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公开(公告)号：US11912400B2
公开(公告)日：2024-02-27
申请号：US17953861
申请日：2022-09-27
发明人： Frazer Wilson , Declan Franks
摘要： A variable length stay for an aircraft landing gear is disclosed having first and second sets of struts lying on different longitudinal axes that enable the stay to extend and contract by movement of the struts parallel to their axes. The stay may be locked in its extended and retracted configurations thus providing downlock and uplock functions for the landing gear. The struts of the stay may have an open and easy to inspect structure, have low friction kinematics, and do not need to telescope within each other or lie on a single common axis.
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公开(公告)号：US20240051659A1
公开(公告)日：2024-02-15
申请号：US18373690
申请日：2023-09-27
申请人： JETZERO, INC.
发明人： Ewald Schuster , Jennifer Whitlock , Joshua B. Long , Cristina Donastorg , Brendan Kennelly , Mark A. Page
摘要： Systems and methods for mechanically rotating an aircraft about its center-of-gravity (CG) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive pitch angle for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.
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公开(公告)号：US20180001999A1
公开(公告)日：2018-01-04
申请号：US15198611
申请日：2016-06-30
发明人： Mark A. Page
IPC分类号： B64C25/22
CPC分类号： B64C25/001 , B64C25/14 , B64C2025/008
摘要： Systems and methods for mechanically rotating an aircraft about its center-of-gravity (CG) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive angle of attack for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.
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公开(公告)号：US09840321B2
公开(公告)日：2017-12-12
申请号：US14966478
申请日：2015-12-11
发明人： Guillaume Gallant , Herve Biennes
摘要： In order to assist fitting of doors to the landing gear housing and adjusting their position, an aircraft nose is provided comprising a connecting frame between the landing gear housing and the outer skin of the fuselage, the connecting frame extending around an opening in the outer skin and comprising a skirt bearing against the outer skin of the fuselage and attached thereto, the skirt defining a passage for landing gear which is configured to be closed off by doors when the landing gear are in a closed position, and supporting members extending between the fuselage and the doors.
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5.发明授权公开(公告)号：US09828086B2
公开(公告)日：2017-11-28
申请号：US14623972
申请日：2015-02-17
发明人： Brian Cook , John Louis , Thomas Van de Ven , Robert M. Vieito
CPC分类号： B64C25/14 , B64C25/001 , B64C25/34 , B64C2025/003
摘要： Nose landing gear arrangements for aircrafts, aircrafts including such nose landing gear arrangements, and methods for making such nose landing gear arrangements are provided. In one example, a nose landing gear arrangement includes a wheel assembly and a main strut. The main strut is operatively coupled to the wheel assembly and is configured to move between an extended position and a retracted position. The main strut in the extended position extends outside of the fuselage substantially along a generally vertical plane to position the wheel assembly for takeoff and/or landing of the aircraft. The main strut in the retracted position is disposed inside the fuselage. A flexible sheet is disposed adjacent to the main strut and is configured such that when the main strut is in the extended position the flexible sheet is positioned substantially around the main strut.
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6.发明授权Aircraft capable of takeoff/landing via the fuselage thereof, and takeoff/landing system for the aircraft 有权能够通过机身起飞/着陆的飞机，以及飞机起飞/着陆系统公开(公告)号：US09302768B2
公开(公告)日：2016-04-05
申请号：US14415438
申请日：2012-07-17
申请人： Donggyu Yang
发明人： Donggyu Yang
摘要： The aircraft capable of takeoff/landing via the fuselage thereof and the takeoff/landing system of the aircraft according to the present invention are configured such that multiple takeoff/landing rollers are arranged in a sliding direction such that the aircraft fuselage having a landing surface formed at the bottom thereof can safely land and slide in a sliding direction, thus enabling the aircraft fuselage to contact a running surface and takeoff/land without separate landing gear. Thus, not only can the weight of the aircraft be reduced, but the fuel consumption of the aircraft can be reduced as well, the useful space in the aircraft can be broadened, the length of the runway can be shortened due to the frictional force generated by the takeoff/landing device, and the safety during the takeoff/landing of the aircraft can be improved.
