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公开(公告)号：US20240190558A1
公开(公告)日：2024-06-13
申请号：US18583261
申请日：2024-02-21
摘要： A folding trailing arm landing gear assembly having a main fitting configured to couple to a hinge positioned at a proximal end; a swing arm rotatably coupled at a proximal end to a distal end of the main fitting; a shock coupled at a distal end to a distal end of the swing arm; a bellcrank coupled at a distal end to a proximal end of the shock, and coupled at a proximal end to the main fitting; and a wheel coupled to the swing arm.
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公开(公告)号：US11932379B2
公开(公告)日：2024-03-19
申请号：US17990577
申请日：2022-11-18
摘要： A folding trailing arm landing gear assembly having a main fitting configured to couple to a hinge positioned at a proximal end; a swing arm rotatably coupled at a proximal end to a distal end of the main fitting; a shock coupled at a distal end to a distal end of the swing arm; a bellcrank coupled at a distal end to a proximal end of the shock, and coupled at a proximal end to the main fitting; and a wheel coupled to the swing arm.
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公开(公告)号：US20190185146A1
公开(公告)日：2019-06-20
申请号：US15841757
申请日：2017-12-14
申请人： Goodrich Corporation
发明人： William E. Luce
CPC分类号： B64C25/26 , B64C25/12 , B64C25/20 , B64C2025/006 , B64C2025/008 , B64C2025/125
摘要： A non jamming shrink latch is provided and may comprise a cradle, a first rocker arm, a first inboard pivot, and a first outboard pivot, wherein the first inboard pivot is coupled to the first rocker arm at a first end and the first outboard pivot is coupled to the first rocker arm at a second end opposite the first end, and wherein the cradle is coupled to the first outboard pivot. In various embodiments, a non jamming shrink latch may further comprise a second rocker arm coupled to the cradle at a second outboard pivot and a second inboard pivot coupled to the second rocker arm opposite the second outboard pivot.
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公开(公告)号：US20180037314A1
公开(公告)日：2018-02-08
申请号：US15661115
申请日：2017-07-27
摘要： An aircraft include a landing gear is disclosed. The landing gear comprises a main strut and an inboard stay assembly connected to the aircraft fuselage such that landing gear loads can be transferred from the inboard stay assembly into the fuselage. The landing gear also comprises a sidestay connected to the wing such that landing gear loads can be transferred from the sidestay into the wing and a link assembly connected to the aircraft such that landing gear loads can be transferred via the link assembly into the aircraft. The landing gear is arranged such that, in use, when the landing gear is extended, substantially all the landing gear loads are transferred from the landing gear to the aircraft via one or more of the inboard stay assembly, the sidestay and the link assembly.
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公开(公告)号：US09868534B2
公开(公告)日：2018-01-16
申请号：US14973098
申请日：2015-12-17
发明人： Nobuhide Hara , Tadahiko Suzuta
IPC分类号： B64D13/00 , B60T5/00 , B64C1/14 , B64C7/00 , B64C25/00 , B64C25/16 , F16D65/847 , B64C25/36 , B64C25/12 , B64C25/34
CPC分类号： B64D13/006 , B60T5/00 , B64C1/14 , B64C7/00 , B64C25/001 , B64C25/12 , B64C25/16 , B64C25/34 , B64C25/36 , F16D65/847
摘要： An aircraft includes: a fairing which covers a lower part of a fuselage having a main landing gear bay (MLG bay), and defines a ventilation cavity communicating with the MLG bay between the fairing and the fuselage; and a heat removal system which removes heat generated from the MLG inside the MLG bay to the outside of the MLG bay by suctioning/discharging air through an inlet port and an outlet port leading from the ventilation cavity or the MLG bay to external air. The fairing defines a wheel opening through which a wheel of the MLG enters and exits, and defines a ventilation port, which functions as one of the inlet and outlet ports, between the fairing and an outer peripheral part of the wheel exposed from the wheel opening to the lower side of the MLG bay when the MLG is retracted.
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公开(公告)号：US20170327207A1
公开(公告)日：2017-11-16
申请号：US15154906
申请日：2016-05-13
申请人： Luis Sierra
发明人： Luis Sierra
CPC分类号： B64C25/20 , B60G3/20 , B60G2204/47 , B60G2300/04 , B62D63/061 , B62D63/062 , B64C25/12
摘要： A retractable wheel assembly includes arm assemblies, wheels, a retraction arm, and a threaded shaft. The arm assemblies are hingedly attached to a lower frame of a utility vehicle. Each arm assembly comprises a first arm, a second arm, and a third arm hingedly linked there between. Each wheel is connected to the third arm of each arm assembly. The retraction arm is connected to the second arm, and a threaded shaft. The threaded shaft is configured to be actuated rearwardly where the retraction arm is rearwardly pulled causing the second arm to unfold the arm assembly outwardly and deploy the wheels and for motion of the utility vehicle. Then, the threaded shaft is configured to be actuated forwardly where the retraction arm is pushed forward causing the second arm to fold the arm assembly inwardly and fold the wheels and when the utility vehicle is positioned at rest.
