自旋导弹飞行共振稳定性研究

Analysis of resonance stability for spinning missile

弹体滚转时,结构不对称等因素会对导弹的角运动产生周期性的强迫干扰。针对自旋导弹飞行过程中的周期性干扰和非线性气动特性,建立了非线性弹体角运动模型。在此基础上,采用多尺度法对自旋导弹的受迫角运动方程进行了求解,得到了近似解析解并研究了其稳定性。研究表明,当弹体转动速率接近固有频率时,气动非线性项及干扰项都将影响弹体角运动的稳定性;分析结果显示,合理地设计气动外形可避免共振不稳定的发生,这对自旋类导弹的工程研制具有一定的指导性意义。

The configurational asymmetry can produce a periodic forced interference to the angular motion of missile when it rotates.On the premise of considering the periodic interference and the nonlinear aerodynamic characteristics of spinning missile,a nonlinear mathematic model of coning motion was established.By the method of multiple scales,an approximate analytic solution of nonlinear differential equation was obtained. On this basis,conditions for steady-state forced motion and their stability of spinning missile were researched.The result indicates that both of the nonlinear aerodynamic coefficients and the periodic interference affect the coning motion stability.The resonance instability can be avoided by appropriate selection of aerodynamic configuration. The research results provide theoretical support to design of the spinning missiles.