噪声与振动控制2018，Vol.38Issue(z1)：376-382,7.DOI:10.3969/j.issn.1006-1355.2018.Z1.080
仿生扑翼模态分析研究与优化设计
Modal Analysis and Optimization on Flapping-wing
摘要
Abstract
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.关键词
振动与波/仿生扑翼/模态分析/模态种类判别/有限元仿真/尺寸优化Key words
vibration and wave/bionic flapping-wing/modal analysis/modal discrimination/finite element simulation/size optimization分类
航空航天引用本文复制引用
崔颖,贺媛媛..仿生扑翼模态分析研究与优化设计[J].噪声与振动控制,2018,38(z1):376-382,7.基金项目
国家自然科学基金资助项目(113020207) （113020207）
