火箭弹锥形运动稳定性分析  

The Coning Motion Stability Analysis of Rocket

作　　者：王华毕[1] 吴甲生[2] 

机构地区：[1]安徽军工集团,安徽合肥230022 [2]北京理工大学宇航科学技术学院,北京100081

出　　处：《兵工学报》2008年第5期562-566,共5页Acta Armamentarii

摘　　要：根据滚转火箭弹的动力学方程,给出了在弹体坐标系下无控低速滚转火箭弹在被动飞行段的锥形运动方程组。对方程进行线性化,采用里雅谱诺夫一级近似方法,得出其系统稳定性方程。由Hurwitz判别准则,找出侧向力矩对系统稳定性的影响。结合实际算例验证侧向力矩对火箭弹锥形运动的影响并通过仿真得到临界转速和临界锥角。The nonlinear coning motion equations in body coordinates on the force moment coefficients of low speed spinning rocket were obtained based on the dynamics equations. Through linearization, the system stability equations were set up by Liapunovs first theory. The side moment effect to the stability of the system was obtained by Hurwitz stability criterion. Through the calculated example, the side moment effect to the coning motion of spinning rocket was validated. The critical rotation speed and critical coning angle were obtained by the simulation.

关 键 词：飞行器控制 导航技术 锥形运动 稳定性 火箭弹 侧向力矩 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]