Multi-objective Optimum Design for High-frequencyFlapping-wing Micro Air Vehicle

Abstract

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.

Keywords

• flapping-wing micro air vehicle
• high-frequency fluttering
• nsga-ⅱ
• load distribution
• multi-objective optimum design