制导火箭弹大着角所需脉冲发动机数量的确定  

Determination of impulse-motor number for guidance rocket missile with large impact-angle

作　　者：李玉林[1] 杨树兴[1] 

机构地区：[1]北京理工大学宇航科学技术学院,北京100081

出　　处：《固体火箭技术》2008年第5期430-434,共5页Journal of Solid Rocket Technology

摘　　要：推导出制导火箭弹为获得期望着角所需的脉冲发动机数量解析公式,并根据此公式对比研究了火箭弹分别采用同时点火和依次点火时俯仰角初始值、期望着角和脉冲发动机推力对脉冲发动机数量的影响。研究表明,同时点火方式优于依次点火方式;飞行末段姿态调整时间较长时,期望着角和初始俯仰角对发动机数量的影响很小;随着脉冲推力的增加,所需的脉冲发动机数量递减。The analytic formula of impulse-motor number for guidance rocket missile with anticipant impact-angle was derived. Based on the formula, the effects of initial pitch angle, anticipant impact-angle and thrust on impulse-motor number under simulta- neous ignition or sequent ignition conditions were compared. The results show that simultaneous ignition is superior to sequent ignition. When attitude adjustment time at the end of flight is long, initial pitch angle and anticipant impact-angle have seldom effect on impulse-motor number; with the increase of impulse thrust, the required impulse-motor number gradually decreases.

关 键 词：制导火箭 期望着角 脉冲发动机 同时点火 依次点火 姿态控制 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]