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公开(公告)号：US12084170B2
公开(公告)日：2024-09-10
申请号：US18179115
申请日：2023-03-06
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： Fraser Wilson , Jeremy Bedarrides , Vladimir Platagea
CPC classification number: B64C25/405 , B64C25/58
Abstract: An aircraft landing gear is disclosed including a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear.
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公开(公告)号：US11820184B2
公开(公告)日：2023-11-21
申请号：US16936016
申请日：2020-07-22
Applicant: SUBARU CORPORATION
Inventor： Daisuke Hirabayashi , Keisuke Tajiri
Abstract: A land-and-air vehicle configured to switch between a ground traveling mode and an aerial flight mode incudes a body, a wing, a wheel, a suspension, and a lock mechanism. The wing is attached to the body. The wheel is provided on a lower side of the body. The suspension is configured to support the body via the wheel on ground, and to contract due to self-weight of the land-and-air vehicle. The lock mechanism is configured to limit expansion of the suspension from a state in which the suspension has contracted due to the self-weight.
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公开(公告)号：US20230202647A1
公开(公告)日：2023-06-29
申请号：US18179115
申请日：2023-03-06
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： Fraser WILSON , Jeremy BEDARRIDES , Vladimir PLATAGEA
IPC: B64C25/40
CPC classification number: B64C25/405 , B64C25/58
Abstract: An aircraft landing gear is disclosed including a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear.
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公开(公告)号：US20180265184A1
公开(公告)日：2018-09-20
申请号：US15917148
申请日：2018-03-09
Applicant: Safran Landing Systems UK LTD
Inventor： Radu Chiritoiu , Daniele Parente
Abstract: An aircraft landing gear assembly including a structural load bearing beam arranged, in use, to react torsional loads applied to it. The beam has a tubular box section main body having four straight sidewall portions, adjacent sidewall portions being orthogonal to one another and connected by rounded corner portions. Each corner portion has a radius of between 10% and 40% of the width and/or height of the tubular box section main body.
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公开(公告)号：US10053210B2
公开(公告)日：2018-08-21
申请号：US15045328
申请日：2016-02-17
Applicant: MESSIER-BUGATTI-DOWTY
Inventor： Carlo Necci
Abstract: An aircraft undercarriage comprising a telescopic linear rod (0, 0′, 0″) comprising first and second sliding rod portions. The undercarriage further comprises: a first permanent magnet set (1a, 1a′, 1a″) fastened to the first rod portion (1, 1′, 1″); and a second permanent magnet set (2a, 2a′, 2a″) fastened to the second rod portion (2, 2′, 2″); the first and second permanent magnet sets (1a, 1a′, 1a″, 2a, 2a′, 2a″) generating a magnetic repulsion force between the first rod portion (1, 1′, 1″) and the second rod portion (2, 2′, 2″) and maintaining a first annular space (E1) between the first rod portion and the second rod portion.
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Patent Agency Ranking
公开(公告)号：US20180170531A1
公开(公告)日：2018-06-21
申请号：US15833549
申请日：2017-12-06
Applicant: Safran Landing Systems UK LTD
Inventor： Valerijan Cokonaj , Laura Collett
IPC: B64C25/58 , G01C19/5776
CPC classification number: B64C25/58 , B64C25/02 , B64D45/0005 , B64D2045/0085 , G01C19/5776
Abstract: An aircraft assembly having a first region, a second region spaced from the first region by a flexible region, and a deflection sensor. The first region has greater positional stability than the second region such that the second region deflects further from its default position than the first region during in-use loads. The deflection sensor includes a first gyroscope at the first region to generate a first signal representing rotation of the first region about one or more orthogonal axes, and a second gyroscope at the second region to generate a second signal representing rotation of the second region about the one or more axes. The second gyroscope is synchronised in time with the first. A controller subtracts one of the first and second signals from the other to obtain a differential signal representing deflection of the second region relative to the first due to flexing of the flexible region.
