高频扑动微扑翼飞行器多目标优化设计  

Multi-objective Optimum Design for High-frequency Flapping-wing Micro Air Vehicle

作　　者：蒋进 郑祥明[1] 冯卓群 沈欢 Jiang Jin;Zheng Xiangming;Feng Zhuoqun;Shen Huan(Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学飞行器先进设计技术国防重点学科实验室,南京210016

出　　处：《航空工程进展》2019年第1期80-86,共7页Advances in Aeronautical Science and Engineering

基　　金：南京航空航天大学研究生创新基地(实验室)开放基金(kfjj20170113);中央高校基本科研业务费江苏高校优势学科建设工程资助项目

摘　　要：微扑翼飞行器高频扑动时机翼与机身最大载荷急剧增加,严重影响飞行性能和飞行寿命。分析微扑翼扑动过程中机翼运动情况及受力情况,建立扑动过程中机翼升力、阻力和惯性力数学模型,提出以改善载荷在时间域上分布情况为目标的多目标优化模型,并且在Matlab环境下采用NSGA-Ⅱ算法进行求解,得到悬停状态下的Pareto最优解集。结果表明:提出的优化模型使升力峰值与惯性力峰值显著降低,载荷分布情况得到明显改善。The maximum load of wing and fuselage increases sharply while flapping-wing micro air vehicles(FWMAVS) flutters at high frequencies, which seriously affect the flight performance and flight life. The mathematical models of wing lift, drag and inertial forces during the FWMAVs fluttering are established, based on the analysis of movement and force conditions of the wing. A multi-objective optimization model targeting at improving the distribution of loads in the time domain is then proposed and solved by using NSGA-Ⅱ algorithm in Matlab environment. After all the work, the Pareto optimal solution set of the hovering state is obtained. Comparison and analysis of the data show that after the optimization, the peaks of lift and inertial forces decline significantly and the load distribution is obviously improved.

关 键 词：微扑翼飞行器 高频扑动 NSGA-Ⅱ 载荷分布 多目标优化 

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]