某型末制导炮弹惯导飞行角运动研究  

Research on the Characters of Angular Motion of Terminal Guide Shell on the Stage of Inertial Flight

作　　者：佟德飞[1] 宋卫东[1] 杨晓霖[1] 

机构地区：[1]军械工程学院火炮工程系,河北石家庄050003

出　　处：《军械工程学院学报》2014年第1期32-35,共4页Journal of Ordnance Engineering College

摘　　要：为研究某型末制导炮弹惯性飞行过程的稳定性,建立该炮弹在惯导飞行阶段有控弹道攻角运动方程.基于该攻角运动方程,求解方程特征根推导出末制导炮弹自由运动的稳定性条件,并给出舵片偏转控制力对弹体强迫作用的解,分别讨论了影响自由运动和受迫运动稳定性的因素.分析结果表明,惯性飞行过程中,舵面参数以及弹丸转动角速度是影响飞行稳定的主要因素,舵片偏转过程与弹丸共振条件无关.In order to study the stability of terminally guided shell during inertial flight,the angu-lar motion of controllable traj ectory is investigated.Based on the general angular motion,flight stability condition is fixed and the canards deflexion imposed on the body is obtained through the special solution of angular motion.The main relative factor of stability of inertial flight is dis-cussed.The results indicate that canards parameters and angular velocity are main factors which influence the dynamic stability,and canards deflexion has no relationship to the sympathetic vibra-tion condition of traj ectory body.

关 键 词：有控弹道 舵片偏转 角运动 飞行稳定性 

分 类 号：TJ012.3[兵器科学与技术—兵器发射理论与技术]