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81. 发明授权

US10604266B2 Electrical assist for aircraft 有权
公开(公告)号：US10604266B2
公开(公告)日：2020-03-31
申请号：US15432230
申请日：2017-02-14
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies Inc.
发明人： Douglas M. Roever , Robert Zeller
IPC分类号： B64D27/02 , B64D27/24 , B64D35/08 , B64D31/10 , B64C27/08 , B64D27/16 , B64D29/00
摘要： Methods and systems to electrically assist an internal combustion engine of an aircraft may be provided. A first bladed rotor may be rotated by a first internal combustion engine. Electricity may be generated from a first motor generator by rotating a first shaft of the first motor generator with the first internal combustion engine. In response to a predetermined event, such as an engine failure, mechanical power may be generated from the first motor generator instead of electricity. The mechanical power may be transferred to the first bladed rotor. The mechanical power may be generated by applying electricity to the first motor generator. The electricity applied is received from a second motor generator, where the electricity received from the second motor generator is generated by rotating a second shaft of the second motor generator with a second internal combustion engine that powers a second bladed rotor.

82. 发明申请

US20190291883A1 FLYING VEHICLE EMERGENCY PROCEDURES 审中-公开
公开(公告)号：US20190291883A1
公开(公告)日：2019-09-26
申请号：US15926841
申请日：2018-03-20
申请人： Hoversurf, Inc.
发明人： Aleksandr ATAMANOV
IPC分类号： B64D31/10 , B64C27/00 , B64C27/08 , B64C27/12 , B64C27/57 , B64D31/12 , B64D45/00
摘要： A system and method for operating a flying vehicle that includes a vehicle having a plurality of motors, each of said motors coupled to a rotor and a motor controller; at least one sensor coupled to either the plurality of motors or the rotors, said sensor operative to sense an operating characteristic of the rotor or motor based on a predetermined setpoint; a processor, said processor coupled to a memory and to said motor control circuitry and said sensors, said processor operable to; receive a signal from the sensor; determine a predetermined operational procedure in response to the signal, and alter the operating characteristics of one or more motors, wherein the signal indicates a failure condition and the operational procedure effects mitigation of the failure condition by removing power to certain motors and increasing power to others.

83. 发明申请

US20190176977A1 PROPELLER IMPACT DETECTION AND FORCE REDUCTION 审中-公开
公开(公告)号：US20190176977A1
公开(公告)日：2019-06-13
申请号：US16249645
申请日：2019-01-16
申请人： Kitty Hawk Corporation
发明人： Christopher Scott Saunders
IPC分类号： B64C27/00 , B64D45/00 , B64D17/80 , B64C27/08 , B64D31/10
摘要： A commanded control signal is compared against an adaptive control signal in order to detect a rotor strike by a rotor included in an aircraft, wherein the adaptive control signal is associated with controlling the rotor and the adaptive control signal varies based at least in part on the commanded control signal and state information associated with the rotor. In response to detecting the rotor strike, a control signal to the rotor is adjusted in order to reduce a striking force associated with the rotor.

84. 发明授权

US10227138B2 Asymmetry-proof multi-engine aircraft 有权
公开(公告)号：US10227138B2
公开(公告)日：2019-03-12
申请号：US15061425
申请日：2016-03-04
申请人： Embraer S.A.
发明人： Ierko De Magalhães Gomes
IPC分类号： B64D31/10 , B64D41/00 , B64D45/00 , B64D27/12 , B64D27/24 , B64D27/02
摘要： An aircraft compensates for asymmetry of engine failure by drawing part of the energy produced by the still-operating engine to generate thrust at the tip of the opposite wing. For example, the left engine drives its own thrust on the left wing, but a portion of the energy the left engine produces is delivered at a propeller at the tip of right wing. Similarly, the right engine drives its own thrust on the right wing, but a portion of the energy the right engine produces is delivered at a propeller at the tip of the left wing. In this way, every pair of engines and opposite tip thrust generators are intrinsically balanced. In the event of one engine failure, no yaw moment will be noticed.

85. 发明授权

US10099795B2 Precision operator for an aircraft autothrottle or autopilot system 有权
公开(公告)号：US10099795B2
公开(公告)日：2018-10-16
申请号：US15554642
申请日：2016-08-01
申请人： INNOVATIVE SOLUTIONS & SUPPORT, INC.
发明人： Geoffrey S. M. Hedrick
IPC分类号： B64D31/04 , B64C13/10 , B64D31/14 , B64D31/12 , B64D31/10
摘要： An autothrottle system for an aircraft includes a motor, actuator assembly, and position sensor operatively connected between the motor and a moving portion of the actuator assembly. An electronic controller is configured to control the motor to move the actuator assembly to actuator positions based at least on position information from the position sensor to move the throttle lever to lever positions. The actuator assembly includes a bearing assembly having a plurality of bearings to contact a surface of a shaft for converting rotational movement of the shaft into linear motion of the bearing assembly along the shaft. The actuator assembly further includes a shuttle arm having at one end a mounting surface to attach to the bearing assembly and at the other end a linkage arm operatively coupled to the attachment end of the lever.

