The invention discloses a guidance method for
attack time control. The guidance method comprises the following steps of establishing mathematical models of a
missile and a target by considering the three-dimensional space of motion of the
missile and the target; obtaining a
dynamic equation of the trajectory inclination angle and the trajectory
deflection angle of the
missile, and obtaining a
dynamic equation of the distance between the missile and the target, the angle of
sight of the missile and the
deflection angle of
sight of the missile; on the basis, establishing a
dynamic equation of the
attack time error of the missile; then, separately designing the guidance law of the missile according to a pitching channel and a
yaw channel, wherein the guidance law of the pitching channel is designed as an augmented proportion guidance law, the guidance law of the
yaw channel is designed as a guidance law with an
attack time error feedback item, and the trajectory track is adjusted to realize
time control over attack on the target; and when the
yaw angle is zero, adjusting the guidance law of the yaw channel to avoid singularity conditions. According to the guidance method, the
attack time error is estimated, the
attack time error tends to be zero through a guidance strategy, and the distance between the missile and the target tends to be zero. The guidance method for
attack time control has the characteristics of clear structure and high applicability.