基于参数化气动弹性模型的Z形折叠翼离散突风响应  

Discrete gust response of Z-shaped folding wing based on a parameterized aeroelastic model

作　　者：祁武超[1] 吴诗淼 田素梅[1] 刘宏亮 QI Wuchao;WU Shimiao;TIAN Sumei;LIU Hongliang(Key Laboratory of Liaoning Province Aircraft Composite Structural Analysis and Simulation,Shenyang Aerospace University,Shenyang 110136,China)

机构地区：[1]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

出　　处：《沈阳航空航天大学学报》2024年第6期1-10,共10页Journal of Shenyang Aerospace University

基　　金：国家自然科学基金(项目编号:12002218);辽宁省教育厅项目(项目编号:JYTMS20230253,JYTMS20230224)。

摘　　要：折叠翼无人机可服役于多任务剖面,飞行环境复杂且易受低空突风的影响。开发一种新型的具有非侵入性特征的参数化气动弹性模型,用以快速计算在不同折叠角度下Z形折叠翼的离散突风响应特性。首先,对现有Z形折叠翼进行了结构和气动方面的增强设计。其次,基于舒展状态下颤振计算的Nastran输入文件,重构任意折叠角下的参数化气动弹性模型。最后,考察了折叠角、飞行速度、突风速度幅值、铰链阻尼等参数对折叠翼突风响应特性的影响。结果表明,增大折叠角可有效减缓突风响应,飞行速度和突风速度幅值的增大对翼尖加速度和翼根弯矩响应的贡献明显,铰链阻尼参数的存在会减缓翼尖加速度响应,但同时会增大翼根弯矩响应。The unmanned aerial vehicle with folding wing can serve in multiple mission profiles,the flight environment is complex and susceptible to low-altitude gusts.A new parameterized aeroelastic model with non-intrusive characteristics was developed to quickly calculate discrete gust response characteristics of Z-shaped folding wing at different folding angles.Firstly,structural and aerodynamic enhancement design was made to the existing Z-shaped folding wing.Secondly,based on the Nastran input file for the flutter calculation of the folded wing in the extended state,the parameterized aeroelastic model under any folding angle was reconstructed.Finally,the effects of parameters such as folding angle,flight speed,gust velocity amplitude and hinge damping between different wing segments on the gust response characteristics of the folding wing were examined.The results show that increasing folding angles can effectively alleviate the gust responses,the increase in flight speed and gust velocity amplitude significantly contributes to the responses of wing tip acceleration and wing root bending moment,the presence of hinge-damping parameters can alleviate the acceleration response of the wing tip,but it also increases the bending moment response of the wing root.

关 键 词：折叠翼 离散突风 非侵入性 参数化 气动弹性 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程]