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公开(公告)号：US11801932B2
公开(公告)日：2023-10-31
申请号：US16730108
申请日：2019-12-30
申请人： JETZERO, INC.
发明人： Ewald Schuster , Jennifer Whitlock , Joshua B Long , Cristina Donastorg , Brendan Kennelly , Mark A. Page
CPC分类号： B64C25/22 , B64C25/001 , B64C25/04 , B64C25/26 , B64C25/40 , B64F5/60 , 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 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：US11731760B2
公开(公告)日：2023-08-22
申请号：US16605001
申请日：2018-04-09
申请人： FLY-R
发明人： François Varigas
CPC分类号： B64C29/0033 , B64C3/10 , B64C25/04 , B64C27/28 , B64C39/068 , B64U30/20
摘要： The aircraft (10) comprises a fuselage (11) and a rhombohedral wing structure (12) comprising front wings (13, 14) mounted on a front wing-root support (17) and rear wings (15, 16) mounted on a rear wing-root support (18).
At least two wings (13, 14) support an engine (24, 26) provided with a propeller (25, 27).
The rear end of the fuselage supports an engine (21) provided with a propeller (22).
The aircraft comprises means (28 to 35) for tilting said engines, the rotary shaft of each of the propellers being tilted between an orientation parallel to the main axis of the fuselage and an orientation perpendicular to the main axis of the fuselage and to an axis extending through the ends of the front wings.-
公开(公告)号：US10011351B2
公开(公告)日：2018-07-03
申请号：US15200244
申请日：2016-07-01
IPC分类号： G05D1/00 , G05D3/00 , G06F7/00 , G06F17/00 , B64C29/02 , G05D1/10 , G08G5/00 , B64D1/22 , B64D1/10 , B64D17/02
CPC分类号： B64C29/02 , B64C11/28 , B64C25/04 , B64C25/10 , B64C27/30 , B64C37/00 , B64C39/024 , B64C39/04 , B64D1/10 , B64D1/22 , B64D17/025 , B64D17/80 , G08G5/0034 , G08G5/0039 , G08G5/0052 , G08G5/0056 , G08G5/0065 , G08G5/0069 , G08G5/025
摘要： In some embodiments, a passenger pod assembly transportation system includes a transportation services provider computing system and a plurality of flying frame flight control systems, wherein the system is configured to receive, at the transportation services provider computing system, a request for transportation of a passenger pod assembly having a current location and a destination; upload a flight plan to a flight control system of a flying frame including an airframe and a propulsion system; dispatch the flying frame to the current location of the passenger pod assembly; couple the flying frame to the passenger pod assembly at the current location of the passenger pod assembly; transport the passenger pod assembly by air from the current location of the passenger pod assembly to the destination of the passenger pod assembly; and decouple the passenger pod assembly from the flying frame at the destination of the passenger pod assembly.
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4.发明申请公开(公告)号：US20180162514A1
公开(公告)日：2018-06-14
申请号：US15840942
申请日：2017-12-13
发明人： Daniel BELLET , Guillaume GALLANT
CPC分类号： B64C3/32 , B64C25/04 , B64C25/10 , B64C25/34 , B64D27/12 , B64D27/18 , B64D27/26 , B64D29/02 , B64D29/06 , B64D2027/264 , Y02T50/44
摘要： An aircraft comprising at least one power plant linked to an airfoil by a power plant support structure comprising a primary structure housed in an aerodynamic fairing. The power plant is formed overhanging behind the airfoil, mostly or wholly above the upper surface of the airfoil. The aircraft comprises a main landing gear comprising at least one landing gear element linked to the airfoil of the aircraft by a support structure. The primary structure and the support structure of the landing gear element are formed by a common structure. The use of such a common structure allows a general optimization of the architecture of the aircraft by virtue of the synergies between the positioning of the power plant, the primary structure of its strut, and the support structure of the main landing gear.
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公开(公告)号：US20170073078A1
公开(公告)日：2017-03-16
申请号：US15359965
申请日：2016-11-23
申请人： The Boeing Company
CPC分类号： B64D27/26 , B64C3/32 , B64C25/04 , B64C25/34 , B64D27/02 , B64D29/02 , B64D29/04 , B64D2027/005 , B64D2027/262 , B64D2027/264 , Y02T50/66
摘要： An aircraft includes an engine mounted to a wing by a first support, such as a strut, configured to secure the engine to the wing in a position above the wing. A second support, secured to a fuselage portion of the aircraft, is defined by a bridge structure configured to separately and independently secure the engine to the fuselage. The engine is thus secured by the first support directly to the aircraft wing, and via the second support, in concert with the first, to a portion of an aircraft fuselage spaced laterally of the engine-to-wing attachment. In one embodiment the bridge structure, which extends between the engine and fuselage, may be bowed upwardly so as to define a convex curvature when viewed along the longitudinal axis of the aircraft. Such a curvature may, inter alia, optimize aerodynamic spacing of the bridge from the wing to minimize undesirable shock waves.
