초록 ▼

Apparatus and method of anti-armor missile trajectory shaping for optimum rhead penetration of armor by a guided missile. The guidance system utilizes a terminal homing guidance unit in conjunction with a programmed control signal through the missile's autopilot to cause the missile to cruise at low

Apparatus and method of anti-armor missile trajectory shaping for optimum rhead penetration of armor by a guided missile. The guidance system utilizes a terminal homing guidance unit in conjunction with a programmed control signal through the missile's autopilot to cause the missile to cruise at low altitudes and then dive onto the armor target. The terminal dive angle can be selected dependent upon the target's armor characteristics.

대표청구항 ▼

1. A missile guidance system for maintaining a missile in a predetermined trajectory to impact with a target, said trajectory including an initial substantially horizontal portion, pitch-up, cruise and attitude transition portions, said guidance system including: (a) programmed guidance means for

1. A missile guidance system for maintaining a missile in a predetermined trajectory to impact with a target, said trajectory including an initial substantially horizontal portion, pitch-up, cruise and attitude transition portions, said guidance system including: (a) programmed guidance means for controlling said missile to said attitude transition portion subsequent to flight in said horizontal, pitch-up, and cruise portions of said trajectory; (b) a seeker carried by said missile for tracking said target; (c) means carried on said missile for determining the angle between the line of sight of said seeker and the body of the missile and for transmitting a signal when said angle reaches a predetermined value said means being a threshold detector, first and second switches disposed in the pitch rate and gimbal angle channels of said seeker, said threshold detector disposed for closing said switches; and (d) autopilot means disposed for receiving said signal to pitch said missile downwardly for impact with said target responsive to said angle reaching said predetermined value. 2. A guidance system as set forth in claim 1 wherein said missile is programmed to said attitude transition portion and utilizes proportional navigation thereafter. 3. A guidance system as set forth in claim 2 including a pitch programmer for programming said missile to said attitude transition portion.