초록 ▼

In a missile system, a simple way to guide a missile in a predetermined trajectory from launch to the impacting with a target for optimum warhead penetration of armor by a guided missile. Initially, the missile is guided in yaw by proportional navigation. Subsequently it is guided in pitch first by

In a missile system, a simple way to guide a missile in a predetermined trajectory from launch to the impacting with a target for optimum warhead penetration of armor by a guided missile. Initially, the missile is guided in yaw by proportional navigation. Subsequently it is guided in pitch first by a pitch programmer until the missile reaches a predetermined gimbal angle between a line of sight of a seeker of the missile and a centerline of the missile, then in pitch by a pseudo-time-optimal closed loop controller to direct the missile pitch attitude at a predetermined rate toward a target until said missile reaches another predetermined gimbal angle, and finally by proportional navigation in pitch of the missile to the target.

대표청구항 ▼

A missile guidance system for guiding a missile in a predetermined trajectory to impact with a target, said trajectory including initial climb, cruise, and attitude transition portions, said guidance system comprising: a seeker carried by said missile for tracking said target; an autopilot, said see

A missile guidance system for guiding a missile in a predetermined trajectory to impact with a target, said trajectory including initial climb, cruise, and attitude transition portions, said guidance system comprising: a seeker carried by said missile for tracking said target; an autopilot, said seeker having a yaw rate channel output coupled to said autopilot for controlling flight of the missile by proportional navigation in the yaw plane; a pitch programmer coupled to said autopilot for controlling flight of the missile in the pitch plane during said climb and cruise portions; a pseudo-time-optimal controller coupled to said autopilot for sharply diving said missile towards the target; and means for controlling the missile in pitch during said attitude transition portion including, threshold detector and switching logic means coupld for receiving pitch gimbal angle signals from said seeker for causing said pseudo-time-optimal controller to apply a constant angular rate to the missile to cause the missile to pitch down sharply towards the target under control of said pseudo-time-optimal controller.