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公开(公告)号：US20160137294A1
公开(公告)日：2016-05-19
申请号：US14936579
申请日：2015-11-09
发明人： Stuart John LACY , Indrakaji GURUNG
CPC分类号： B64C25/10 , B64C25/001 , B64C25/12 , B64C2025/125 , B64D2045/008 , G01L5/0052
摘要： An aircraft assembly (10) having an indicator (20) configured to provide an indication of when an element of the aircraft assembly has received a predetermined load or traveled to a predetermined position.
摘要翻译： 具有指示器（20）的飞行器组件（10）被配置为提供何时飞行器组件的元件已经接收到预定负载或行进到预定位置的指示。
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公开(公告)号：US09205917B2
公开(公告)日：2015-12-08
申请号：US13287177
申请日：2011-11-02
申请人： James P. Acks , Dennis W. Martin
发明人： James P. Acks , Dennis W. Martin
CPC分类号： B64C25/12 , B64C25/20 , B64C25/34 , B64C2025/125
摘要： A side articulating main landing gear assembly for an aircraft which includes a wheel axle fitting oriented in a horizontal plane when the landing gear assembly is in an extended condition deployed from a landing gear bay of the aircraft, a shock absorber adapted to stroke between an extended state and a compressed state upon landing the aircraft, a first linkage for maintaining a tire supported on the wheel axle fitting in a substantially vertical plane as the shock absorber strokes between the extended state and the compressed state, and a second linkage for maintaining the wheel axle fitting in the horizontal plane as the shock absorber strokes between the extended state and the compressed state. The first and second linkages are adapted and configured to minimize lateral tire scuffing during shock absorber stroking.
摘要翻译： 一种用于飞行器的侧面关节式主起落架组件，其包括当起落架组件处于从飞行器的起落架舱部分展开的延伸状态时定向在水平面中的轮轴配件，适于在延伸状态之间行进的减震器 状态和在飞机着陆时的压缩状态，第一联动装置，用于当缓冲器在伸出状态和压缩状态之间行进时，将支撑在车轮轴上的轮胎装配在基本垂直的平面中;以及第二连杆，用于保持车轮 当缓冲器在伸展状态和压缩状态之间进行冲击时，在水平面中的轴配合。 第一和第二连杆被适配和构造成使减震器冲击期间的侧面轮胎磨损最小化。
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公开(公告)号：US20150203192A1
公开(公告)日：2015-07-23
申请号：US13875972
申请日：2013-05-02
申请人： Goodrich Corporation
摘要： A landing gear actuation system comprising a motive force system, such as an actuator and/or a piston to move the landing gear from a first position to a second position is disclosed herein. The landing gear actuation system may also comprise a spring system configured to counterbalance the weight of the landing gear and/or assist the motive force system in moving the landing gear from a first position to a second position. The landing gear actuation system may further comprise a camming mechanism to distribute the direction and/or location of the force applied to the landing gear.
摘要翻译： 本文公开了一种起落架致动系统，其包括诸如致动器和/或活塞的运动系统，以将起落架从第一位置移动到第二位置。 起落架致动系统还可以包括弹簧系统，该弹簧系统构造成抵抗起落架的重量和/或协助动力系统将起落架从第一位置移动到第二位置。 起落架致动系统还可包括凸轮机构，以分配施加到起落架的力的方向和/或位置。
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公开(公告)号：US20150041586A1
公开(公告)日：2015-02-12
申请号：US14322217
申请日：2014-07-02
发明人： Keiji Nakashima , Shinichi Hada , Takashi Sugimoto
IPC分类号： B64C25/00
CPC分类号： B64C25/001 , B64C25/12 , B64C2025/125
摘要： To provide a landing gear storage compartment of an aircraft which can protect accessories installed around a landing gear by blocking jet blast and dust etc. while suppressing the weight and the cost. A landing gear storage compartment 3 of an aircraft 1 includes: a storage bay 31 that stores a landing gear 2 for use in takeoff and landing; and a shielding wall 32, inside of which a wheel assembly 21 of the landing gear 2 stored in the storage bay 31 is arranged, and whose lower side, through which the wheel assembly enters and exits, and whose upper side are opened. An upper opening 32C of the shielding wall 32 is covered with a partition wall 13 that separates a cabin 12 located above the storage bay 31, and the storage bay 31.
摘要翻译： 提供飞机的起落架储存室，其可以通过阻止喷气和灰尘等来保护安装在起落架周围的附件，同时抑制重量和成本。 飞机1的起落架储存室3包括：存储起落架2，用于起飞和降落; 和屏蔽壁32，其内部布置有存储在储存架31中的起落架2的轮组件21，并且其下部侧通过该车轮组件进出，并且其上侧打开。 遮蔽壁32的上部开口32C被分隔开位于储存室31上方的舱室12和储存室31的分隔壁13覆盖。
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