摘要翻译： 飞机包括通过诸如支柱的第一支撑件安装到机翼的发动机，其构造成将发动机固定在机翼上方的机翼上。 固定在飞行器的机身部分上的第二支撑件由桥结构限定，桥结构构造成将发动机单独地并独立地固定在机身上。 因此，发动机通过第一支撑件直接固定到飞行器机翼，并且经由第二支撑件与第一支撑件一体地固定到发动机到翼的附件侧向间隔的飞行器机身的一部分。 在一个实施例中，在发动机和机身之间延伸的桥结构可以向上弯曲，以便当沿着飞行器的纵向轴线观察时限定凸曲率。 这样的曲率可以特别地优化桥梁与机翼的空气动力学间隔，以最小化不期望的冲击波。
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6.发明授权Transformation method of hybrid transportation vehicle for ground and air, and hybrid transportation vehicle itself 有权地面和空中混合运输车辆的转型方法，以及混合动力运输车辆本身公开(公告)号：US09555681B2
公开(公告)日：2017-01-31
申请号：US14241239
申请日：2012-08-22
IPC分类号： B60F5/02 , B64C3/56 , B64C37/00 , B60F5/00 , B64C3/38 , B64C3/54 , B64C25/04 , B64C25/54 , B64C25/00
CPC分类号： B60F5/02 , B60F5/003 , B64C3/385 , B64C3/54 , B64C3/56 , B64C25/04 , B64C25/54 , B64C37/00 , B64C2025/003 , Y02T50/14
摘要： Transformation method of hybrid transportation vehicle for ground and air includes the following transformation and reciprocal steps: Tilting the compensation cover (7) on. Expansion of both whole wings (1) from the transportation vehicle longitudinal position around two vertical axes (2) into the flying position. Expansion of rear parts of wings (1) from the top front parts of wings (1) into the spread flying position by tilting the rear of each wing (1) around a horizontal axis (3). The take-off and landing tilting of wings (1) by an angle of attack alpha=0 to 40° of the wings onset. Front wheels track (5) is reduced by axially shifting the front wheels (5) towards the fuselage. Furthermore, a corresponding hybrid transportation vehicle for ground and air is described which contains reciprocal transformation mechanisms for transformation from a sterling double or four-track automobile into a sterling aircraft for take-off and landing on the ground or water, and vice versa.
摘要翻译： 地面和空中混合动力运输车辆的变换方法包括以下转换和相互的步骤：倾斜补偿盖（7）。 将整个机翼（1）从围绕两个垂直轴（2）的运输车辆纵向位置扩展到飞行位置。 通过使每个机翼（1）的后部围绕水平轴线（3）倾斜，翼部（1）的后部部分从翼部（1）的顶部前部部分扩展到扩展的飞行位置。 机翼的起飞和着陆倾斜（1）以机翼的角度α= 0到40°开始。 前轮轨道（5）通过将前轮（5）轴向移动朝向机身而减小。 此外，描述了用于地面和空气的相应的混合运输车辆，其包含用于从英镑双轨或四轨车转换成用于起飞和降落在地面或水上的英制飞机的相互转换机制，反之亦然。
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公开(公告)号：US20160304186A1
公开(公告)日：2016-10-20
申请号：US15133758
申请日：2016-04-20
摘要： An aircraft comprising a fuselage which has a central part with a cross section of constant geometry which comprises a floor. The floor comprises two lateral portions which are fixed respectively to two opposite lateral edges of the fuselage and which enclose a central portion to which they are fixed. One of the lateral floor portions is fixed to the central portion so as to allow a relative lateral movement between the two portions in the event of a modification in pressure inside the fuselage. The cross section thus deforms homogeneously when the fuselage is pressurized and the floor is not involved in maintaining the shape of the fuselage.
