Techniques for providing surface control to a guidable projectile
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F42B-010/00
F42B-010/52
F42B-010/62
출원번호
UP-0820815
(2007-06-21)
등록번호
US-7791007
(2010-09-27)
발명자
/ 주소
Harnoy, Amir
출원인 / 주소
Woodward HRT, Inc.
대리인 / 주소
BainwoodHuang
인용정보
피인용 횟수 :
3인용 특허 :
21
초록▼
A guidable projectile has a central shaft, a projectile body, and a surface control assembly. The projectile body is arranged to rotate around at least a portion of the central shaft during flight of the guidable projectile to provide stabilization. The surface control assembly is supported by the c
A guidable projectile has a central shaft, a projectile body, and a surface control assembly. The projectile body is arranged to rotate around at least a portion of the central shaft during flight of the guidable projectile to provide stabilization. The surface control assembly is supported by the central shaft. The surface control assembly includes a movable member arranged to control a trajectory of the guidable projectile during flight of the guidable projectile, and an electromagnetic actuator interconnected between the central shaft and the movable member. The electromagnetic actuator is arranged to control movement of the movable member relative to the central shaft.
대표청구항▼
What is claimed is: 1. A surface control assembly, comprising: a central shaft mount arranged to mount to a central shaft of a guidable projectile, the guidable projectile having a roll portion which rotates around at least a portion of the central shaft during flight of the guidable projectile to
What is claimed is: 1. A surface control assembly, comprising: a central shaft mount arranged to mount to a central shaft of a guidable projectile, the guidable projectile having a roll portion which rotates around at least a portion of the central shaft during flight of the guidable projectile to provide stabilization; a movable member arranged to control a trajectory of the guidable projectile during flight of the guidable projectile, wherein the movable member defines a flight control surface; an electromagnetic actuator interconnected between the central shaft mount and the movable member, the electromagnetic actuator being arranged to control movement of the movable member relative to the central shaft mount, wherein the electromagnetic actuator is arranged to control angular orientation of the flight control surface relative to a central axis defined by the central shaft; and a latching mechanism supported by the central shaft mount, the latching mechanism being arranged to bias the movable member to a latching position relative to the central shaft mount. 2. A surface control assembly as in claim 1 wherein the latching mechanism includes: a pull spring having a first end adjacent the central shaft mount and a second end adjacent the movable member, the pull spring being arranged to provide an attractive spring force which biases the movable member to the latching position relative to the central shaft mount. 3. A surface control assembly as in claim 1 wherein the latching mechanism includes: a push spring having a first end adjacent the central shaft mount and a second end adjacent the movable member, the push spring being arranged to provide a repulsive spring force which biases the movable member to the latching position relative to the central shaft mount. 4. A surface control assembly as in claim 1 wherein the latching mechanism includes: a pull spring having a first end adjacent the central shaft mount and a second end adjacent the movable member, the pull spring being arranged to provide an attractive spring force which biases the movable member in a first direction relative to the central shaft mount; and a push spring having a first end adjacent the central shaft mount and a second end adjacent the movable member, the push spring being arranged to provide a repulsive spring force which biases the movable member in a second direction relative to the central shaft mount, the attractive spring force provided by the pull spring and the repulsive spring force provided by the push spring operating to substantially bias the movable member to the latching position relative to the central shaft mount. 5. A surface control assembly as in claim 1 wherein the movable member is a nose cone of the guidable projectile; wherein the roll portion is a projectile body of the guidable projectile which follows the nose cone during flight; and wherein the electromagnetic actuator is arranged to tilt the nose cone relative to the projectile body during flight. 6. A surface control assembly as in claim 1, further comprising: a static nose member which is constructed and arranged to couple to the central shaft and remain substantially stationary with respect to the central shaft during flight, the movable member being constructed and arranged to move relative to the static nose member during flight to provide trajectory control. 7. A surface control assembly as in claim 6, further comprising: a hinge having a first end coupled to the central shaft mount and residing within the static nose member, a second end coupled to the movable member, and mid section which extends between the first and second ends and through an opening defined by the static nose member. 8. A guidable projectile having a surface control assembly as in claim 1. 