摘要
目的 :研究并揭示超远程炮弹无控段及滑翔段的弹道特性。方法 :建立无控弹道数学模型和大气数学模型 ,研究初始射角和发动机点火时间的双参数寻优以及弹道下落段最佳起始滑羞翔点的确定 ,建立弹道滑翔段最优控制数学模型 ,研究最优滑翔弹道。
In this paper, by the study of ERGM trajectory characteristics, ERGM free flight and glide trajectory characteristics are revealed and illustrated. On the basis of free flight trajectory mathematical model, a two-parameter optimization problem of quadrant elevation and rocket ignition time is studied. Using the atmosphere mathematical model , the best glide starting point of the downward trajectory is determined. With an optimal control mathematical model, the ERGM optimal glide trajectory is obtained.
出处
《弹箭与制导学报》
CSCD
北大核心
2002年第2期26-30,共5页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
超远程炮弹
无控弹道
最优控制
滑翔弹道
free flight trajectory
parameter optimization
optimal control
optimal glide trajectory
