基于陀螺力学的旋转导弹锥形运动分析  

Coning Motion Analysis of Spinning Missile Based on Gyrodynamics

作　　者：任天荣[1,2] 马建敏[1] 

机构地区：[1]复旦大学力学与工程科学系,上海200433 [2]上海机电工程研究所,上海200233

出　　处：《宇航学报》2010年第9期2082-2087,共6页Journal of Astronautics

摘　　要：针对旋转导弹飞行中弹体的锥形运动,利用陀螺动力学中的双自由度陀螺线性扰动方程建立数学模型,分别分析了纵向静稳定力矩和侧向力矩对旋转导弹锥形运动的作用机理;利用布尔加可夫相空间方程组,分析线性气动阻尼对旋转导弹的锥形运动的影响。结果表明,旋转导弹锥形运动的幅度随弹体气动静稳定性而增加,故气动参数mzα的选择应以导弹质心最靠后时仍能保持弹体纵向中立静稳定为标准,而且线性气动阻尼对旋转导弹的锥形运动的稳定是不利的,并最后导致旋转导弹锥形运动的发散。Aiming at the coning motion of spinning missiles in flight,a mathematic model is constructed by means of two-degree of freedom gyro linear equation,and principles of the coning motion influenced by a longitudinal static moment and a lateral stabic moment are analyzed respectively,and the effect of linear aerodynamic damping on the coning motion is analyzed with the Bulgakov phase space theory.The study indicates that the amplitude of coning motion increases with the increase of the aerodynamic static stability,and the way to select the aerodynamics parameter mzα is to take that the missile is kept in the neutral static stability when its centre of mass is in the utmost rear limit as a standard,and the linear aerodynamic damping has unfavorable effects on the stability of the coning motion and results in divergent.

关 键 词：旋转导弹 陀螺动力学 锥形运动 稳定性 

分 类 号：TJ760.1[兵器科学与技术—武器系统与运用工程]