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1. 发明授权

US11541997B2 Systems and methods for improved rotor assembly for use with a stator 有权
公开(公告)号：US11541997B2
公开(公告)日：2023-01-03
申请号：US16744897
申请日：2020-01-16
申请人： Maglev Aero Inc.
发明人： Ian Morris Randall
IPC分类号： B64C27/20 , H02K1/2786 , H02N15/00 , F01D5/02 , B64C27/10 , B64C27/72 , B64D27/24 , H02K1/17 , H02K1/2793 , B64C29/00 , B64C13/50 , H02K21/22 , B64C27/32 , H02K1/18 , H02K11/21 , B64C27/473 , H02K21/24 , B64C13/26 , B64D35/02 , B64D35/04 , H02K1/28 , H02K16/00 , B64C27/68 , B64C27/00 , B64C29/02 , B64C27/14 , B64C27/80 , B64C39/02 , B64D35/06
摘要： Systems and methods relate to a vertical takeoff and landing (VTOL) platform that can include a stator and a rotor magnetically levitated by the stator. The rotor and stator can be annular, such that the rotor rotates about a rotational axis. The stator can include magnets that provide guidance, levitation, and drive forces to drive the rotor, as well as to control operation of rotor blades of the rotor that can be independently rotated to specific pitch angles to control at least one of lift, pitch, roll, or yaw of the VTOL platform. Various controllers can be used to enable independent and redundant control of components of the VTOL platform.

2. 发明申请

US20220269291A1 FAULT TOLERANT AIRCRAFT FLIGHT CONTROL SYSTEM AND AIRCRAFT PREFERABLY HAVING SUCH AN AIRCRAFT FLIGHT CONTROL SYSTEM 有权
公开(公告)号：US20220269291A1
公开(公告)日：2022-08-25
申请号：US17670852
申请日：2022-02-14
申请人： Lilium eAircraft GmbH
发明人： João Filipe TELES FERREIRA , Gabriel Oliveira RIBAS
IPC分类号： G05D1/10 , B64C9/04 , B64C13/50 , B64C13/26 , B64D27/02 , B64D31/02 , B64C39/12 , H04L12/40 , H04L69/18
摘要： A flight control system for an aircraft comprises a flight control computer system connected via a bus system with a plurality of bus nodes, which each are configured to at least one of controlling an associated aircraft device based on command messages received from the flight control computer system via the bus system and sending information messages to the flight control computer system via the bus system. The bus system is a redundant bus system comprising plural independent bus sub-systems, wherein each bus node is configured to communicate with the flight control computer system via two different bus sub-systems, wherein each bus node further is configured to communicate with the flight control computer system on basis of an associated predetermined bus communication protocol via a first bus sub-system and on basis of an associated predetermined bus communication protocol via a second bus sub-system.

3. 发明授权

US11199248B2 Compact linear to rotary actuator 有权
公开(公告)号：US11199248B2
公开(公告)日：2021-12-14
申请号：US16399557
申请日：2019-04-30
申请人： Woodward, Inc.
发明人： Craig D. Mawle , Mark A. Spickard , Barry T. Brinks
IPC分类号： F16H21/34 , F16H21/22 , B64C13/26 , F15B15/06 , F16C7/02
摘要： The subject matter of this specification can be embodied in, among other things, a linear-to-rotary apparatus that includes a linear actuator having an actuator housing including a piston chamber, a piston shaft disposed in the piston chamber, and a rotor apparatus. The rotor apparatus includes a rotary joint defining a rotational axis, a rotor arm extending radially from the rotary joint and configured to at least partially pivot about the rotary joint, and a torque linkage pivotably connected to the rotor arm. The torque linkage is also attached to an end of the piston shaft of the piston at a pivot connection joint, where the pivot connection joint defines a pivot axis that is substantially perpendicular to the translation axis of the piston shaft.

4. 发明授权

US11059579B2 Universal flying terrain vehicle 有权
公开(公告)号：US11059579B2
公开(公告)日：2021-07-13
申请号：US16473363
申请日：2017-12-26
申请人： Moshe Levy
发明人： Moshe Levy
IPC分类号： B64C37/00 , B64C13/04 , B60D99/00 , B60F5/02 , B64C7/00 , B64C13/16 , B64C13/26 , B64C13/50 , B64C25/00 , B64C25/10 , B64C27/00 , B64C31/036 , B64D27/02
摘要： A universal aerial platform (11, 41) supports lift elements (13, 14), thrusters (15), landing gear (21, 22) and a fuel supply (16) and has a coupling mechanism (17) external to the aerial platform for coupling to a terrain vehicle (20) so as to convert any suitably adapted terrain vehicle to a flying vehicle (10, 40). The terrain vehicle forms the cockpit of the flying vehicle. The terrain vehicle (20) includes flight controls that are automatically coupled to the airplane structure either wirelessly or by wires when the terrain vehicle is coupled thereto.

