摘要
运用比例导引实现对目标卫星拦截的中制导方法进行了研究。在发射惯性坐标系中由已知目标卫星和拦截器的实时绝对状态参数构造两者的相对运动参数 ,由此形成导引信号 ,调整拦截器姿态 ,得到正确的推力矢方向 ,然后在拦截器体坐标系中执行制导指令 ,达到抑制视线转率的目的。为此 ,提出了多种导引方案 ,并进行了比较 ,还给出了选择开关曲线的方法。计算结果表明 ,在中段运用比例导引可保证向末制导转换时有较高精度的转换条件。
This paper studies the implementation of intercepting satellite by using proportional guidance in the midcourse. In the launch inertial coordinate system the given realtime absolute state parameters of the satellite and interceptor are combined into their relative motion parameters, which form guidance signals, to adjust the interceptor's attitude to get correct thrust vector orientation. Then, the guidance command is executed in the interceptor's body coordinate system to achieve the aim, which is to restrain line-of-sight(LOS) rate. Accordingly several kinds of guidance plans are put forward and compared. In addition, the method for selection of on-off curves is also given. The computational results show that the transform condition with higher precision to the terminal guidance by using proportional guidance in the midcourse is guaranteed.
出处
《系统工程与电子技术》
EI
CSCD
北大核心
2001年第2期25-27,64,共4页
Systems Engineering and Electronics
