[특허]Thrust reversers including latching mechanisms and methods for manufacturing such thrust reversers

The Boeing Company

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특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Thrust reversers including latching mechanisms and methods for manufacturing such thrust reversers

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-001/54 F02K-001/00
미국특허분류(USC)	060/226.2; 060/796; 244/110.B; 029/889.2
출원번호	US-0936418 (2004-09-08)
등록번호	US-7275362 (2007-10-02)
발명자 / 주소	Strunk,John T. Gabel,Bruce
출원인 / 주소	The Boeing Company
대리인 / 주소	Perkins Coie LLP
인용정보	피인용 횟수 : 7 인용 특허 : 29

초록
▼

Thrust reversers having latching mechanisms and methods for manufacturing such thrust reversers are disclosed herein. An aircraft system in accordance with one embodiment includes a thrust reverser having a first inner panel and a second inner panel opposite the first inner panel. The first and second inner panels have an inner surface and an upper portion. The system further includes a catch projecting inwardly from the inner surface and the upper portion of the first inner panel, and a latch projecting inwardly from the inner surface and the upper port...

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We claim: 1. An aircraft system, comprising: a thrust reverser including a first inner panel and a second inner panel opposite the first inner panel, the first and second inner panels having an inner surface and an upper portion; a catch projecting inwardly from the inner surface and the upper portion of the first inner panel, wherein the catch includes a first member with a first aperture and a second member with a second aperture, the first member being spaced apart from and generally parallel to the second member; a latch projecting inwardly from the inner surface and the upper portion of the second inner panel, the latch positioned to selectively interlock with the catch to inhibit relative movement between the first and second inner panels, wherein the latch is a remotely-actuated latch having a driving mechanism and an engagement member coupled to the driving mechanism, the engagement member having a first end portion and a second end portion; and the driving mechanism is configured to move the engagement member between (a) a lock position in which the first end portion is received at least partially in the first aperture and the second end portion is received at least partially in the second aperture, and (b) a release position in which the first end portion is external to the first aperture and the second end portion is external to the second aperture. 2. The aircraft system of claim 1 wherein the engagement member rotates between the lock position and the release position. 3. The aircraft system of claim 1 wherein the engagement member has a "T" shaped configuration. 4. The aircraft system of claim 1 wherein the first and second inner panels further include a lower portion and an arcuate portion between the upper and lower portions. 5. The aircraft system of claim 1 wherein: the first and second inner panels further include a lower portion and an arcuate portion between the upper and lower portions; and the system further comprises a trigger at least proximate to the lower portion of the second inner panel and an actuator coupling the trigger to the latch. 6. The aircraft system of claim 1, further comprising a support member; wherein the upper portion of the first inner panel is pivotably coupled to the support member; wherein the upper portion of the second inner panel is pivotably coupled to the support member; and wherein the first and second inner panels are inhibited from moving relative to the support member when the latch interlocks with the catch. 7. The aircraft system of claim 1 wherein: the first and second inner panels further include a forward portion and an aft portion opposite the forward portion; and the catch is attached to the forward portion of the first inner panel and the latch is attached to the forward portion of the second inner panel. 8. The aircraft system of claim 1 wherein: the first and second inner panels further include a forward portion and an aft portion opposite the forward portion; and the catch is attached to the aft portion of the first inner panel and the latch is attached to the aft portion of the second inner panel. 9. The aircraft system of claim 1 wherein: the upper portion of the first inner panel is spaced apart from the upper portion of the second inner panel by a gap; and the latch and the catch project into the gap. 10. The aircraft system of claim 1 further comprising: a wing coupled to the thrust reverser; a fuselage attached to the wing; and a tail coupled to the fuselage. 11. An aircraft system, comprising: a support member; a thrust reverser including a first inner wall and a second inner wall opposite the first inner wall, the first inner wall having an inner surface and an upper portion pivotably attached to the support member, the second inner wall having an inner surface and an upper portion pivotably attached to the support member, wherein the first and second inner walls form a barrel through which engine gases pass during operation, and wherein the upper portion of the first inner wall is spaced apart from the upper portion of the second inner wall by a gap; a catch projecting inwardly from the inner surface of the upper portion of the first inner wall into the gap, the catch having an opening; and a latch projecting inwardly from the inner surface of the upper portion of the second inner wall into the gap, the latch including an engagement member movable between (a) a lock position in which the engagement member is at least partially received in the opening of the catch to inhibit the first and second inner walls from pivoting relative to the support member, and (b) a release position in which the engagement member is external to the opening of the catch. 