摘要翻译： 一种包括机身的飞机，该机身具有包括地板的具有恒定几何形状的横截面的中心部分。 该地板包括分别固定在机身的两个相对的侧边缘上的两个侧面部分，它们围绕着固定在其上的中心部分。 在侧面底板部分中的一个固定到中心部分，以便在机身内的压力改变的情况下允许两个部分之间的相对横向移动。 当机身加压时，横截面因而变形均匀，而且地板不参与保持机身的形状。
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公开(公告)号：US20150090837A1
公开(公告)日：2015-04-02
申请号：US14489607
申请日：2014-09-18
CPC分类号： B64C25/04 , B64C25/06 , B64C25/52 , B64C27/04 , B64C2025/325
摘要： A bracket (24) for connecting a traverse (20) of a landing gear to a cabin of a helicopter. A landing gear retainer (5) is fixed around the traverse (20) coaxially to the longitudinal direction of the traverse (20) and at least one cabin clamp mount (7) is fixed to the cabin. The landing gear retainer (5) is in between the cabin and upper and lower pendulum bolts (12, 13) and upper and lower pendulum bearings (18, 19). A pendulum (9) is in longitudinal direction of the traverse (20) hinged to the landing gear retainer (5). The invention is further related to an application of such brackets (24).
摘要翻译： 一种用于将起落架的横动（20）连接到直升机的舱室的支架（24）。 起落架保持器（5）围绕横向（20）固定在横向（20）的纵向方向上，并且至少一个客舱夹具安装件（7）固定到机舱。 起落架保持架（5）位于机舱与上下摆钟螺栓（12,13）和上下摆轴承（18,19）之间。 摆锤（9）在与起落架保持器（5）铰接的横动（20）的纵向方向上。 本发明还涉及这种支架（24）的应用。
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9.发明申请TRANSFORMATION METHOD OF HYBRID TRANSPORTATION VEHICLE FOR GROUND AND AIR, AND HYBRID TRANSPORTATION VEHICLE ITSELF 有权地面和空中混合运输车辆的转换方法及混合动力车辆系统公开(公告)号：US20150028150A1
公开(公告)日：2015-01-29
申请号：US14241239
申请日：2012-08-22
申请人： Stefan Klein
发明人： Stefan Klein
CPC分类号： B60F5/02 , B60F5/003 , B64C3/385 , B64C3/54 , B64C3/56 , B64C25/04 , B64C25/54 , B64C37/00 , B64C2025/003 , Y02T50/14
摘要： Transformation method of hybrid transportation vehicle for ground and air includes the following transformation and reciprocal steps: Tilting the compensation cover (7) on. Expansion of both whole wings (1) from the transportation vehicle longitudinal position around two vertical axes (2) into the flying position. Expansion of rear parts of wings (1) from the top front parts of wings (1) into the spread flying position by tilting the rear of each wing (1) around a horizontal axis (3). The take-off and landing tilting of wings (1) by an angle of attack alpha=0 to 40° of the wings onset. Front wheels track (5) is reduced by axially shifting the front wheels (5) towards the fuselage. Furthermore, a corresponding hybrid transportation vehicle for ground and air is described which contains reciprocal transformation mechanisms for transformation from a sterling double or four-track automobile into a sterling aircraft for take-off and landing on the ground or water, and vice versa.
摘要翻译： 地面和空中混合动力运输车辆的变换方法包括以下转换和相互的步骤：倾斜补偿盖（7）。 将整个机翼（1）从围绕两个垂直轴（2）的运输车辆纵向位置扩展到飞行位置。 通过使每个机翼（1）的后部围绕水平轴线（3）倾斜，翼部（1）的后部部分从翼部（1）的顶部前部部分扩展到扩展的飞行位置。 机翼的起飞和着陆倾斜（1）以机翼的角度α= 0到40°开始。 前轮轨道（5）通过将前轮（5）轴向移动朝向机身而减小。 此外，描述了用于地面和空气的相应的混合运输车辆，其包含用于从英镑双轨或四轨车转换成用于起飞和降落在地面或水上的英制飞机的相互转换机制，反之亦然。
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公开(公告)号：US08915470B2
公开(公告)日：2014-12-23
申请号：US13710569
申请日：2012-12-11
摘要： An aircraft nose structure includes a fuselage, a floor for a pressurized space and a nose landing gear bay arranged under the floor, on the opposite side to the space. The bay includes walls that form a pressure barrier, of which there are two lateral panels mechanically secured to the floor by load-reacting members, an upper panel adjacent to the floor and extending between the lateral panels, and a rear panel extending between the upper panel and the fuselage.
摘要翻译： 飞机鼻梁结构包括机身，加压空间的地板和布置在地板下面的与起落架相对的一个前起落架舱。 海湾包括形成压力屏障的壁，其中有两个侧面板通过负载反作用构件机械地固定到地板上，邻近地板并在侧板之间延伸的上板和在上板之间延伸的后板 面板和机身。
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