Pitching Stability Analysis And Empennage Design Of Half-Rotating Wing Air Vehicle

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),which is similar as Bionic Flapping Wing Air Vehicle(BFWAV),is expected to make breakthrough in large scale of Bionic Air Vehicle(BAV).The research of flying stability of air vehicle is very important during the period of design and manufacture of BAV.Based on this background,the pitching stability of HRWAV was investigated in detail and a new kind of method about empennage design was proposed which not only provide support for attitude research of HRWAV,but also furnish theoretical guidance to aircraft structure design.The main contents of this dissertation were list as follows:Firstly,the aerodynamic force layout of HRWAV.In this paper,a new kind of bionic motion mechanism called Half-Rotating Mechanism(HRM)was introduced.By establishing the mechanical model of HRM,the working principle of HRM was introduced and the aerodynamic force of HRM in different combinations were calculated,the effect of empennage in air vehicle was also included.Secondly,pitching stability analysis of HRWAV.The mechanical model including two cases that were HRWAV without empennage and HRWAV with empennage were established,which were used to analyze the stability of HRWAV and that was verified by numerical analysis.Thirdly,design of bionic swallow-type branch tail.In this paper,the design of the tail was derivated theoretically and calculated quantitatively,which was focused from the orientation of the branch tail axis and the shape of the airfoil,and simultaneously inspired by a high mobility bird-swallow's tail.Thereby,the preliminary scheme of the bionic tail of the wing was presented to apply to the HRW.Finally,research on layout design and control strategy of HRW for attitude control.On the basis of the analysis on pitch stability and the design of bionic tail of aircraft,this paper presented a layout design and control strategy for attitude control applied for HRWAV based on fixed wing aircraft in order to realize the attitude control of HRWAV,which would later provide reference for the design of other structural parameters and attitude control of HRWAV.