12. The aircraft system of claim 11 wherein the latch further includes (a) a driving mechanism to move the engagement member between the lock and release positions, and (b) a resilient member to urge the engagement member to move in a direction. 13. The aircraft system of claim 11 wherein the engagement member pivots between the lock position and the release position. 14. The aircraft system of claim 11 wherein the engagement member moves linearly between the lock position and the release position. 15. The aircraft system of claim 11 wherein the latch is a remotely-actuated latch. 16. The aircraft system of claim 11 wherein the first and second inner walls further include a lower portion and an arcuate portion between the upper and lower portions. 17. An aircraft system, comprising: a thrust reverser including first and second inner panels each movable between an open position and a closed position, the first and second inner panels having an inner surface and a forward portion, wherein the first and second inner panels form a barrel through which engine gases pass during operation, and wherein at least a segment of the forward portion of the first inner panel is spaced apart from at least a segment of the forward portion of the second inner panel by a gap; a catch projecting inwardly from the inner surface of the forward portion of the first inner panel into the gap; and a remotely-actuated latch projecting inwardly from the inner surface of the forward portion of the second inner panel into the gap, the latch having (a) an engagement member to selectively engage the catch to retain the first and second inner panels in the closed position, and (b) a driver to move the engagement member. 18. The aircraft system of claim 17 wherein: the first and second inner panels further include an upper portion, a lower portion, and an arcuate portion between the upper and lower portions; the catch is coupled to the upper portion of the first inner panel; and the latch is coupled to the upper portion of the second inner panel. 19. The aircraft system of claim 17 wherein: the catch includes an aperture; and the engagement member is movable between (a) a lock position in which the engagement member is at least partially received in the aperture of the catch, and (b) a release position in which the engagement member is external to the aperture of the catch. 20. The aircraft system of claim 17 wherein the driver includes a solenoid. 21. An aircraft system, comprising: a thrust reverser including a first inner panel and a second inner panel opposite the first inner panel, the first and second inner panels having an upper portion, a lower portion, and an arcuate portion between the upper and lower portions, wherein the first and second inner panels form a barrel through which engine gases pass during operation, and wherein the upper portion of the first panel is spaced apart from the upper portion of the second panel by a gap; a receiving member projecting inwardly from the upper portion of the first inner panel into the gap; and an engagement member projecting inwardly from the upper portion of the second inner panel into the gap, the engagement member being selectively movable between (a) a lock position in which the engagement member interlocks with the receiving member to inhibit relative movement between the first and second panels, and (b) a release position in which the engagement member does not inhibit the first and second panels from moving relative to each other. 22. The aircraft system of claim 21 wherein: the first and second inner panels further include an inner surface; the receiving member is coupled to the inner surface of the first inner panel; and the engagement member is operably coupled to the inner surface of the second inner panel. 23. An aircraft system, comprising: a thrust reverser including a first inner panel and a second inner panel opposite the first inner panel, the first and second inner panels having an inner surface and an upper portion, wherein at least one of the first and second inner panels is movable relative to the other and wherein the first and second inner panels form a barrel through which engine gases pass during operation, and wherein the upper portion of the first inner panel is spaced apart from the upper portion of the second inner panel by a gap; and means for selectively inhibiting the first and second panels from moving relative to each other, wherein the means for selectively inhibiting the first and second panels include a catch attached to the first inner panel and a latch attached to the second inner panel, the means for inhibiting projecting inwardly from the inner surface and the upper portion of the first and second inner panels into the gap. 24. The aircraft system of claim 23 wherein the means for selectively inhibiting the first and second panels includes a plate with an aperture and an engagement member sized to be at least partially received in the aperture. 