摘要
针对导弹实际飞行弹道与理论弹道的偏差问题,以导弹六自由度弹道方程为基础,分别建立了发动机推力偏心、弹翼及舵安装误差、横风干扰等主要扰动因素模型。仿真计算和对比分析了上述扰动因素对飞行弹道参数的影响。研究结果表明,弹道侧偏主要受发动机推力偏心、舵安装误差、横风干扰影响,弹翼安装误差和舵安装误差会引起明显的弹体滚转扰动。
For the deviation between the missile actual flight trajectory and the theoretical trajectory,the main disturbance models about engine misalignment,wing and rudder installation errors,wind disturbance are established on the base of the six-degree ballistic equations. Simulation and comparison are studied. The results show that the ballistic yawing is mainly affected by engine thrust misalignment,rudder installation error,wind disturbance. the wing and rudder installation errors lead to obvious roll.
作者
杨云刚
刘钧圣
王琨
刘航航
YANG Yun-gang;LIU Jun-sheng;WANG Kun;LIU Hang-hang(Xi′an Modern Control Technology Research Institute,Xi′an, 710065, China)
出处
《指挥控制与仿真》
2018年第3期127-131,共5页
Command Control & Simulation
关键词
弹道参数
推力偏心
安装误差
横风干扰
trajectory parameter
thrust misalignment
installation error
wind disturbance
