滚转偏转头导弹动态特性分析

Dynamic Characteristic Analysis of Roll Deflectable Nose Missile

基于复角模型,研究了弹头偏转对于偏转头导弹飞行稳定性和操纵性的影响。依据偏转头导弹的多体特点,建立了包含弹头和弹体动力学特征的滚转偏转头导弹多体动力学模型,通过模型简化,得出了其复角模型。以弹头偏角作为输入,攻角和侧滑角作为输出,得出了滚转偏转头导弹的传递函数。分析传递函数发现,弹头偏转主要影响了导弹传递函数的零点,文中给出了满足系统最小相位的条件公式;当弹体绕纵轴逆时针旋转时(由弹尾向前看),导弹模型总为最小相位系统;定性分析了气动参数对于导弹运动稳定性的影响,得出弹头偏转运动对于飞行稳定性没有直接影响的结论;动力学仿真表明,弹头与弹体相互作用,导致两者产生相反的角运动。本研究表明,通过合理的选择气动和结构参数,并使导弹飞行过程中绕纵轴逆时针旋转,可以保证偏转头滚转导弹飞行过程中的运动稳定性,并有利于自动驾驶仪的设计。

The analysis of maneuverability and stability of a roll deflectable nose missile based on the plural angle model is presented in the paper.A dynamics model including motions of the nose and the main body is built.According to the simplified dynamics model,its plural angle model is gotten.Taking the angle of attack and side slip angle as output and deflectable angle of nose as input,transfer functions are given.By analyzing the transfer functions,it is found that this missile model belongs to a minimum phase system if it rolls counter clockwise round the longitudinal axis of the body.The effect of aerodynamic parameters on the stability and maneuverability is analyzed according to latent roots of transfer functions.The research show that it is advantageous to the flight stability and design of autopilot properly setecting aerodynamic and structural parameters as well as making the missile counter clockwise roll.