Institut Franco Allemand de Recherches de Saint Louis
대리인 / 주소
Oliff &
인용정보
피인용 횟수 :
6인용 특허 :
8
초록▼
A device and method for guiding or steering projectiles (self-propelled or non-self-propelled), or missiles, and for steering a supersonic projectile, or a missile, having a nose, generally in the shape of a cone, having a more or less pointed end, and capable of creating a plasma discharge near the
A device and method for guiding or steering projectiles (self-propelled or non-self-propelled), or missiles, and for steering a supersonic projectile, or a missile, having a nose, generally in the shape of a cone, having a more or less pointed end, and capable of creating a plasma discharge near the end of the projectile over a limited sector of the outer surface of nose.
대표청구항▼
What is claimed is: 1. A method for steering, in a direction Y, a supersonic projectile or a missile having a generally cone-shaped nose, that has a substantially pointed end, comprising discharging plasma over a limited sector of the outer surface of the nose on the side of direction Y. 2. The
What is claimed is: 1. A method for steering, in a direction Y, a supersonic projectile or a missile having a generally cone-shaped nose, that has a substantially pointed end, comprising discharging plasma over a limited sector of the outer surface of the nose on the side of direction Y. 2. The method according to claim 1, comprising creating a plasma discharge proximate the end, over a limited sector of the outer surface of the nose and on the side of direction Y. 3. A method for steering a supersonic projectile or a missile having a nose, generally cone-shaped, that has a substantially pointed end, comprising, for each change in the trajectory of the projectile or the missile, discharging plasma proximate the end over a limited sector of the outer surface of the nose on a side corresponding to a direction toward which the trajectory is to be changed. 4. The steering method according to claim 3, comprising producing plasma discharges, for each change in the trajectory of the projectile or the missile, proximate the end and over a limited sector of the outer surface of the nose. 5. A device for steering a supersonic projectile or a missile having a nose, generally cone-shaped, that has a substantially pointed end, comprising means for emitting a plasma discharge proximate the end over a limited sector of the outer surface of the nose on a side of the nose toward which direction the projectile or the missile is to be steered. 6. The device according to claim 5, wherein the means for emitting a plasma discharge comprise a triggered spark-gap, two electrodes, and a high-voltage generator. 7. The device according to claim 5, wherein the means include at least one pair of electrodes. 8. The device according to claim 6, wherein the means include at least one pair of electrodes.
연구과제 타임라인
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이 특허에 인용된 특허 (8)
Amieux Jean-Claude (Voisins le Bretonneux FRX), Active nutation control system for space vehicle.
Guyton Robert W. (Beavercreek OH) Tinapple Jon A. (Fairborn OH) Cornelius Kenneth C. (Centerville OH), Forebody nozzle for aircraft directional control.
Tilley Scott W. (Belmont CA) Liu Tung Y. (Union City CA) Higham John S. (Mountain View CA), Spacecraft attitude control and momentum unloading using gimballed and throttled thrusters.
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