Abstract In this paper, aeroelastic modeling of aircraft wings with variations in sweep angle, taper ratio, and variable pre-twist angle along the span is considered. The wing structure is modeled as a classical beam with torsion and bending flexibility. The governing equations are derived based on Hamilton’s principle. Moreover, Peters’ finite state aerodynamic model which is modified to take into account the effects of the wing finite-span, the wing sweep angle, and the wing pre-twist angle, is used to simulate the aerodynamic loads on the wing. The coupled partially differential equations are discretized to a set of ordinary differential equations using Galerkin’s approach. By solving these equations the aeroelastic instability conditions are derived. The results are compared with some experimental and analytical results of previous published papers and good agreement is attained. Effects of the wing sweep angle, taper ratio, bending to torsional rigidity, and pre-twist angle on the flutter boundary in several cases are studied. Results show that these geometrical and physical parameters have considerable effects on the wing flutter boundary.

中文翻译：

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后掠预扭曲机翼气动弹性分析

摘要 在本文中，考虑了沿翼展具有变化的后掠角、锥度比和可变预扭转角的飞机机翼气动弹性建模。机翼结构被建模为具有扭转和弯曲灵活性的经典梁。控制方程是根据哈密顿原理推导出来的。此外，考虑到机翼有限跨度、机翼后掠角和机翼预扭转角的影响而修改的 Peters 有限状态空气动力学模型用于模拟机翼上的气动载荷。使用伽辽金方法将耦合偏微分方程离散为一组常微分方程。通过求解这些方程，推导出气动弹性不稳定条件。结果与以前发表的论文的一些实验和分析结果进行了比较，并取得了良好的一致性。研究了几种情况下机翼后掠角、锥度比、弯曲扭转刚度和预扭转角对颤振边界的影响。结果表明，这些几何和物理参数对机翼颤振边界有相当大的影响。