Pitching stability analysis of half-rotating wing air vehicle

International Conference on Aerospace, Mechanical and Mechatronic Engineering

航空航天工程;机械制造;无线电电子学

Wang, Xiaoyi^1 ; Wu, Yang^1 ; Li, Qian^1 ; Li, Congmin^1 ; Qiu, Zhizhen^1

School of Mechanical Engineering, Anhui University of Technology, Ma'anshan

243002, China^1

关键词: Additional moment;    Aerodynamic forces;    Air vehicle;    Design and control;    Flapping wing air vehicles;    Flight stability;    Research results;    Stability analysis;   

Others  :  https://iopscience.iop.org/article/10.1088/1757-899X/211/1/012004/pdf
DOI  :  10.1088/1757-899X/211/1/012004

学科分类：航空航天科学

来源: IOP

【 摘 要 】

Half-Rotating Wing (HRW) is a new power wing which had been developed by our work team using rotating-type flapping instead of oscillating-type flapping. Half-Rotating Wing Air Vehicle (HRWAV) is similar as Bionic Flapping Wing Air Vehicle (BFWAV). It is necessary to guarantee pitching stability of HRWAV to maintain flight stability. The working principle of HRW was firstly introduced in this paper. The rule of motion indicated that the fuselage of HRWAV without empennage would overturn forward as it generated increased pitching movement. Therefore, the empennage was added on the tail of HRWAV to balance the additional moment generated by aerodynamic force during flight. The stability analysis further shows that empennage could weaken rapidly the pitching disturbance on HRWAV and a new balance of fuselage could be achieved in a short time. Case study using numerical analysis verified correctness and validity of research results mentioned above, which could provide theoretical guidance to design and control HRWAV.