三维前飞扑翼运动学参数优化  

Optimization of kinematic parameters of 3D forward flapping wing

作　　者：徐启炎 朱建阳 朱名康 谢鹏 XU Qiyan;ZHU Jianyang;ZHU Mingkang;XIE Peng(Key Laboratory of Metallurgical Equipment and Control Technology of Ministry of Education,Wuhan University of Science and Technology,Wuhan 430081,China;Institute of Robotics and Intelligent Systems,Wuhan University of Science and Technology,Wuhan 430081,China;Sino-German College of Intelligent Manufacturing,Shenzhen Technology University,Shenzhen Guangdong 518118,China)

机构地区：[1]武汉科技大学冶金装备及其控制省部共建教育部重点实验室,武汉430081 [2]武汉科技大学机器人与智能系统研究院,武汉430081 [3]深圳技术大学中德智能制造学院,广东深圳518118

出　　处：《航空动力学报》2024年第9期171-180,共10页Journal of Aerospace Power

基　　金：国家自然科学基金(51975429,51505347)。

摘　　要：采用田口试验和数值求解三维N-S方程相结合的方法,以提升扑翼的升举效率为目标,对缩减频率、扑动振幅和俯仰振幅这3个运动学参数进行优化。结果表明:与最差参数组合扑翼相比,最佳参数组合扑翼的时均升力系数提升了52.1%,升举效率提高了85.52%;运动学参数对扑翼气动性能影响的强弱依次为缩减频率,扑动振幅和俯仰振幅。进一步通过对扑翼表面的流场分析发现,采用最佳参数可以增强贴附在扑翼表面上涡流的强度,以及促进扑翼尾迹反卡门涡街的形成,从而使扑翼具有更好的气动特性。In order to improve the lifting efficiency of the flapping wing,the influences of three kinematic parameters,such as reduced frequency,flapping amplitude and pitching amplitude,on the aerodynamic performance of flapping wing were analyzed by the combination of the Taguchi test and numerical solution of three-dimensional N-S equation.The results showed that compared with the worst parameters combination,the average lifting coefficient and lifting efficiency of the flapping wing with best parameters combination increased by 52.1%and 85.52%,respectively.The influences on the aerodynamic performance of flapping wing referred to reduced frequency,flutter amplitude and pitch amplitude in turn.Further,through analysis of the flow field on the flapping wing surface,it was found that the best parameters combination can enhance the intensity of the vortex attached to the flapping wing surface and promote the formation of von Karman vortex street in the wake of the flapping wing,so as to make the flapping wing have better aerodynamic characteristic.

关 键 词：扑翼 运动学参数 田口方法 Navier-Stokes(N-S)方程 升举效率 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]