9. A surface control assembly, comprising: a central shaft mount arranged to mount to a central shaft of a guidable projectile, the guidable projectile having a roll portion which rotates around at least a portion of the central shaft during flight of the guidable projectile to provide stabilization; a movable member arranged to control a trajectory of the guidable projectile during flight of the guidable projectile, wherein the movable member defines a flight control surface; and an electromagnetic actuator interconnected between the central shaft mount and the movable member, the electromagnetic actuator being arranged to control movement of the movable member relative to the central shaft mount, wherein the electromagnetic actuator is arranged to control angular orientation of the flight control surface relative to a central axis defined by the central shaft; wherein the electromagnetic actuator includes (i) a first coil disposed at a first location relative to the central shaft mount, (ii) a second coil disposed at a second location relative to the central shaft mount, and (iii) a permanent magnet disposed between the first and second coils; wherein the first coil and the second coil are arranged to receive respective electrical signals from control circuitry disposed at a fixed location relative to the central shaft mount; and wherein the angular orientation of the flight control surface defined by the movable member is dependent on an amount of displacement of the permanent magnet between the first and second coils. 10. A surface control assembly as in claim 9 wherein the movable member is a nose cone of the guidable projectile; wherein the roll portion is a projectile body of the guidable projectile which follows the nose cone during flight; and wherein the electromagnetic actuator is arranged to tilt the nose cone relative to the projectile body during flight. 11. A surface control assembly as in claim 9, further comprising: a static nose member which is constructed and arranged to couple to the central shaft and remain substantially stationary with respect to the central shaft during flight, the movable member being constructed and arranged to move relative to the static nose member during flight to provide trajectory control. 12. A surface control assembly as in claim 11, further comprising: a hinge having a first end coupled to the central shaft mount and residing within the static nose member, a second end coupled to the movable member, and mid section which extends between the first and second ends and through an opening defined by the static nose member. 13. A guidable projectile having a surface control assembly as in claim 9. 14. A surface control assembly, comprising: a central shaft mount arranged to mount to a central shaft of a guidable projectile, the guidable projectile having a roll portion which rotates around at least a portion of the central shaft during flight of the guidable projectile to provide stabilization; a movable member arranged to control a trajectory of the guidable projectile during flight of the guidable projectile, wherein the movable member defines a flight control surface; and an electromagnetic actuator interconnected between the central shaft mount and the movable member, the electromagnetic actuator being arranged to control movement of the movable member relative to the central shaft mount, wherein the electromagnetic actuator is arranged to control angular orientation of the flight control surface relative to a central axis defined by the central shaft; wherein the electromagnetic actuator includes: a coil and a soft magnetic member having soft magnetic material, the coil and the soft magnetic member forming a soft magnet in response to an electrical signal from control circuitry disposed at a fixed location relative to the central shaft mount, the angular orientation of the flight control surface defined by the movable member being dependent on an amount of displacement of the soft magnetic member relative to the central shaft mount. 15. A surface control assembly as in claim 14 wherein the movable member is a nose cone of the guidable projectile; wherein the roll portion is a projectile body of the guidable projectile which follows the nose cone during flight; and wherein the electromagnetic actuator is arranged to tilt the nose cone relative to the projectile body during flight. 16. A surface control assembly as in claim 14, further comprising: a static nose member which is constructed and arranged to couple to the central shaft and remain substantially stationary with respect to the central shaft during flight, the movable member being constructed and arranged to move relative to the static nose member during flight to provide trajectory control. 17. A surface control assembly as in claim 16, further comprising: a hinge having a first end coupled to the central shaft mount and residing within the static nose member, a second end coupled to the movable member, and mid section which extends between the first and second ends and through an opening defined by the static nose member. 18. A guidable projectile having a surface control assembly as in claim 14. 19. A surface control assembly, comprising: a central shaft mount arranged to mount to a central shaft of a guidable projectile, the guidable projectile having a roll portion which rotates around at least a portion of the central shaft during flight of the guidable projectile to provide stabilization; a movable member arranged to control a trajectory of the guidable projectile during flight of the guidable projectile; and an electromagnetic actuator interconnected between the central shaft mount and the movable member, the electromagnetic actuator being arranged to control movement of the movable member relative to the central shaft mount; wherein the movable member is a fin of the guidable projectile; wherein the roll portion is a projectile body of the guidable projectile which follows the nose cone during flight; and wherein the electromagnetic actuator is arranged to control angular displacement of the fin relative to the projectile body during flight. 20. A guidable projectile having a surface control assembly as in claim 19.
Hurlimann Walter (Watt ; Regensdorf CH), Projectile fuze for a spinning projectile containing a detonator cap and an electromagnetic firing or ignition current g.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.