摘要
使用分层求解技术进行了高超声速舵面的颤振分析。基于Volterra级数降阶模型构造非定常气动力状态空间模型;应用载荷参数空间插值传递方法实现气动网格和结构网格之间的数据传递;应用非耦合热-结构方法得到热结构有限元模型;结合非定常气动力模型构造气动弹性分析模型。最后应用该气动弹性模型,针对一个根部固支的高超声速舵面进行了颤振分析。计算结果表明受高超声速气动热载荷影响,根部固支舵面的一阶弯曲和扭转频率变化较大,从而导致临界颤振速度下降较多。
A hierachical solution process is used to analyze the flutter of a fin in hypersonic flow. A reduced-order model based on Volterra series is employed to establish an unsteady aerodynamic state space model A load interpolation transfer method in parametric space is used to transfer data between aerodynamic meshes and structural meshes. A finite model for thermal-vibration analysis is obtained with the uncoupled thermal-structure analysis method. Combining the unsteady aerodynamic model with the structural finite model, an aeroelastic model is established. At last, this aeroelastic model is applied to predict the flutter of a fin with root fixed in hypersonic flow. The results show that, taking the aerodynamic heating into account, the critical flutter speed decreases sharply due to the declination of the first bend and torsion frequencies.
出处
《工程力学》
EI
CSCD
北大核心
2009年第11期232-237,共6页
Engineering Mechanics
基金
总装十一五国防科学技术预先研究项目(513130303)
博士点基金国防基础预研项目(20070699054)
关键词
气动弹性
降阶模型
载荷传递
热气动弹性
高超声速
颤振
aeroelastiticy
reduced-order model
load transfer
aerothermoelasticity
hypersonic
flutter
