高超声速热气动弹性中结构热边界影响研究  

Effect of Structural Thermal Boundary on Areothermoelasticity for Hypersonic Vehicles

作　　者：叶坤[1] 叶正寅[1] 屈展[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《西北工业大学学报》2016年第1期1-10,共10页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(91216202)资助

摘　　要：基于分层求解思路研究结构热边界对高超声速飞行器全动舵面和翼面结构热气动弹性特性的影响。首先,基于CFD求解N-S方程得到热环境,在此基础上进行结构的瞬态热传导分析,进而分析结构由于温度梯度产生的热应力和温度对材料属性的影响下的模态固有特性,然后将结构振型插值到气动网格上,最后,通过求解Euler方程得到流动参数,基于CFD的当地流活塞理论计算气动力,在状态空间中进行了气动弹性分析。通过对4组结构模型进行热气动弹性分析,研究了结构热边界对舵面和翼面热气动弹性的影响,结果表明:对全动舵面而言,结构热边界首先会影响舵轴处结构的热传导过程及温度分布,进而对结构固有频率、频率间距、颤振速度以及颤振频率的变化产生的影响达到了16%。对翼面而言,结构热边界对结构固有频率、频率间距、颤振速度以及颤振频率的变化产生的影响约为1%。因此,工程实际当中,进行热气动弹性分析时应采用合理的结构热边界。The effect of structural thermal boundary on aerothermoelasticity of hypersonic all-movable control sur- face/wing is studied on the basis of hierarchical solution process. On the basis of CFD technology, Navier-Stokes equation is solved to get the thermal environment. And then transient thermal conduction of structure is analyzed. Then structural modal is analyzed under the effect of structure is thermal stress caused by temperature gradient and material property decrease caused by high temperature, then structural mode is interpolated to the aerodynamic grid; Finally, Euler equation is solved to get flow parameter, and based on CFD local piston theory, aerother- moelasticity is analyzed in state space. Through analyzing aerothermoelasticity of four different structural models, the effect of the structural thermal boundary on aerothermoelasticity of all-movable control surface/wing is analyzed.The results show that： for the control surface in this paper, the structural thermal boundary would firstly affect the heat transfer process and temperature distribution of shaft structure. The effect on the variation of the natural fre- quency, frequency spacing, flutter velocity and flutter frequency is about 16%. For the wing in this paper, The effect on the variation of the natural frequency, frequency spacing, flutter velocity and flutter frequency is about 1%. Therefore, in practical engineering, reasonable thermal boundary should be used while analyzing aerothermoelasticity.

关 键 词：高超声速 热气动弹性 结构热边界 气动加热 当地流活塞理论 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]