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公开(公告)号：US20170297706A1
公开(公告)日：2017-10-19
申请号：US15338802
申请日：2016-10-31
Applicant: Ewatt Technology Co., Ltd.
Inventor： Guocheng ZHAO , Wei LUO
CPC classification number: B64C39/024 , B64C1/00 , B64C1/06 , B64C3/00 , B64C5/02 , B64C25/58 , B64C39/028 , B64C2201/021 , B64C2201/042 , B64C2201/08 , B64C2201/104 , B64C2201/146 , B64C2201/162 , B64C2201/165 , B64C2201/187
Abstract: The invention discloses a hand-launched unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The hand-launched unmanned aerial vehicle comprises a body, a tail, at least one power source and a lens bin, wherein the body comprises a middle section, a first side section and a second side section; two sides of the middle section are respectively detachably connected with the first side section and the second side section correspondingly; the tail is fixed to the middle section; the power source is fixed to the middle section; and the lens bin is fixed to the middle section and provided with a flexible cushion. The invention overcomes the technical defects in the prior art that the body maintenance cost of the hand-launched unmanned aerial vehicle is high and the lens bin is very likely to be damaged due to collision between the lens bin of the hand-launched unmanned aerial vehicle and the ground.
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公开(公告)号：US20170297684A1
公开(公告)日：2017-10-19
申请号：US15637645
申请日：2017-06-29
Applicant: THE BOEING COMPANY
Inventor： Terrence S. BIRCHETTE , Akif O. BOLUKBASI
Abstract: An active landing gear damping system and method for decelerating a vehicle during a terrain impact event, such as an aircraft landing or crash. The system monitors aircraft state data and terrain information to predict an impact of the vehicle with the terrain. The system can then determine a target damper force for each landing gear of the vehicle and a predicted damper velocity at the time of impact. Each landing gear can include an adjustable damper valve, wherein adjustment of the damper valves varies the damping coefficient of the respective dampers. The system can adjust valves of the respective dampers to provide the target force based on the predicted damper velocity. After an impact begins, the system can continuously monitor and adjust the valve to maintain the target force.
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公开(公告)号：US09732817B2
公开(公告)日：2017-08-15
申请号：US14882140
申请日：2015-10-13
Applicant: Goodrich Corporation
Inventor： Richard A. Himmelmann
IPC: H02P3/06 , F16F6/00 , B64C25/58 , B64C25/34 , B64C25/50 , H02K1/22 , H02K5/24 , H02K7/00 , H02K49/02 , H02K49/04
CPC classification number: F16F6/005 , B64C25/34 , B64C25/505 , B64C25/58 , F16F15/03 , H02K1/22 , H02K5/24 , H02K7/003 , H02K49/02 , H02K49/043 , H02P3/06
Abstract: The present disclosure provides an axial engagement-controlled variable damper comprising a rotor assembly coupled to a rotor shaft and disposed about an axis of rotation and a stator, coaxially aligned with the rotor assembly. The axial engagement-controlled variable damper may further comprise a flux sleeve, axially movable relative to the rotor assembly between at least a first position and a second position. The flux sleeve may comprise a circumferential flange portion disposed radially between the rotor assembly and the stator, and may be configured to alter magnetic coupling between the stator and the rotor assembly in response being moved axially. The axial-engagement controlled variable damper may be configured to generate a first drag torque in response to the flux sleeve being in the first position and a second drag torque in response to the flux sleeve being in the second position.
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公开(公告)号：US20170203833A1
公开(公告)日：2017-07-20
申请号：US15407001
申请日：2017-01-16
Applicant: Safran Landing Systems UK Limited
Inventor： Robert Kyle Schmidt
Abstract: An aircraft landing gear assembly includes a structural member coupled to another part by a joint including engagement formations or a relatively high friction coating arranged such that the joint inhibits pivotal movement of the structural member when the structural member is compressively loaded in an axial manner.
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