发射圆轨道卫星运载火箭的制导

圆轨道卫星偏心率的一阶偏导数在入轨点不存在,因此,给我们沿用以往的线性偏导数制导理论造成了困难。经过研究简捷地找到了圆轨道卫星偏心率偏差的毕达哥拉斯公式,解决了发射圆轨道卫星制导问题,并给出了通过调整发动机关机时间和末级飞行程序来达到设计时需要的圆轨道的标准指标公式。

THE GUIDANCE OF ROCKET FOR LAUNCHING CIRCLE-ORBIT SATELLITES

The first order partial derivatives of the eccentricity for circle-orbit satellites are non-existent at the point of orbite injection. This cause troubles in using the guidance theory of linear partial derivatives in the past time. We find a pythagoras's formula of eccentric deviation briefly for such cases that enable us to realize circular orbit injection. We also derive out the formula to obtain normal index of circular orbit by adjusting the shut down time of the engine and the flight program of the last stage in design.