[특허]Structural mechanism for unlocking and engaging a controllable surface on a hinged platform (Wing)

The Boeing Company

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특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Structural mechanism for unlocking and engaging a controllable surface on a hinged platform (Wing)

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-003/56 B64C-013/00 F16D-011/04
미국특허분류(USC)	244/049; 244/099.2; 192/069.91
출원번호	UP-0949980 (2007-12-04)
등록번호	US-7665690 (2010-04-09)
발명자 / 주소	Sheahan, Jr., James J. Morris, Charles E.
출원인 / 주소	The Boeing Company
대리인 / 주소	McNees Wallace & Nurick, LLC
인용정보	피인용 횟수 : 3 인용 특허 : 22

초록
▼

A structural mechanism for an aircraft includes a support, a hinged surface, and a hinge assembly joining the hinged surface to the support. An actuation system includes an actuator shaft engaged to the hinges and lying coincident with a hinged-surface hinge axis and extending through the aligned center passageways of the hinges of the hinge assembly. A lock is selectively operable to lock the hinged surface to the support when the actuator shaft engages the lock. An actuator structure is controllably operable to move the actuator shaft longitudinally along the hinge-surface hinge axis between a first shaft axial position wherein the actuator shaft engages the lock and the hinges, and a second shaft axial position wherein the actuator shaft does not engage the lock but does engage the hinges, and is controllably operable to rotate the actuator shaft about the hinged-surface hinge axis.