5. 发明授权

US10372149B2 Detent alignment mechanism assembly 有权
公开(公告)号：US10372149B2
公开(公告)日：2019-08-06
申请号：US15209186
申请日：2016-07-13
申请人： Hamilton Sundstrand Corporation
发明人： Cory M. Crandall-Seibert , Jeffrey Paul Jacobs
IPC分类号： G05G5/03 , B64C13/14 , B64C13/26 , B64C13/04 , B64C13/10 , G05G1/04 , G05G5/00 , G05G5/06
摘要： A detent alignment mechanism assembly is provided and includes a shaft, a lock mechanism configured to selectively occupy an unlocked position at which the shaft is movable and a locked position at which the shaft is immovable, a detent mechanism coupled to the shaft and formed to define detent positions for the shaft to assume and move between and a detent alignment mechanism configured to provide to an operator of the shaft feedback and assistance corresponding to assumptions of the detent positions by the shaft during movements thereof by the operator.

6. 发明申请

US20150274280A1 AIR VEHICLE, ACTUATOR ASSEMBLY AND ASSOCIATED METHOD OF MANUFACTURE 有权
标题翻译：空中车辆，执行机构总成及相关制造方法
公开(公告)号：US20150274280A1
公开(公告)日：2015-10-01
申请号：US14242088
申请日：2014-04-01
申请人： The Boeing Company
发明人： James Joseph Sheahan, JR. , Donald V. Drouin, JR.
IPC分类号： B64C13/34 , B64C13/26 , B64C9/00
CPC分类号： B64C13/34 , B64C9/00 , B64C9/02 , B64C13/26 , B64C13/38 , B64C13/40 , B64C13/50 , Y02T50/32 , Y02T50/44 , Y10T29/49826
摘要： An air vehicle, an actuator assembly and a method of manufacture are provided in order to incorporate the actuator assembly within the outer mold line of the air vehicle. In regards to an air vehicle, the air vehicle includes a primary structure and a movable structure configured to be controllably moved relative to the primary structure. The air vehicle also includes an actuator assembly configured to cause the movable structure to be positioned relative to the primary structure. The actuator assembly includes an actuator housing and an actuation mechanism. The actuation mechanism is at least partially disposed within the actuator housing and is configured to provide for relative movement between the primary structure and the movable structure. At least a portion of the actuator assembly is built into at least one of the primary structure and the movable structure so as to be within an outer mold line of the air vehicle.
摘要翻译：提供了一种机动车辆，致动器组件和制造方法，以将致动器组件并入到空中交通工具的外部模具线内。关于空中交通工具，该空中交通工具包括主结构和可相对于主结构可控制地移动的可移动结构。空中车辆还包括构造成使可移动结构相对于主结构定位的致动器组件。致动器组件包括致动器壳体和致动机构。所述致动机构至少部分地布置在所述致动器壳体内，并且构造成提供所述主结构和所述可移动结构之间的相对运动。致动器组件的至少一部分内置在主结构和可移动结构中的至少一个中，以便在空中车辆的外部模具线内。

7. 发明申请

US20140175217A1 FLAP DEPLOYING DEVICE AND AIRCRAFT 有权
标题翻译： FLAP部署设备和飞机
公开(公告)号：US20140175217A1
公开(公告)日：2014-06-26
申请号：US14105814
申请日：2013-12-13
申请人： MITSUBISHI AIRCRAFT CORPORATION
发明人： Kenya ISHIHARA , Zenta SUGAWARA
IPC分类号： B64C13/34 , B64C13/26
CPC分类号： B64C9/16 , B64C9/22 , B64C13/28
摘要： The flap deploying device deploys a flap provided at a leading edge or a trailing edge of a main wing of the aircraft, the deploying device including: a drive source; a moving mechanism with a moving body advancing and retracting by power of the drive source; a carriage mechanism that carries advancing and retracting motion of the moving body to the flap so as to deploy the flap between a retracted position and a deployed position; and a rail that guides the carriage mechanism. Since the moving mechanism is arranged lateral to the rail in the wingspan direction of the main wing, the dimension of the wing in a thickness direction can be reduced at least by a dimension corresponding to the moving mechanism. Therefore, the wing can be made thinner, or the projecting height of a flap track fearing can be reduced.
摘要翻译：翼片展开装置部署设置在飞行器的主翼的前缘或后缘处的翼片，所述展开装置包括：驱动源; 移动机构，其具有通过所述驱动源的动力而前进和后退的移动体; 托架机构，其将所述移动体的前进和后退运动运送到所述翼片，以便在缩回位置和展开位置之间展开所述翼片; 以及引导滑架机构的导轨。由于移动机构沿着主翼的翼展方向布置在轨道的横向上，所以机翼在厚度方向上的尺寸可以至少减小对应于移动机构的尺寸。因此，机翼可以做得更薄，或者可以减少襟翼的突出高度。

