[특허]Methods and apparatus for missile air inlet

Raytheon Company

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특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Methods and apparatus for missile air inlet

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F41G-007/00 F42B-015/01 G06F-019/00
미국특허분류(USC)	244/003.22
출원번호	UP-0456396 (2006-07-10)
등록번호	US-7851733 (2011-02-10)
발명자 / 주소	Geswender, Chris E.
출원인 / 주소	Raytheon Company
대리인 / 주소	Renner, Otto, Boisselle & Sklar, LLP
인용정보	피인용 횟수 : 1 인용 특허 : 3

초록

Methods and apparatus for delivering a missile may operate in conjunction with a missile comprising an outer skin. The missile may be configured in a closed position and an open position. In the open position, an aperture is opened in the outer skin, for example to supply air to an air-breathing engine. In the closed position, the aperture is closed.

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The invention claimed is: 1. A missile comprising: a framework; an outer skin attached to the framework defining an exterior region of the missile and an interior region of the missile, wherein the outer skin defines an aperture; an engine disposed at least partially within the interior region; a passageway surface defining a passageway between the engine and the aperture; and an aperture control system connected to the outer skin and configured to selectively open the aperture; wherein the aperture control system comprises at least one slidable arm connected to the structural framework, wherein the slidable arm is configured to longitudinally move from a closed position to an open position to open the aperture in the outer skin; and wherein the at least one slidable arm forms part of the outer skin. 2. A missile according to claim 1, wherein the slidable arm comprises: a female member; and a male member at least partially disposed within the female member. 3. A missile according to claim 2, wherein the male member and female member are at least partially rectangular in cross-section. 4. A missile according to claim 1, further comprising a locking mechanism connected to the slidable arm configured to lock the slidable arm in at least one of an open position and a closed position. 5. A missile comprising: a framework; an outer skin attached to the framework defining an exterior region of the missile and an interior region of the missile, wherein the outer skin defines an aperture; an engine disposed at least partially within the interior region; a passageway surface defining a passageway between the engine and the aperture; and an aperture control system connected to the outer skin and configured to selectively open the aperture; wherein the aperture comprises an annular aperture around a circumference of the outer skin; wherein the aperture control system comprises slidable arms extending around the circumference of the outer skin; and wherein the slidable arms each include a female member and a male member, wherein the female members longitudinally move relative to the male members from a closed position to an open position, to open the aperture. 6. A missile according to claim 1, wherein the passageway surface comprises: an aft surface extending between an aft edge of the aperture and the engine, wherein at least a portion of the aft surface is conical; and a forward surface extending between a forward edge of the aperture and a terminus, wherein: the terminus is disposed forward of the engine along a longitudinal axis of the missile; and at least a portion of the forward surface is conical. 7. A missile according to claim 6, wherein the aperture control system moves the aft surface away from the forward surface in conjunction with opening the aperture. 8. A missile, comprising: a framework, comprising a nose section and an aft section, wherein the nose section is configured to move longitudinally relative to the aft section between an open position and a closed position; and a skin, comprising a nose skin section and an aft skin section wherein: the nose skin section is attached to the nose section; the aft skin section is attached to the aft section; a forward edge of the aft skin section engages an aft edge of the nose skin section in the closed position; the forward edge of the aft skin section is separated from the aft edge of the nose skin section in the open position; and the forward edge of the aft skin section and the aft edge of the nose skin section define an annular aperture in the open position; an aperture control system connected to the framework and configured to move the framework between the open position and the closed position; an engine; and an air surface defining a passageway between the aperture and the engine; wherein the aperture control system comprises a plurality of slidable arms, wherein: a first end of each slidable arm is connected to the nose section; a second end of each slidable arm is connected to the aft section; and each slidable arm is configured to move between the closed position and the open position; and wherein the slidable arms form part of an outer skin of the missile. 9. A missile according to claim 8, wherein each of the slidable arms comprises: a female member; and a male member at least partially disposed within the female member. 10. A missile according to claim 9, wherein the male member and female member are at least partially rectangular in cross-section. 11. A missile according to claim 10, further comprising a locking mechanism connected to the slidable arms configured to lock the slidable arms in at least one of an open position and a closed position. 12. A missile according to claim 8 wherein the air surface comprises: a forward surface extending between the aft edge of the nose skin section and a terminus, wherein: the terminus is disposed forward of the engine along a longitudinal axis of the missile; and at least a portion of the forward surface is conical; and an aft surface extending between the forward edge of the aft skin section and the engine, wherein at least a portion of the aft surface is conical. 13. A missile according to claim 12, wherein the aperture control system moves the aft surface away from the forward surface in conjunction with opening the aperture. 14. A missile, comprising: a nose section having a nose skin section; and an aft section having an aft skin section; wherein the nose section moves relative to the aft section between an open position and a closed position; wherein a forward edge of the aft skin section engages an aft edge of the nose skin section in the closed position; wherein the forward edge of the aft skin section is separated from the aft edge of the nose skin section in the open position; and wherein the forward edge of the aft skin section and the aft edge of the nose skin section define an aperture in the open position; further comprising slidable arms of one of the sections that move longitudinally relative to the other of the sections as the nose section moves relative to the aft section between the open position and the closed position; wherein the slidable arms provide a structural joint in an airframe structure of the missile, between the nose section and the aft section; and wherein the slidable arms form part of an outer skin of the missile. 15. The missile of claim 14, wherein each of the slidable arms comprises: a female member; and a male member at least partially disposed within the female member. 16. The missile of claim 15, wherein the male members are parts of one of the skin sections, and the female members are parts of the other of the skin sections. 17. The missile of claim 14 wherein the nose section moves longitudinally relative to the aft section between the open position and the closed position. 18. The missile of claim 17, wherein longitudinal movement of the nose section relative to the aft section, from the closed position to the open position, extends overall length of the missile. 19. The missile of claim 14 wherein the aperture in the open position is an annular aperture. 20. The missile of claim 14 further comprising: an engine; and an air surface defining a passageway between the aperture and the engine.

이 특허에 인용된 특허 (3)

이 특허를 인용한 특허 (1)

Geswender, Chris E., Methods and apparatus for missile air inlet.

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Methods and apparatus for missile air inlet

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특허 상세정보

Methods and apparatus for missile air inlet

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