[특허]Decoupled steering/planing air vehicle nose landing gear

Lockheed Martin Corporation

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특허 상세정보

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Decoupled steering/planing air vehicle nose landing gear

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-025/10 B64C-025/00 B64C-025/20
미국특허분류(USC)	244/102.A; 244/102.SS
출원번호	UP-0933962 (2004-09-03)
등록번호	US-7621481 (2009-12-02)
발명자 / 주소	Hershberger, Brian Keith Devine, David J. Sehic, Axel
출원인 / 주소	Lockheed Martin Corporation
대리인 / 주소	Koestner Bertani LLP
인용정보	피인용 횟수 : 4 인용 특허 : 28

초록
▼

A landing gear assembly comprises a landing gear strut assembly further comprising a landing gear strut having a longitudinal axis and extending from an inboard end to an outboard end capable of attaching to a wheel, and a landing gear housing. The landing gear housing has a longitudinal axis coincident with the landing gear strut longitudinal axis and having an interior chamber capable of accepting a portion of the landing gear strut. The landing gear housing is capable of pivotably coupling to an aircraft. The landing gear assembly further comprises a retraction linkage having an inboard end capable of coupling to the aircraft and an outboard end coupled to the landing gear housing. The retraction linkage is moveable to retract the landing gear strut assembly into an aircraft landing gear compartment about the landing gear housing pivotable aircraft coupling. The landing gear assembly further comprises a steering linkage capable of coupling and decoupling to the landing gear strut and, when coupled, capable of steerably rotating the landing gear strut with respect to the landing gear housing about the coincident longitudinal axis. The landing gear assembly further comprises a planing linkage that can gradually rotate the landing gear strut into a planar position as the landing gear strut assembly is retracted and decoupled from the steering linkage.

