仿生扑翼模态分析研究与优化设计

Modal Analysis and Optimization on Flapping-wing

微型扑翼飞行器是微型飞行器和扑翼飞行器的结合,是飞行器设计领域的研究热点,但在低雷诺数下存在升力不足的现象。已有研究表明,扑翼的弯扭耦合对于提高升力有效,弯扭耦合可通过共振激励放大驱动机理来实现,但该机理对扑翼的模态提出要求。本文首先建立仿生扑翼有限元模型,对其进行模态分析,并提出1种适用于扑翼的模态种类判别方法。为满足模态要求,提出了2种改进方案,并进行了有限元仿真验证。结合两种改进方案,提出双斜梁-主梁变截面扑翼模型。基于PCL语言对该模型进行参数化建模,采用遗传算法对其进行尺寸优化,得到满足模态要求的相对理想的仿生扑翼,为仿生扑翼的设计和优化提供重要的科学依据和工程应用价值。

Flapping-wing Micro Air Vehicle is a combination of flapping and micro air vehicle, and has become a hotspot in the field of flight vehicle design. However, there may not be enough lift under the low Reynolds. It has been proved that the coupling between the bending mode and torsional mode of the flapping wings is effective for increasing lift,and resonance incentive amplification mechanism can be used to realize that. But this mechanism has a strong request of accurate mode design. Finite element model of bionic flapping-wing is established at first, and the modal analysis is performed. A method of modal discrimination is proposed. For meeting the rules of modes, two improved schemes are proposed. Finite element simulation is used to verify the improvement of these improved schemes. Combining with two schemes, a new flapping-wing model with two oblique beams and variable main beam section area is proposed. The parametric model is founded based on PCL language. Then, the size optimization is conducted on the parametric model, and an ideal flapping-wing model is obtained. This paper is of great theoretical significance and practical value in the field of the design and optimization of the flapping wing.