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| Discrete gust responses of a multi-segment folding wing based on a bending-torsional beam element |
| Received:April 24, 2022 Revised:September 01, 2022 |
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| DOI：10.7511/jslx20220424006 |
| KeyWord:bending-torsional beam element multi-segment folding wing discrete gust the strip theory |
| Author | Institution |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
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| Abstract: |
| 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. |