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本文介绍一种电子制导系统,若导弹在发射前已知一组目标位置坐标信息,则该制导系统能计算出飞行阶段导弹在固定惯性坐标系中的位置和速度.惯性坐标系的所有变量,均由以目标位置为中心的三轴正交坐标系确定.该制导系统不采用主动滚动控制便能不断地使导弹速度矢量指向目标位置.
This paper introduces an electronic guidance system, which can calculate the position and velocity of missiles in a fixed inertial coordinate system during the flight phase if all missiles have a known target position coordinate information prior to launch. All variables of the inertial coordinate system, Are determined by a three-axis orthogonal coordinate system centered on the target position.The guidance system continuously directs the missile velocity vector to the target position without active roll control.