摘要
为了分析发动机分离对主弹体散布的影响,通过对分离过程进行受力分析,确定了反向燃气喷流、分离速度误差为主弹体散布的扰动因素。通过选择不同分离点,采用蒙特卡洛方法进行仿真分别得到两种影响因素下的落点散布。结果表明:分离速度误差只对距离散布有影响,并随射程和射角的增大而增大;反向燃气喷流对距离散布和方向散布都有影响,方向散布随射程和射角增加而增大,距离散布随射程的增大而增大,随射角的增大而减小;不同分离点弹道参数和大气参数的差异对散布无明显影响。
In order to analyze the influence factor of PGR dispersion,the influence factor was determined by analyzing force of main rocket body and engine,i.e.reverse gas jet and separating speed error.Shooting test was simulated by Monte Carlo after choosing different separation points.The result of simulation shows the separating speed error only effects on range dispersion,which is worse with the increase of range and fire angle.Reverse gas jet has effect on both range dispersion and lateral dispersion.Lateral dispersion is worse with range and fire angle increase.Range dispersion is worse with range increase and better with fire angle increase.Trajectory parameter and air parameter at different separation point has no effect on dispersion.
出处
《弹箭与制导学报》
CSCD
北大核心
2012年第1期119-122,126,共5页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
落点散布
发动机分离
分离速度误差
impact point dispersion
engine separation
separating speed error
