[특허]Techniques for providing surface control to a guidable projectile

Woodward HRT, Inc.

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특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Techniques for providing surface control to a guidable projectile

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F42B-010/00 F42B-010/52 F42B-010/62
미국특허분류(USC)	244/003.21; 244/003.24; 244/003.23
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 : 3 인용 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 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 ...

대표
청구항
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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.

이 특허에 인용된 특허 (21)

이 특허를 인용한 특허 피인용횟수: 3

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구성항목	관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표IPC 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 공고번호, 공고일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표출원인, 출원인국적, 출원인주소, 발명자, 발명자E, 발명자코드, 발명자주소, 발명자 우편번호, 발명자국적, 대표IPC, IPC코드, 요약, 미국특허분류, 대리인주소, 대리인코드, 대리인(한글), 대리인(영문), 국제공개일자, 국제공개번호, 국제출원일자, 국제출원번호, 우선권, 우선권주장일, 우선권국가, 우선권출원번호, 원출원일자, 원출원번호, 지정국, Citing Patents, Cited Patents
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Techniques for providing surface control to a guidable projectile

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Techniques for providing surface control to a guidable projectile

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