摘要翻译： 根据本发明的能够通过其机身起飞/着陆的飞行器和飞行器的起飞/着陆系统被构造成使得多个起飞/着陆滚轮沿滑动方向布置，使得具有着陆面的飞行器机身形成 在其底部可以安全地滑动并滑动方向，从而使飞机机身能够接触运行的表面，起飞/着陆，而无需单独的起落架。 因此，不仅可以减少飞机的重量，还可以减少飞机的燃料消耗，从而可以扩大飞机的有用空间，由于产生的摩擦力可以缩短跑道的长度 通过起飞/着陆装置，可以提高飞机起飞/着陆期间的安全性。
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公开(公告)号：US09302767B2
公开(公告)日：2016-04-05
申请号：US13674303
申请日：2012-11-12
发明人： Brian G. Cook , John Louis , Thomas Van de Ven , Robert M. Vieito
CPC分类号： B64C25/001 , B64C25/14 , B64C25/16 , B64C2025/003 , B64C2025/006 , Y10T29/49826
摘要： A nose landing gear arrangement for an aircraft and a method of assembling the nose landing gear arrangement are disclosed herein. The nose landing gear arrangement includes, but is not limited to, a wheel assembly, a shock strut extending upwards from the wheel assembly towards a fuselage of the aircraft, and a torque arm assembly coupled to the wheel assembly and to the shock strut. The torque arm assembly is configured to transmit torque to the wheel assembly. The torque arm assembly is disposed forward of the shock strut with respect to a direction of travel of the aircraft.
摘要翻译： 本文公开了一种用于飞行器的前起落架装置和组装前起落架装置的方法。 前起落架装置包括但不限于轮组件，从车轮组件向上延伸到飞行器的机身的冲击支柱，以及联接到车轮组件和冲击支柱的扭矩臂组件。 扭矩臂组件构造成将扭矩传递到车轮组件。 扭矩臂组件相对于飞行器的行进方向设置在冲击支柱的前方。
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公开(公告)号：US09284034B2
公开(公告)日：2016-03-15
申请号：US14154661
申请日：2014-01-14
申请人： William M. Otto
发明人： William M. Otto
IPC分类号： B64C3/38 , B64C5/10 , B64C9/00 , B64C13/00 , B64C1/00 , B64C1/10 , B64C25/02 , B64C25/10 , B64C25/18 , B64C25/22 , B64C25/14 , B64C1/06 , B64C3/18 , B64C3/26 , B64C3/58 , B64C5/02 , B64C5/16 , B64C9/02 , B64C9/16 , B64C9/20 , B64C13/30 , B64C25/12 , B64C25/20 , B64D33/10 , B64D37/04 , F02B37/00
CPC分类号： B64C25/20 , B64C1/00 , B64C1/065 , B64C1/069 , B64C1/10 , B64C3/185 , B64C3/26 , B64C3/58 , B64C5/02 , B64C5/16 , B64C9/02 , B64C9/16 , B64C9/20 , B64C13/30 , B64C25/02 , B64C25/10 , B64C25/12 , B64C25/14 , B64C25/18 , B64C25/22 , B64C2025/125 , B64D33/10 , B64D37/04 , F02B37/001 , Y02T50/32 , Y02T50/44
摘要： A wing flap control system on a wing comprising at least two control plates having an opening sized to accommodate a drive shaft, a drive shaft that engages each of the openings in each of the plurality of plates, a sprocket rotatively affixed the drive shaft with the drive shaft penetrating the other control plate, at least two idler sprockets between the control plates, a chain wrapped around the sprocket and idler sprockets, a support arm rotatively coupled to the chain by a chain shoe and to a foreflap, a link arm rotatively coupled to the support arm and to a flap, where movement of the drive shaft causes the foreflap and flap to extend and retract to increase or decrease the surface area of the wing.
