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公开(公告)号：US10710736B2
公开(公告)日：2020-07-14
申请号：US15798332
申请日：2017-10-30
申请人： The Boeing Company
摘要： There is provided a latch indication system for a fan cowl of an air vehicle. The system has a door movable between a closed position and an open position, and has a handle movable between a handle stowed position and a handle deployed position. The system has a linkage assembly mechanically connecting the handle to a cover assembly. The cover assembly has a movable member movable between a movable member stowed position and a movable member deployed position, such that when the door is in the closed position and the handle is in the handle stowed position, the system indicates that one or more latch assemblies of the fan cowl are in a latched condition, and when the door is in the open position and the handle is in the handle deployed position, the system indicates that one or more of the latch assemblies are in an unlatched condition.
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公开(公告)号：US20180244371A1
公开(公告)日：2018-08-30
申请号：US15445836
申请日：2017-02-28
申请人： The Boeing Company
摘要： A strut assembly for an aircraft landing gear structure according to the present disclosure is transitioned between an extended configuration, corresponding to the aircraft being off the ground, and a retracted configuration, in which the strut assembly is shortened along its longitudinal axis with respect to the extended configuration, for stowage during flight. The strut assembly includes an upper bulkhead supported by an upper tubular housing, and a lower tubular housing configured to be longitudinally translated with respect to the upper tubular housing. To transition the strut assembly to the retracted configuration, translation of the upper bulkhead with respect to the upper tubular housing mechanically causes translation of the lower tubular housing to a retracted position, such that the overall length of the strut assembly is reduced. In some examples, the strut assembly is an oleo strut assembly.
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公开(公告)号：US11186360B2
公开(公告)日：2021-11-30
申请号：US16713525
申请日：2019-12-13
申请人： The Boeing Company
摘要： Methods of retracting a strut assembly for stowing aircraft landing gear comprise longitudinally translating an upper bulkhead within an upper tubular housing from a lower position to an upper position by pressurizing an upper bulkhead space between an upper plate of the upper bulkhead and an upper bulkhead restriction structure that is fixed to the upper tubular housing. Other methods of retracting a strut assembly for stowing aircraft landing gear comprise flowing liquid from an upper liquid chamber positioned above an upper bulkhead within an upper tubular housing to a recoil chamber, wherein during the flowing, the liquid is prevented from passing from the recoil chamber to a pressure chamber that is defined between the upper bulkhead and a lower bulkhead, thereby longitudinally translating a lower tubular housing upward.
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4.发明授权公开(公告)号：US10766608B2
公开(公告)日：2020-09-08
申请号：US15444986
申请日：2017-02-28
申请人： The Boeing Company
摘要： An aircraft landing gear structure includes a retract actuator and a shrink mechanism. The retract actuator is configured to transition a strut assembly of the aircraft landing gear structure between an extended configuration and a retracted configuration via the shrink mechanism, thereby reducing the overall longitudinal length of the strut assembly. The retract actuator is also configured to retract the aircraft landing gear into a stowage area of the aircraft during flight, via a retraction mechanism. The retraction mechanism may be a walking beam that rotates about a retraction axis to retract the aircraft landing gear structure, while simultaneously actuating the shrink mechanism, such as via a drive link coupling the retraction mechanism and the shrink mechanism. The shrink mechanism may be mechanically slaved to the retraction mechanism. The shrink mechanism may be a locking link assembly.
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公开(公告)号：US10669017B2
公开(公告)日：2020-06-02
申请号：US15445836
申请日：2017-02-28
申请人： The Boeing Company
摘要： A strut assembly for an aircraft landing gear structure is transitioned between an extended configuration, corresponding to the aircraft being off the ground, and a retracted configuration, in which the strut assembly is shortened along its longitudinal axis with respect to the extended configuration, for stowage during flight. The strut assembly includes an upper bulkhead supported by an upper tubular housing, and a lower tubular housing configured to be longitudinally translated with respect to the upper tubular housing. To transition the strut assembly to the retracted configuration, translation of the upper bulkhead with respect to the upper tubular housing mechanically causes translation of the lower tubular housing to a retracted position, such that the overall length of the strut assembly is reduced. The strut assembly may be an oleo strut assembly.
