摘要
针对固体助推滑翔弹主动段制导问题,提出一种满足最大高度、再入倾角约束的耗尽关机闭路制导方法。该方法基于开普勒定理和能量守恒定理,得到了满足最大高度、再入倾角约束的自由轨道,并据射程、射向修正轨道,获得导弹需用速度;然后以改进通用能量管理(GEM)方法对发动机剩余能量进行管理,实现了耗尽关机闭路制导。在地球旋转椭球模型下,分别对定轨精度和主动段制导效果进行了数学仿真验证,结果表明:1)修正轨道后,高度、再入倾角精度明显提升,其中倾角误差减小了2个数量级;2)可以高精度地实现不同高度、倾角约束弹道,制导指令姿态变化平缓,有利于控制实现。
According to satisfy the constraints of maximum height and reentry angle of boost glide missile, a depleted shutdown closed loop guidance is proposed. The required velocity to meet the constraints is obtained from the ballistic segment trajectory, which is based on the Kepler＇s law and the law of conservation of energy and is modified according to its direction and range. And then, the closed loop depleted shutdown guidance is completed by using general energy management （GEM） method to waste excessive energy. Fi- nally, based on the ellipsoid earth model, the precision and effect of proposed method is verified by computer simulation. The results show that the precision of maximum height and reentry angle are improved through modification and particularly the error of reentry angle is decreased by two orders of magnitude. Moreover, the high -precision trajectory of difference height and reentry angle can be achieved and is suitable to con- trol system as the attitude angle command changes slowly.
出处
《航天控制》
CSCD
北大核心
2014年第2期68-72,共5页
Aerospace Control
关键词
闭路制导
耗尽关机
多约束
助推滑翔
Closed loop guidance
Depleted shutdown
Multi - constraints
Boost glide
