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公开(公告)号：US20240336349A1
公开(公告)日：2024-10-10
申请号：US18628183
申请日：2024-04-05
申请人： Joby Aero, Inc.
IPC分类号： B64C13/26 , B64C39/00 , B64C39/10 , G05D1/495 , G05D109/22
CPC分类号： B64C13/26 , G05D1/495 , B64C39/029 , B64C39/10 , G05D2109/22
摘要： A robust control method for an oblique flying wing aircraft includes computing an angular velocity error between a reference angular velocity and an actual angular velocity and computing a moment command with an angular velocity controller based at least in part on the angular velocity error. The angular velocity controller decouples two or more of a yaw rate axis, a pitch rate axis, and a roll rate axis of the asymmetric aircraft for the moment command.
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公开(公告)号：US20240209926A1
公开(公告)日：2024-06-27
申请号：US18600330
申请日：2024-03-08
申请人： Woodward, Inc.
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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公开(公告)号：US20240134387A1
公开(公告)日：2024-04-25
申请号：US18535604
申请日：2023-12-11
发明人： Jong-Yeob Shin , Gi-Yun Chung , Lakmal Kaviratna
摘要： Flight control systems, flight control laws, and aircraft are provided. An flight control system includes an input configured to receive a pitch rate command, a processor operative to receive the pitch angle command, to calculate a pitch angle saturation limit, to compare the sum of the pitch rate command, the scaled pitch rate, and the scaled pitch angle to the pitch angle saturation limit, to convert the pitch rate command system to the pitch angle command system in response to the sum exceeding the pitch angle saturation limit value to limit the pilot pitch-up pitch rate command, and to couple the pitch rate command to an aircraft control surface for the failure case of one of control surface, and the aircraft control surface configured to adjust an aircraft control surface setting in response to the pitch rate command and/or pitch angle command to protect an aircraft from being in stall condition.
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公开(公告)号：US11814169B2
公开(公告)日：2023-11-14
申请号：US17053318
申请日：2019-05-10
发明人： Sawyer Fuller , Shyamnath Gollakota , Johannes James , Vikram Subramaniam Iyer , Yogesh M. Chukewad
IPC分类号： B64C39/02 , H02S10/40 , H02S30/10 , H02S40/30 , B64C13/20 , B64C13/26 , B64C33/02 , B64U50/31 , H10N30/20 , H02M3/156 , B64U10/40 , B64U50/19 , B64U50/34
CPC分类号： B64C39/024 , B64C13/20 , B64C13/26 , B64C33/025 , B64U50/31 , H02S10/40 , H02S30/10 , H02S40/30 , H10N30/2045 , B64C33/02 , B64U10/40 , B64U50/19 , B64U50/34 , B64U2201/10 , H02M3/156
摘要： An aerial robot system may include an aerial robot having an airframe, a piezo actuator, a wing connected to the piezo actuator, and a photovoltaic cell. The system may further include a laser source configured to emit a laser beam oriented toward the photovoltaic cell for conversion by the photovoltaic cell into electrical energy. The aerial robot may further include a boost converter connected to the photovoltaic cell and configured to raise a voltage level of the electrical energy, and a signal generator connected to the boost converter and configured to generate an alternating signal. The piezo actuator is connected to the signal generator to move according to the alternating signal to cause the wing to move in a flapping motion to generate aerodynamic force that moves the robot. Methods for manufacturing aerial robots and corresponding electronics are also disclosed herein.
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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.
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公开(公告)号：US20220269291A1
公开(公告)日：2022-08-25
申请号：US17670852
申请日：2022-02-14
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.
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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.
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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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.
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公开(公告)号：US10372149B2
公开(公告)日：2019-08-06
申请号：US15209186
申请日：2016-07-13
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.
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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
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。
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