高超声速翼面气动热与静气动弹性综合分析

李国曙; 万志强; 杨超

高超声速翼面气动热与静气动弹性综合分析

北京航空航天大学航空科学与工程学院, 北京 100191

基金项目: 国家自然科学基金资助项目(90716006, 10902006)

详细信息

作者简介:
李国曙(1983-),男,山西运城人,博士生, liguoshu1983@163.com.

中图分类号: V 211.47
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- 被引次数: 0
出版历程
- 收稿日期: 2010-11-19
- 网络出版日期: 2012-01-30

Integrated analysis of aerothermal-aeroelastic wings in hypersonic flow

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 研究了考虑热效应影响的高超声速飞行器的静气动弹性问题.建立了考虑热效应影响的高超声速飞行器从气动热计算到静气动弹性分析的快速分析方法,该方法采用分层求解思路对热气动弹性问题进行解耦,利用边界层外的无粘数值求解和边界层内的工程算法相结合的方法,计算高超声速飞行器的表面热流,获得模型的温度场,并基于该温度场计算结构热刚度矩阵.以高超声速飞行器小展弦比翼面为研究对象,计算了该模型在3种飞行状态下的温度场、热应力、热刚度和静气动弹性特性,从而验证了热静气动弹性快速分析方法的可行性和适用性.
- 高超声速 /
- 静气动弹性 /
- 分层求解 /
- 热效应 /
- 温度场
Abstract: To research the static aeroelastic problems of the hypersonic vehicles in which the thermal effects must be considered, the rapid analysis of the hypersonic vehicles from aerodynamic heating to static aeroelasticity was developed. A hierarchical solution process was used to dealing with the aerothermal-aeroelastic coupling problems. The whole flow field was divided into inviscid flow field out of the boundary layer and viscous field inside the boundary layer, and the method simulating the inviscid flow field numerically and predicting the viscous field experientially was used to compute the hypersonic aerodynamic heating and the temperature field. The stress stiffness matrix under this temperature field was developed. A hypersonic low aspect-ratio wing was researched, and the temperature field, thermal stress, thermal stiffness and static aeroelastic characteristic of the wing was computed. Therefore, the feasibility and applicability of this aerothermoelastic rapid analysis is demonstrated.
- hypersonic /
- static aeroelasticity /
- hierarchical solution /
- thermal effects /
- temperature field

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参考文献(1)

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