摘要翻译： 一种机翼上的机翼翼片控制系统，包括至少两个控制板，该控制板的开口尺寸适于容纳驱动轴;驱动轴，其接合多个板中的每一个中的每个开口;链轮，其将驱动轴与 驱动轴穿过另一个控制板，控制板之间至少有两个空转链轮，围绕链轮和惰轮链轮缠绕的链条，支撑臂通过链条可转动地联接到链条和前翼，连杆臂可旋转地联接 到支撑臂和翼片，其中驱动轴的运动导致前翼和翼片延伸和缩回以增加或减小机翼的表面积。
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公开(公告)号：US08905352B2
公开(公告)日：2014-12-09
申请号：US13710577
申请日：2012-12-11
摘要： An aircraft nose structure includes a fuselage and a pressuretight bulkhead fixed at its periphery to the fuselage and transversely dividing the fuselage into a pressurized upper zone and an unpressurized lower zone for accommodating retractable nose landing gear. The pressuretight bulkhead includes a floor of the pressurized upper zone, and a substantially flat rear panel extending between a rear edge of the floor and the fuselage. The floor and the rear panel are fixed laterally to the fuselage. The fuselage includes an exterior wall and reinforcing transverse frames to which the exterior wall is fixed. In line with the pressuretight bulkhead, at least some of the transverse reinforcing frames extend along the outline of the pressurized upper zone and constitute members that reinforce the pressuretight bulkhead.
摘要翻译： 飞机鼻部结构包括机身和固定在其机身周围的机身的压紧隔板，并将机身横向分为加压上部区域和未加压下部区域，用于容纳可伸缩的起落架。 压紧的舱壁包括加压的上部区域的底板，以及在地板的后边缘和机身之间延伸的基本平坦的后面板。 地板和后面板侧向固定在机身上。 机身包括外壁和外壁固定到其上的加强横向框架。 与压紧隔板一致，至少一些横向加强框架沿着加压的上部区域的轮廓延伸并且构成加强压力密封舱壁的构件。
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公开(公告)号：US20140197275A1
公开(公告)日：2014-07-17
申请号：US14154353
申请日：2014-01-14
申请人： William M. OTTO
发明人： William M. OTTO
CPC分类号： B64C25/20 , B64C1/00 , B64C1/065 , B64C1/069 , B64C1/10 , B64C3/185 , B64C3/26 , B64C3/58 , B64C5/02 , B64C5/16 , B64C9/02 , B64C9/16 , B64C9/20 , B64C13/30 , B64C25/02 , B64C25/10 , B64C25/12 , B64C25/14 , B64C25/18 , B64C25/22 , B64C2025/125 , B64D33/10 , B64D37/04 , F02B37/001 , Y02T50/32 , Y02T50/44
摘要： A main landing gear system for an aircraft including a truss element including a front portion joined to a rear portion, a first support unit and second support unit affixed to the truss at the junction of the first portion and the second portion on opposing sides of the truss, a first actuator and a second actuator rotatively affixed to respective first support unit and second support unit and to a respective first wheel and second wheel, a first trailing link and second trailing link each coupled to the respective first wheel and second wheel, a first extension plate and second extension plate each rotatively coupled to the respective first trailing link and second trailing link and to a side of the truss, a first plate locking unit and second plate locking unit rotatively affixed to an end of the respective first extension plate or second extension plate and to a side of the truss, where actuation of the actuator causes the extension plates to move up or down with respect to the truss raising and lowering the wheels.
摘要翻译： 一种用于飞行器的主起落架系统，其包括桁架元件，该桁架元件包括接合到后部的前部，第一支撑单元和第二支撑单元，该第一支撑单元和第二支撑单元在第一部分和第二部分的接合处固定到桁架 桁架，第一致动器和第二致动器，其旋转地固定到相应的第一支撑单元和第二支撑单元以及相应的第一轮和第二轮，每个联接到相应的第一轮和第二轮的第一拖链和第二拖链， 第一延伸板和第二延伸板，每个旋转地联接到相应的第一牵引连杆和第二牵引连杆以及桁架的一侧，第一板锁定单元和第二板锁定单元可旋转地固定到相应的第一延伸板的端部，或 第二延伸板和桁架的一侧，致动器致动器使得延伸板相对于tru上下移动 ss提升和降低车轮。
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