Guided missile

Details Guided missile Guided missile

1995-09-13

1997-03-25

Carone, Michael J.

Aeronautics and astronautics

Missile stabilization or trajectory control

Automatic guidance

102211, 244 315, 244 319, F42B 1501, F41G 720

Patent

active

056136501

ABSTRACT:
In a guided missile, a target direction detecting unit finds, from target information obtained at a target acquisition unit, a direction of the target in terms of a roll-, a pitch- and a yaw-axis of a missile fuselage, rotation amount computing units computer amounts of rotation around the roll-, pitch- and yaw-axis to allow the missile fuselage to be directed at a predictive missile/target point, and steering control units impart the amounts of rotation to the missile fuselage. Antennas for a proximity fuse are arranged around a circumferential surface side of the missile fuselage and radiate beams in mutually different directions with at least one of these antennas radiating a different beam at a forward-tilt angle other than the remaining ones. A beam forward-tilt angle selecting unit selects a proper forward-tilt angle beam from flight information of the missile and target. The fuselage is controlled based on a result of computation around the roll-axis to allow the selected beam to be oriented toward the direction of the target. It is, therefore, possible to provide a compact guided missile which can select a beam forward-tilt angle in a simple procedure in accordance with the velocity of the target and exert a warhead detonation effect on a missile target having various speed ranges.

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