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Discrete gust responses of a multi-segment folding wing based on a bending-torsional beam element

DOI：10.7511/jslx20220424006

 作者 单位 E-mail 祁武超 沈阳航空航天大学 辽宁省飞行器复合材料结构分析与仿真重点实验室, 沈阳 110136 qiwuchao@sau.edu.cn 赵传旭 沈阳航空航天大学 辽宁省飞行器复合材料结构分析与仿真重点实验室, 沈阳 110136 王猛 沈阳航空航天大学 辽宁省飞行器复合材料结构分析与仿真重点实验室, 沈阳 110136 田素梅 沈阳航空航天大学 辽宁省飞行器复合材料结构分析与仿真重点实验室, 沈阳 110136 赵维涛 沈阳航空航天大学 辽宁省飞行器复合材料结构分析与仿真重点实验室, 沈阳 110136

基于弯扭组合梁元对大展弦比多段折叠翼的离散突风响应特性进行了研究。首先,将平面一般梁元叠加扭转自由度得到一种新的弯扭组合梁元,建立包含折叠角参数的缩减有限元模型。其次,对片条理论进行修正以得到不同折叠角度下弯扭组合梁元上的气动力,构建多段折叠翼在离散突风作用下的动力学方程。最后,引入Laplace变换处理动力学方程中的积分微分项,得到折叠角对翼尖加速度、翼根弯/扭矩等响应的影响。一个近地面无人机三段式折叠翼的算例结果表明,机翼固有频率会随着折叠角的变化呈现非线性性态,相比舒展状态,折叠角的存在虽不能明显减小翼尖加速度,但能够有效减小翼根弯/扭矩响应。

Discrete gust responses of a high-aspect-ratio multi-segment folding wing are studied based on a bending-torsional beam element model.First,a new bending-torsional beam element is obtained by superimposing the plane general beam element with torsional degree of freedom.Then a reduced finite element model including folding angle parameters is established.Secondly,the aerodynamic forces on the bending-torsional beam elements under different folding angles are obtained by the modified strip theory.Thus the dynamic equations of the multi-segment folding wing under a discrete gust are constructed.Finally,Laplace Transform is introduced to deal with the integral-differential terms in the dynamic equations.Then the effects of folding angles on accelerations of the wingtip and bending moments/torques at the wing root are investigated.Numerical results of a three-segment folding wing of a near-ground UAV show that the natural frequencies of the wing show nonlinear behaviors with the change of folding angles.Compared with the extended state,the existence of folding angles can’t significantly reduce the accelerations of the wingtip,but can effectively reduce the bending moments/torques at the wing root.