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公开(公告)号：US11530030B2
公开(公告)日：2022-12-20
申请号：US17532615
申请日：2021-11-22
申请人： The Boeing Company
摘要： An aircraft tail skid energy absorption indicator including a crushable indicator cartridge disposed within the an outer shock absorber canister of the aircraft tail skid, and an indicator rod coupled to the crushable indicator cartridge so as to move with a portion of the crushable indicator cartridge as a unit, where the indicator rod extends through an aperture in a wall of the outer shock absorber canister, where the indicator rod includes at least one graduation that indicates an amount of remaining energy absorption of the aircraft tail skid energy absorption indicator.
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公开(公告)号：US11242135B2
公开(公告)日：2022-02-08
申请号：US16845148
申请日：2020-04-10
申请人： The Boeing Company
摘要： A tail skid shock absorber including an outer shock absorber canister, a crushable indicator cartridge disposed within the outer shock absorber canister, and an indicator rod coupled to the crushable indicator cartridge so as to move with a portion of the crushable indicator cartridge as a unit.
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公开(公告)号：US20190127075A1
公开(公告)日：2019-05-02
申请号：US15798332
申请日：2017-10-30
申请人： The Boeing Company
摘要： There is provided a latch indication system for a fan cowl of an air vehicle. The system has a door movable between a closed position and an open position, and has a handle movable between a handle stowed position and a handle deployed position. The system has a linkage assembly mechanically connecting the handle to a cover assembly. The cover assembly has a movable member movable between a movable member stowed position and a movable member deployed position, such that when the door is in the closed position and the handle is in the handle stowed position, the system indicates that one or more latch assemblies of the fan cowl are in a latched condition, and when the door is in the open position and the handle is in the handle deployed position, the system indicates that one or more of the latch assemblies are in an unlatched condition.
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公开(公告)号：US20180244373A1
公开(公告)日：2018-08-30
申请号：US15444986
申请日：2017-02-28
申请人： The Boeing Company
CPC分类号： B64C25/26 , B64C25/20 , B64C25/34 , B64C2025/125
摘要： An aircraft landing gear structure according to the present disclosure includes a retract actuator and a shrink mechanism. The retract actuator is configured to transition a strut assembly of the aircraft landing gear structure between an extended configuration and a retracted configuration via the shrink mechanism, thereby reducing the overall longitudinal length of the strut assembly. The retract actuator is also configured to retract the aircraft landing gear into a stowage area of the aircraft during flight, via a retraction mechanism. In some examples, the retraction mechanism is a walking beam that rotates about a retraction axis to retract the aircraft landing gear structure, while simultaneously actuating the shrink mechanism, such as via a drive link coupling the retraction mechanism and the shrink mechanism. In some examples, the shrink mechanism is mechanically slaved to the retraction mechanism. The shrink mechanism is a locking link assembly in some examples.
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10.发明授权公开(公告)号：US11407499B2
公开(公告)日：2022-08-09
申请号：US16789190
申请日：2020-02-12
申请人： The Boeing Company
发明人： Mark Nicholas Simpson , Mitchell Loren Ray Mellor , James E. Cusworth , Justin Cottet , Richard Kevin Johnson , George Sonnenburg
摘要： An aircraft landing gear structure includes a strut assembly and a wheel assembly operatively coupled to the strut assembly. The strut assembly includes an upper tubular housing and a lower tubular housing configured to be longitudinally translated with respect to the upper tubular housing such that the overall length of the strut assembly is transitioned between an extended configuration and a retracted configuration for stowage during flight. The wheel assembly includes a forward link pivotally coupled to the upper tubular housing and a truck beam that is pivotally coupled to the lower tubular housing such that translation of the lower tubular housing with respect to the upper tubular housing causes pivoting of the forward link and the truck beam with respect to one another, thereby tilting and/or raising a wheel of the wheel assembly with respect to the upper tubular housing.
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