대표
청구항
▼

What is claimed is: 1. A landing gear assembly comprising: a landing gear strut assembly comprising: a landing gear strut having a longitudinal axis and extending from an inboard end to an outboard end configured to attach to a wheel; and a landing gear housing having a longitudinal axis that is coincident with the landing gear strut longitudinal axis and having an interior chamber configured to accept a portion of the landing gear strut, the landing gear housing configured for pivotable coupling to an aircraft; a retraction linkage having an inboard end configured to couple to the aircraft and an outboard end coupled to the landing gear housing, the retraction linkage being moveable to retract the landing gear strut assembly into an aircraft landing gear compartment about the pivotable coupling; a steering linkage configured to couple and decouple to the landing gear strut and, when coupled, configured to steerably rotate the landing gear strut with respect to the landing gear housing about the landing gear strut longitudinal axis and decoupling from the landing gear strut in a fully retracted position, wherein the steering linkage further comprises: a first planar axial element associated with the landing gear strut assembly and a second planar axial element associated with an aircraft wheel steering mechanism, the first and second planar axial elements being in parallel alignment and configured for mutual rotation about a central axis; and roller pins mounted to the first planar axial element, the roller pins disengaging from the second planar axial element when the landing gear strut assembly is retracted, freeing the first planar axial element for movement independent of the second planar axial element; and a planing linkage having a longitudinal axis that is coincident with the central axis when extended, the planing linkage being configured to gradually rotate the landing gear strut into a planar position as the landing gear strut assembly is retracted. 2. The landing gear assembly according to claim 1 wherein the steering linkage further comprises: the landing gear strut during landing gear assembly retraction being configured for rotation about the planing linkage longitudinal axis mutually disengaging the first and second planar axial elements and decoupling an aircraft wheel steering mechanism from the roller pins; and the planing linkage coupled to the first planar axial element and constraining landing gear strut movement during retraction to a rotational moment that rotates the landing gear strut to a planar configuration. 3. The landing gear assembly according to claim 1 further comprising: a hinged linkage that couples the landing gear strut to the landing gear housing. 4. The landing gear assembly according to claim 1 further comprising: a collar coupled to the landing gear housing and configured for rotation about the landing gear strut longitudinal axis; and a hinged linkage that couples the landing gear strut to the landing gear housing, the hinged linkage moving to a planar configuration on retraction. 5. The landing gear assembly according to claim 1 wherein the retraction linkage further comprises: a shaft portion mounted to the landing gear housing; a handle portion extending upwardly into the aircraft landing gear compartment for connection to the aircraft and the retraction linkage configured to retract and extend the landing gear; and a hinge coupling the shaft portion and the handle portion. 6. The landing gear assembly according to claim 1 wherein the retraction linkage further comprises: a shaft portion mounted to the landing gear housing; a handle portion extending upwardly into the aircraft landing gear compartment for connection to the aircraft and the retraction linkage configured to retract and extend the landing gear; and a hinge coupling the shaft portion and the handle portion wherein upon actuation of an aircraft landing gear mechanism the retraction linkage is drawn upwardly into the aircraft landing gear compartment, pivoting the landing gear strut assembly about the planing linkage longitudinal axis into a planar configuration. 7. A landing gear assembly comprising: a landing gear strut having a longitudinal axis and extending from an inboard end to an outboard end configured to attach to a wheel; and a landing gear housing having a longitudinal axis that is coincident with the landing gear strut longitudinal axis and having an interior chamber configured for accepting a portion of the landing gear strut, the landing gear housing including a pivotable couple configured to pivotably couple the landing gear housing to an aircraft; a retraction linkage having an inboard end configured to couple to the aircraft and an outboard end coupled to the landing gear housing, the retraction linkage being moveable to retract the landing gear strut into an aircraft landing gear compartment about the landing gear housing pivotable couple; a steering linkage configured to couple and decouple to the landing gear strut and, when coupled, to steerably rotate the landing gear strut with respect to the landing gear housing about the landing gear strut longitudinal axis and decoupling from the landing gear strut in a fully retracted position; and a planing linkage having a longitudinal axis that is coincident with a landing gear strut steering axis when extended, the planing linkage being configured to gradually rotate the landing gear strut into a planar position as the landing gear strut is retracted, the steering linkage further comprises: first and second planar axial elements in parallel alignment and configured for mutual rotation about the landing gear strut steering axis; roller pins mounted to the first planar axial element, the landing gear strut during landing gear assembly retraction being configured for rotation about the planing linkage longitudinal axis mutually disengaging the first and second planar axial elements and decoupling an aircraft wheel steering mechanism from the roller pins; and the planing linkage coupled to the first planar axial element and constraining landing gear strut movement during retraction to a rotational moment that rotates the landing gear strut to a planar configuration. 8. The landing gear assembly according to claim 7 further comprising: a hinged linkage that couples the landing gear strut to the landing gear housing. 