究的典型成果与特点;比较了单向耦合分层求解方法与双向耦合方法在热气动弹性分析方面的优缺点,指出气动力、气动热的工程计算方法和降阶方法存在一定误差,采用时域方法求解Navier-Stokes方程的全阶模型获取气动力和气动热更为准确;并对未来的研究趋势进行了展望,提出了需要进一步深入探讨的若干问题,包括空间再入过程气/热/固多场耦合物理机制的准确描述、空间充气式再入减速器这类柔性结构的热气动弹性分析以及热气动弹性试验验证等三个方面。Aerothermoelastic research is a major concern for aerodynamic performance, structure safty and vibration characteristics of a space reentry vehicle. A review of numerical research on space reentry vehicle aerothermoelasticity is presented in this paper, including typical investigation on aero-thermo-structure coupl- ing and computation method of unsteady aerodynamics and aerothermodynamics in hypersonic flow. Further- more, a comparison between one-way coupling and two-way coupling method is conducted in this paper, which points out that both engineering simplified calculation method and order-reduced method have some error in aerodynamic and aerothermodynamic calculation, while a computational fluid dynamic model to solve Navi- er-Stokes equation in time domain is more accurate in aerodynamic and aerothermodynamic numerical simula- tion. Finally, several possible aerothermoelastic research trends are also discussed. Aero-thermo-structure coupling mechanism, and flexible structure aerothermoelasticity analysis such as inflatable space reentry aero- shell are valuable in further study. And more attention should be paid to hypersonic experimental research to validate accuracy of numerical aerothermoelastic analysis.

关 键 词：空间再入 热气动弹性 数值研究 气/固/热耦合 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]