摘要
提出了一种基于标准弹道点的制导方法,以标准弹道的某点为虚拟目标进行需要速度计算及制导,无需修正地球扁率和再入阻力的影响。给出了需要椭圆轨道与需要速度的确定,以及导引与关机控制模型。以某导弹弹道为标准弹道,计算了多种干扰条件下的方法误差。结果表明:其方法误差较小。
A guidance method based on standard ballistic point was put forward in this paper,in which the calculation of the required velocity and guidance were done when some point in standard trajectory was regarded as virtual target,so that the influence of the earth oblateness and reentry aerodynamic resistance would not be revised.The models of the required ellipse orbit,the required velocity and the guidance and shot-off control were presented.The method error under various disturbances while some missile was se...
出处
《上海航天》
北大核心
2008年第1期16-20,共5页
Aerospace Shanghai
关键词
制导
虚拟目标
需要轨道
需要速度
标准弹道点
方法误差
Guidance
Virtual target
Required trajectory
Required velocity
Standard ballistic point
Method error
