An Intrinsic Description of the Nonlinear Aeroelasticity of Very Flexible Wings
An Intrinsic Description of the Nonlinear Aeroelasticity of Very Flexible Wings
复制标题
高柔性机翼非线性气动弹性的本质描述
DOI：
10.2514/6.2011-1917
复制
发表时间：
2011
影响因子：
4.7
通讯作者：
B. Epureanu
中科院分区：
文献类型：
--
作者：
R. Palacios;B. Epureanu
本文给出了以惯性速度和惯性应变为主要变量的内禀形式的柔性机翼气动弹性方程的模态解。在假定机翼截面为2-D薄翼型空气动力学后，证明了运动方程可以写成固有模态坐标上的规范状态空间形式，而不需要任何矩阵求逆，只包括二次非线性。颤振特性很容易从动力学方程的线性化描述中获得，并且该方法提供了计算大机翼位移的非线性响应的有效方法。这两种情况都以Golang机翼为例进行了艾德数值计算。在具有几何非线性的气动弹性问题中，模态坐标的使用将突出固有梁解的某些特殊特性。
A modal solution is presented to the aeroelastic equations of very exible wings in intrinsic form, that is written using inertial velocities and strains as primary variables. After assuming 2-D thin-airfoil aerodynamics on the wing sections, it is shown that the equations of motion can be written in canonical state-space form on the intrinsic modal coordinates without any matrix inversion and including only quadratic nonlinearities. Flutter characteristics are readily obtained from a linearized description of the dynamics equations, and the approach provides an e cient way of computing the nonlinear response with large wing displacements. Both situations are exempli ed numerically on the Golang wing. The use of modal coordinates will serve to highlight some of the particular characteristics of the use of intrinsic beam solutions in aeroelastic problems with geometrical nonlinearities.