Dynamic Model of Flapping Wing Micro-Aerial-Vehicle
In allusion to design and estimate of flapping flight control, this paper presents the dynamic characteristic of Flapping-wing Micro Aerial Vehicle, and researches the problem of modeling and simulating the dynamic model with Matlab /Simulink. The unsteady instantaneous aerodynamics associated with flapping flight is estimated through improved strip theory, and the aerodynamic characteristic of fuselage and tails has been studied by wind tunnel experiment. Simulation on the proposed model demonstrate that the flight process can be simulated preferably and can manifest the character of flapping flight in evidence. We compare the simulation result with the flight-test data and analyse the angular orientation of flapping flight, then give a primary attitude control strategy and test the efficiency of control system by adding disperse gust to the simulation, the result demonstrate that control system can minish external gust effect on the FMAV in evidence. An analysis has also been made of the fuselage motion of an FMAV resulting from wing flapping and compared it with flight-test data. It is suggested that this motion may reduce the efficiency of task equipment (such as minisize vidicon) and the thrust produced by wings, some techniques should be adopted for eliminating dithering.
flapping-wing dynamic model simulation dithering absorber
Gao Guanglin Song Bifeng Wang Liguang Yang Wenqing Ding Xiang
School of Aeronautics, Northwestern Polytechnical University, Xian 710072, China Navy Flying Academy, Liaoning 125001, China
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
485-488
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）