8. 发明申请

US20130320151A1 ROTARY ACTUATED HIGH LIFT GAPPED AILERON 有权
标题翻译：旋转启动高升降飞机
公开(公告)号：US20130320151A1
公开(公告)日：2013-12-05
申请号：US13482537
申请日：2012-05-29
申请人： Jan A. Kordel , Seiya Sakurai
发明人： Jan A. Kordel , Seiya Sakurai
IPC分类号： B64C3/50 , B64C13/26 , B64C9/00
CPC分类号： B64C1/10 , B64C9/16 , B64C9/18 , B64C2009/143
摘要： A rotary actuated high lift gapped aileron system and method are presented. A high lift gapped aileron couples to an airfoil at a hinge line and changes a camber of the airfoil. A rotary actuator coupled to the high lift gapped aileron produces a rotary motion of the high lift gapped aileron in response to an actuation command. A droop panel positioned over the hinge line enhances lift of the high lift gapped aileron. A cove lip door positioned under the hinge line provides an airflow over the high lift gapped aileron. A deployment linkage mechanism coupled to the high lift gapped aileron positions the droop panel and the cove lip door in response to the rotary motion.
摘要翻译：提出了一种旋转驱动的高电梯间隙副翼系统和方法。一个高升降机的副翼在铰链上与翼型相连，并改变翼型的弯度。耦合到高电梯间隙副翼的旋转致动器响应于致动指令产生高升力带隙副翼的旋转运动。定位在铰链线上方的垂直面板增强了升降机间隙副翼的升力。位于铰链线下方的海湾唇门在高升高间隙副翼上提供气流。联接到高提升间隙副翼的展开联动机构响应于旋转运动而定位下垂面板和小湾唇门。

9. 发明申请

US20050151028A1 Apparatus for driving and adjusting flaps hinged to an aircraft 有权
标题翻译：用于驱动和调整翼片的装置铰接到飞机上
公开(公告)号：US20050151028A1
公开(公告)日：2005-07-14
申请号：US11021723
申请日：2004-12-22
申请人： Ulrich Pohl , Carsten Thomas , Christian Lulla , Martin Kloenne
发明人： Ulrich Pohl , Carsten Thomas , Christian Lulla , Martin Kloenne
IPC分类号： B64C13/26 , B64D45/00 , B64C3/58
CPC分类号： B64D45/0005 , B64C13/26 , B64D2045/001
摘要： Flaps, for example leading edge flaps and/or trailing edge flaps of an aircraft wing, are driven and adjusted by respective drive units. Drive shafts of neighboring flaps are coupled to each other by a differential gear. The differential gear is thus coupled to a main drive shaft which is driven by a main drive unit. Additionally, the differential gear is coupled to a secondary drive unit. The main drive power and the secondary drive power and thus the respective flap motions are super-imposable on each other, which permits operating the flaps independently of each other or in synchronism with each other.
摘要翻译：翼片，例如飞机机翼的前缘翼片和/或后缘翼片由相应的驱动单元驱动和调节。相邻翼片的驱动轴通过差速齿轮相互连接。因此，差速齿轮联接到由主驱动单元驱动的主驱动轴。此外，差速齿轮联接到辅助驱动单元。主驱动功率和二次驱动功率以及因此相应的皮瓣运动彼此是超重的，这允许彼此独立地彼此操作或彼此同步地操作翼片。

10. 发明申请

US20220090657A1 COMPACT LINEAR TO ROTARY ACTUATOR 有权
公开(公告)号：US20220090657A1
公开(公告)日：2022-03-24
申请号：US17457560
申请日：2021-12-03
申请人： Woodward, Inc.
发明人： Craig D. Mawle , Mark A. Spickard , Barry T. Brinks
IPC分类号： F16H21/34 , B64C13/26 , F16H21/22 , F16C7/02 , F15B15/06
摘要： The subject matter of this specification can be embodied in, among other things, a linear-to-rotary apparatus that includes a linear actuator having an actuator housing including a piston chamber, a piston shaft disposed in the piston chamber, and a rotor apparatus. The rotor apparatus includes a rotary joint defining a rotational axis, a rotor arm extending radially from the rotary joint and configured to at least partially pivot about the rotary joint, and a torque linkage pivotably connected to the rotor arm. The torque linkage is also attached to an end of the piston shaft of the piston at a pivot connection joint, where the pivot connection joint defines a pivot axis that is substantially perpendicular to the translation axis of the piston shaft.

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