Effects of rotational motion on dynamic aeroelasticity of flexible spinning missile with large slenderness ratio
Effects of rotational motion on dynamic aeroelasticity of flexible spinning missile with large slenderness ratio
复制标题
旋转运动对大长细比柔性自旋导弹动态气动弹性的影响
DOI：
10.1016/j.ast.2019.105384
复制
发表时间：
2019-11
影响因子：
5.6
通讯作者：
Zhengyin Ye
中科院分区：
文献类型：
--
作者：
Heng Li;Zhengyin Ye
大长径比旋转导弹的结构刚度一般较小，结构变形和变形速率不可忽略。此外，旋转运动使气动弹性更加复杂。为此，采用刚体运动网格和径向基函数（Radial-basis-function，RBF）变形网格技术，将非定常欧拉方程和广义动气动弹性方程耦合起来，对大长径比自旋导弹的动气动弹性响应进行了数值模拟。非定常欧拉方程的求解采用计算流体动力学（CFD）技术的内部代码。在广义动气动弹性方程中同时考虑了旋转运动引起的科里奥利项和离心载荷项。刚体运动网格和径向基变形网格技术都是基于非结构网格的，刚体运动网格用于处理旋转运动引起的刚体运动，径向基变形网格用于处理气动弹性引起的柔性结构变形。气动弹性算例的数值计算结果与实验结果吻合较好，验证了数值方法的有效性。建立了X-X构型导弹模型，研究了旋转运动对导弹动气动弹性的影响。分别计算了导弹有无旋转运动时的动气动弹性响应。比较结果表明，横向模式和纵向模式耦合在一起，因为旋转运动。此外，由于旋转运动，结构的固有频率发生变化。最后，对本文所采用的广义动气动弹性方程进行了详细的数值分析，揭示了旋转运动引起横、纵振型耦合并改变结构固有频率的机理。
The structural rigidity of a spinning missile with large slenderness ratio is usually small, and the structural deformation and rate should not be ignored. Furthermore, rotational motion makes the aeroelasticity more complicated. Therefore, unsteady Euler equations and generalized dynamic aeroelastic equations are coupled simultaneously to simulate the dynamic aeroelastic response of a spinning missile with large slenderness ratio using rigid-motion mesh and radial-basis-function (RBF) morphing mesh techniques. The unsteady Euler equations are solved by computational fluid dynamics (CFD) technique by the in-house code. The Coriolis term and centrifugal loading term due to rotational motion are both considered in the generalized dynamic aeroelastic equations. The rigid-motion mesh and RBF morphing mesh techniques are both based on unstructured mesh, and the rigid-motion mesh is adopted to treat the rigid motion due to rotational motion, while the RBF morphing mesh is employed for flexible structural deformation caused by aeroelasticity. Numerical results of aeroelastic case are well agreed with the experimental results, which validates the numerical method. A missile model with X-X configuration is constructed to investigate the effects of rotational motion on dynamic aeroelasticity. The dynamic aeroelastic responses of the missile with and without rotational motion are simulated, respectively. Comparison results show that the lateral modes and longitudinal modes are coupled together because of rotational motion. In addition, the structural natural frequencies are changed due to rotational motion. In the end, detailed numerical analysis of the generalized dynamic aeroelastic equations used in this paper indicates the mechanism by which the rotational motion leads to the coupling of lateral modes and longitudinal modes and changes the structural natural frequencies.
登录
查看更多内容
影响因子：
7.3
作者：
Tian-fu Xu;J. Rong;D. Xiang;Chenglong Pan;Xinzhe Yin
通讯作者：
Tian-fu Xu;J. Rong;D. Xiang;Chenglong Pan;Xinzhe Yin
DOI：
10.1080/19942060.2007.11015197
发表时间：
2007-01
影响因子：
6.1
作者：
Weiwei Zhang;Yuewen Jiang;Zhengyin Ye
通讯作者：
Weiwei Zhang;Yuewen Jiang;Zhengyin Ye
影响因子：
2.9
作者：
T. Rendall;C. Allen
通讯作者：
T. Rendall;C. Allen
影响因子：
5.6
作者：
Ruhao Hua;Zhengyin Ye;Jie Wu
通讯作者：
Ruhao Hua;Zhengyin Ye;Jie Wu
影响因子：
2.2
作者：
Changchuan Xie;Yang Lan;Liu Yi;Yang Chao
通讯作者：
Changchuan Xie;Yang Lan;Liu Yi;Yang Chao