대표
청구항
▼

What is claimed is: 1. A structural mechanism comprising: an air vehicle support surface; a hinged surface affixed to the air vehicle support surface; a hinge assembly joining the hinged surface to the air vehicle support surface so that the hinged surface may pivot relative to the air vehicle support surface, wherein the hinge assembly comprises at least one hinge, and wherein the at least one hinge have center passageways therethrough linearly aligned along a hinged-surface hinge axis; an actuation system comprising an actuator shaft lying coincident with the hinged-surface hinge axis and extending through the aligned center passageways of the hinges of the hinge assembly, wherein the actuator shaft is engaged to the at least one hinge, a lock selectively operable to lock the hinged surface to the support when the actuator shaft engages the lock, an actuator structure controllably operable to move the actuator shaft longitudinally along the hinge-surface hinge axis between a first shaft axial position wherein the actuator shaft engages the lock and the hinges, and a second shaft axial position wherein the actuator shaft does not engage the lock but does engage the hinges, and controllably operable to rotate the actuator shaft about the hinged-surface hinge axis; and an actuator controller for the actuator structure. 2. The structural mechanism of claim 1, wherein the air vehicle support surface is a deployable wing. 3. The structural mechanism of claim 2, further including: a retention pin-receiver recess in the actuator shaft, a retention pin in the body, wherein the retention pin is disposed to engage the pin-receiver recess when the actuator shaft is in the second shaft axial position, and a retention pin driver that drives the retention pin into the pin-receiver recess when the retention pin is aligned with the pin-receiver recess. 4. The structural mechanism of claim 2, further including: a retention pin-receiver recess in the actuator shaft, a retention pin in the body, wherein the retention pin is disposed to engage the pin-receiver recess when the actuator shaft is in the second shaft axial position, and a retention pin driver that drives the retention pin into the pin-receiver recess when the retention pin is aligned with the pin-receiver recess, and controllably withdraws the retention pin from the pin-receiver recess. 5. The structural mechanism of claim 1, wherein the air vehicle support surface has a thickness of 3 inches or less. 6. The structural mechanism of claim 1, wherein the air vehicle support surface extends from a fuselage of an air vehicle. 7. The structural mechanism of claim 6, wherein the air vehicle support surface is a deployable wing. 8. The structural mechanism of claim 1, wherein the at least one hinge comprises at least two spaced-apart hinges. 9. The structural mechanism of claim 1, wherein each of the hinges of the at least one hinge comprises an interior hinge spline, and the actuator shaft comprises an exterior shaft spline for each of the interior hinge splines, wherein the exterior shaft splines are positioned to engage the respective interior hinge splines to permit movement of the actuator shaft longitudinally along the hinged-surface hinge axis between the first shaft axial position and the second shaft axial position, while continuing to maintain the engagement between the interior hinge splines and the exterior shaft splines. 10. The structural mechanism of claim 1, wherein the lock comprises: an exterior locking spline and a compatible interior locking spline. 11. The structural mechanism of claim 1, wherein the actuator structure comprises: an engagement linear device controllably operable to move the actuator shaft longitudinally along the hinge surface hinge axis between the first shaft axial position and the second shaft axial position, and a rotational actuator engaged to the actuator shaft, whereby the actuator shaft may be controllably rotated. 12. The structural mechanism of claim 1, wherein the actuator controller defines a zeroed pivotable position of the hinged surface when the actuator shaft is in the first shaft axial position. 13. The structural mechanism of claim 1, further including: a retention mechanism that retains the actuator shaft in the second shaft axial position. 14. The structural mechanism of claim 1, further including: a controllable retention mechanism that controllably retains the actuator shaft in the second shaft axial position, and controllably allows the actuator shaft to return to the first shaft axial position. 15. An aircraft comprising: a body of an air vehicle; a folding surface joined to the body of the air vehicle, wherein the folding surface is movable from a stowed position to a deployed position; a control surface; a hinge assembly joining the control surface to the folding surface so that the control surface may pivot relative to the folding surface, wherein the hinge assembly comprises at least two spaced-apart hinges and wherein the at least two spaced-apart hinges have passageways therethrough linearly aligned along a control-surface hinge axis; an actuation system comprising an actuator shaft lying coincident with the control-surface hinge axis and extending through the passageways of the hinges of the hinge assembly, wherein the actuator shaft is engaged to each hinge of the at least two the hinges, a lock selectively operable to lock the control surface to the folding surface when the actuator shaft engages the lock, an actuator structure controllably operable to move the actuator shaft longitudinally along the control-surface hinge axis between a first shaft axial position wherein the actuator shaft engages the lock and the at least two spaced-apart hinges, and a second shaft axial position wherein the actuator shaft does not engage the lock but does engage the hinges, and controllably operable to rotate the actuator shaft about the control-surface hinge axis; and an actuator controller for the actuator structure. 16. The aircraft of claim 15, wherein each of the at least two spaced-apart hinges comprises an interior hinge spline, and the actuator shaft comprises an exterior shaft spline for each of the interior hinge splines, wherein the exterior shaft splines are positioned to engage the respective interior hinge splines to permit movement of the actuator shaft longitudinally along the control-surface hinge axis between the first shaft axial position and the second shaft axial position, while continuing to maintain the engagement between the interior hinge splines and the exterior shaft splines. 17. The aircraft of claim 15, wherein the actuator structure comprises: an engagement linear device controllably operable to move the actuator shaft longitudinally along the control-surface hinge axis between the first shaft axial position and the second shaft axial position, and a rotational actuator engaged to the actuator shaft, whereby the actuator shaft may be controllably rotated. 18. The aircraft of claim 15, wherein the actuator controller defines a zeroed pivotable position of the control surface when the actuator shaft is in the first shaft axial position. 19. The aircraft of claim 15, further including: a retention mechanism that retains the actuator shaft in the second shaft axial position. 20. The aircraft of claim 15, further including: a controllable retention mechanism that controllably retains the actuator shaft in the second shaft axial position, and controllably allows the actuator shaft to return to the first shaft axial position. 21. The aircraft of claim 15, further including: a retention pin-receiver recess in the actuator shaft, a retention pin in the body, wherein the retention pin is disposed to engage the pin-receiver recess when the actuator shaft is in the second shaft axial position, and a retention pin driver that drives the retention pin into the pin-receiver recess when the retention pin is aligned with the pin-receiver recess. 22. The aircraft of claim 15, further including: a retention pin-receiver recess in the actuator shaft, a retention pin in the body, wherein the retention pin is disposed to engage the pin-receiver recess when the actuator shaft is in the second shaft axial position, and a retention pin driver that drives the retention pin into the pin-receiver recess when the retention pin is aligned with the pin-receiver recess, and controllably withdraws the retention pin from the pin-receiver recess. 23. The aircraft of claim 15, wherein the folding surface has a thickness of 3 inches or less. 24. The aircraft of claim 15, wherein the lock comprises: an exterior locking spline and a compatible interior locking spline.

이 특허에 인용된 특허 (22)

이 특허를 인용한 특허 피인용횟수: 3

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특허 상세정보

Structural mechanism for unlocking and engaging a controllable surface on a hinged platform (Wing)

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Structural mechanism for unlocking and engaging a controllable surface on a hinged platform (Wing)

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이 특허에 인용된 특허 (22)

이 특허를 인용한 특허 피인용횟수: 3

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IPC 상세정보(version : 201201)

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