25. The aircraft system of claim 23 wherein the means for selectively inhibiting the first and second panels includes a remotely-actuated latch. 26. An aircraft system, comprising: a thrust reverser including a first inner panel and a second inner panel opposite the first inner panel, the first and second inner panels having an upper portion, wherein at least one of the first and second inner panels is movable relative to the other and wherein the first and second inner panels form a barrel through which engine gases pass during operation, and wherein the upper portion of the first inner panel is spaced a part from the upper portion of the second inner panel by a gap; and a locking mechanism coupled to the first and second inner panels to selectively inhibit the first and second panels from moving relative to each other, wherein the locking mechanism includes a latch projecting inwardly into the gap from inner surface of the upper portion of the first inner panel and a catch projecting inwardly into the gap from the inner surface of the supper portion of the second inner panel. 27. A method for manufacturing a thrust reverser on an aircraft, the thrust reverser having a first inner panel and a second inner panel, wherein the first and second inner panels form a barrel through which engine gases pass during operation, and wherein an upper portion of the first inner panel is spaced apart from an upper portion of the second inner panel by a gap, the method comprising: coupling a catch to an inner surface of an upper portion of the first inner panel such that the catch projects from the first inner panel into the gap; and attaching a latch to an inner surface of an upper portion of the second inner panel such that the latch projects from the second panel into the gap and is positioned to selectively interlock with the catch to inhibit relative movement between the first and second inner panels. 28. The method of claim 27 wherein: coupling the catch includes attaching a plate to the first inner panel, the plate having an opening; and attaching the latch includes coupling an engagement member to the second inner panel, the engagement member having a distal portion sized to be at least partially received within the opening. 29. The method of claim 27 wherein: coupling the catch includes attaching a plate to the first inner panel, the plate having an opening; and attaching the latch includes coupling an engagement member and a driving mechanism to the second inner panel such that the driving mechanism is positioned to move the engagement member between (a) a lock position in which the engagement member is at least partially received in the opening of the plate, and (b) a release position in which the engagement member is external to the opening. 30. The method of claim 27 wherein attaching the latch includes coupling a remotely-actuated latch to the second inner panel. 31. The method of claim 27 wherein: coupling the catch includes attaching the catch to a forward portion of the first inner panel; and attaching the latch includes coupling the latch to a forward portion of the second inner panel. 32. The method of claim 27, further comprising: pivotably coupling the first inner panel to a support member; and pivotably coupling the second inner panel to the support member. 33. The method of claim 27, further comprising: attaching a trigger to a lower portion of the second inner panel; and positioning an actuator between the trigger and the latch to actuate the latch to interlock with the catch. 34. The method of claim 27 wherein the first and second inner panels further include a lower portion and an arcuate portion between the upper and lower portions. 35. A method for operating a latching mechanism on a thrust reverser of an aircraft, the thrust reverser having a first inner panel and a second inner panel forming a barrel through which engine gases pass during operation, wherein the latching mechanism projects into a gap between inner upper portions of the first and second inner panels, the method comprising: remotely actuating a latch to move an engagement member of the latch from (a) a lock position in which the engagement member is interlocked with a catch such that the latch and catch inhibit relative motion between the first and second inner panels, to (b) a release position in which the latch and catch do not inhibit relative movement between the first and second inner panels, wherein the catch projects inwardly from an inner surface of an upper portion of the first inner panel and the latch projects inwardly from an inner surface of an upper portion of the second inner panel; and moving at least one of the first and second inner panels relative to the other. 36. The method of claim 35 wherein remotely actuating the latch comprises actuating a trigger at a lower portion of the second inner panel.

이 특허에 인용된 특허 (29)

이 특허를 인용한 특허 피인용횟수: 7

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Thrust reversers including latching mechanisms and methods for manufacturing such thrust reversers

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