9. The landing gear assembly according to claim 7 further comprising: a collar coupled to the landing gear housing and configured for rotation about the landing gear strut longitudinal axis; and a hinged linkage that couples the landing gear strut to the landing gear housing, the hinged linkage moving to a planar configuration on retraction. 10. The landing gear assembly according to claim 7 wherein the retraction linkage further comprises: a shaft portion mounted to the landing gear housing; a handle portion extending upwardly into the aircraft landing gear compartment to connect to the aircraft and the retraction linkage configured to retract and extend an aircraft landing gear; and a hinge coupling the shaft portion and the handle portion. 11. The landing gear assembly according to claim 7 wherein the retraction linkage further comprises: a shaft portion mounted to the landing gear housing; a handle portion extending upwardly into the aircraft landing gear compartment for connection to the aircraft and the retraction linkage configured to retract and extend an aircraft landing gear; and a hinge coupling the shaft portion and the handle portion wherein upon actuation of an aircraft landing gear mechanism the retraction linkage is drawn upwardly into the aircraft landing gear compartment, pivoting the landing gear strut about the planing linkage longitudinal axis into a planar configuration. 12. A landing gear assembly comprising: a steering linkage configured to couple and decouple to a landing gear strut and, when coupled, configured to steerably rotate the landing gear strut with respect to a landing gear housing about a longitudinal axis of the landing gear strut and decoupling from the landing gear strut in a fully retracted position, the steering linkage further comprising: a first planar axial element associated with the landing gear strut and second planar axial element associated with an aircraft wheel steering mechanism, the first and second planar axial elements being in parallel alignment and configured for mutual rotation about a central axis; and roller pins mounted to the first planar axial element, the roller pins disengaging from the second planar axial element when the landing gear strut is retracted freeing the first planar axial element for movement independent of the second planar axial element; and a planing linkage having a longitudinal axis that is coincident with the central axis when extended, the planing linkage being configured to gradually rotate the landing gear strut into a planar position as the landing gear strut is retracted. 13. The landing gear assembly according to claim 12 further comprising: a hinged linkage that couples the landing gear strut to the landing gear housing. 14. The landing gear assembly according to claim 12 further comprising: a collar coupled to the landing gear housing and being configured for rotation about the longitudinal axis of the landing gear strut with respect to the landing gear housing; and a hinged linkage that couples the landing gear strut to the landing gear housing, the hinged linkage moving to a planar configuration on retraction. 15. The landing gear assembly according to claim 12 further comprising: a retraction linkage having an inboard end configured for coupling to an aircraft and an outboard end coupled to the landing gear housing, the retraction linkage being moveable to retract the landing gear strut into an aircraft landing gear compartment about a pivotable coupling of the landing gear housing to the aircraft, the retraction linkage further comprising: a shaft portion mounted to the landing gear housing; a handle portion extending upwardly into the aircraft landing gear compartment for connection to an aircraft and the retraction linkage configured to retract and extend an aircraft landing gear; and a hinge coupling the shaft portion and the handle portion. 16. The landing gear assembly according to claim 12 further comprising: a retraction linkage having an inboard end configured for coupling to an aircraft and an outboard end coupled to the landing gear housing, the retraction linkage being moveable to retract the landing gear strut into an aircraft landing gear compartment about a pivotable coupling of the landing gear housing to the aircraft, the retraction linkage further comprising: a shaft portion mounted to the landing gear housing; a handle portion extending upwardly into the aircraft landing gear compartment for connection to an aircraft and the retraction linkage configured to retract and extend an aircraft landing gear; and a hinge coupling the shaft portion and the handle portion wherein upon actuation of an aircraft landing gear mechanism the retraction linkage is drawn upwardly into the aircraft landing gear compartment, pivoting the landing gear strut assembly about the planing linkage longitudinal axis into a planar configuration. 17. The landing gear assembly according to claim 12 further comprising: a landing gear strut having a longitudinal axis and extending from an inboard end to an outboard end configured to attach to a wheel; and a landing gear housing having a longitudinal axis that is coincident with the landing gear strut longitudinal axis and having an interior chamber configured for accepting a portion of the landing gear strut, the landing gear housing being configured for pivotably coupling to an aircraft; and a retraction linkage having an inboard end configured to couple to the aircraft and an outboard end coupled to the landing gear housing, the retraction linkage being moveable to retract the landing gear strut assembly into an aircraft landing gear compartment about the landing gear housing pivotable aircraft coupling. 18. The landing gear assembly according to claim 12 further comprising: a retraction linkage having an inboard end configured to couple to an aircraft and an outboard end coupled to the landing gear housing, the retraction linkage being moveable to retract the landing gear strut assembly into an aircraft landing gear compartment about a pivotable coupling of the landing gear housing to the aircraft.

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이 특허를 인용한 특허 피인용횟수: 4

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Decoupled steering/planing air vehicle nose landing gear

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이 특허에 인용된 특허 (28)

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Decoupled steering/planing air vehicle nose landing gear

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이 특허에 인용된 특허 (28)

이 특허를 인용한 특허 피인용횟수: 4

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