86. 发明申请

US20180105280A1 MULTI-ENGINE AIRCRAFT THRUST BALANCING 审中-公开
公开(公告)号：US20180105280A1
公开(公告)日：2018-04-19
申请号：US15846664
申请日：2017-12-19
申请人： United Technologies Corporation
发明人： Philip A. Schmidt
IPC分类号： B64D31/12 , G05D1/00 , B64D31/10 , F02C9/42 , B64C13/16 , B64D31/06
摘要： An aircraft controller includes a memory for storing instructions. The instructions are operable to cause the controller to perform a thrust balancing method and ensure a balanced thrust output from the aircraft.

87. 发明申请

US20180002027A1 Aircraft having a Fault Tolerant Distributed Propulsion System 审中-公开
公开(公告)号：US20180002027A1
公开(公告)日：2018-01-04
申请号：US15200273
申请日：2016-07-01
申请人： Bell Helicopter Textron Inc.
发明人： John Richard McCullough , Paul K. Oldroyd
IPC分类号： B64D31/10 , B64D17/02 , B64D1/22 , B64D25/12 , B64C29/02
CPC分类号： B64D31/10 , B64C29/02 , B64D1/22 , B64D17/02 , B64D25/12
摘要： In some embodiment, an aircraft includes a flying frame having an airframe, a distributed propulsion system attached to the airframe, the distributed propulsion system including a plurality of propulsion assemblies and a flight control system operably associated with the distributed propulsion system. The flying frame has a vertical takeoff and landing mode and a forward flight mode. The flight control system is operable to independently control the propulsion assemblies. The flight control system is also operable to detect faults in individual propulsion assemblies and to perform corrective action responsive to detected faults at a distributed propulsion system level.

88. 发明授权

US6102330A Emergency multiengine aircraft system for lateral control using differential thrust control of wing engines 失效
标题翻译：用于侧翼控制的紧急多发发射机系统使用翼型发动机的差分推力控制
公开(公告)号：US6102330A
公开(公告)日：2000-08-15
申请号：US905777
申请日：1997-07-29
申请人： John J. Burken , Frank W. Burcham, Jr. , John Bull
发明人： John J. Burken , Frank W. Burcham, Jr. , John Bull
IPC分类号： B64D31/10 , B64C19/00
CPC分类号： B64D31/10 , G05D1/0808
摘要： An emergency flight control system is disclosed for lateral control using only differential engine thrust modulation of multiengine aircraft having at least two engines laterally displaced to the left and right from the axis of the aircraft in response to a heading angle command .psi..sub.c to be tracked. By continually sensing the heading angle .psi. of the aircraft and computing a heading error signal .psi..sub.e as a function of the difference between the heading angle command .psi..sub.c and the sensed heading angle .psi., a track control signal is developed with compensation as a function of sensed bank angle .PHI., bank angle rate .phi., or roll rate p, yaw rate .tau., and true velocity to produce an aircraft thrust control signal ATC.sub..psi.(L,R). The thrust control signal is differentially applied to the left and right engines with equal amplitude and opposite sign such that a negative sign is applied to the control signal on the side of the aircraft to which a turn is required to reduce the error signal until the heading feedback reduces the error to zero.
摘要翻译：公开了一种用于横向控制的紧急飞行控制系统，其仅使用具有响应于待跟踪的航向角度指令psi c的至少两个从飞行器的轴线向左和向右偏移的发动机的多发机飞行器的差分发动机推力调制。通过连续地感测飞行器的航向角度psi，并计算航向误差信号psi e作为航向角度指令psi c与感测到的航向角度psi之间的差的函数，轨道控制信号被开发，补偿作为感测的倾斜角度PHI，倾斜角速率phi或滚动速率p，横摆角速度tau和真实速度以产生飞行器推力控制信号ATC psi（L，R）。推力控制信号以相同的幅度和相反的符号差分地施加到左右引擎，使得负号被施加到需要转弯的飞机侧面上的控制信号以减少误差信号直到航向反馈将误差降低到零。

89. 发明授权

US12072717B2 System and method for controlling differential thrust of a blown lift aircraft 有权
公开(公告)号：US12072717B2
公开(公告)日：2024-08-27
申请号：US18494416
申请日：2023-10-25
申请人： Electra Aero, Inc.
发明人： Robert John Hansman, Jr. , Christopher B. Courtin , Oliver Masefield
IPC分类号： G05D1/00 , B64C13/16 , B64D31/10
CPC分类号： G05D1/0825 , B64C13/16 , B64D31/10
摘要： An aircraft may include a tail having a rudder and a pair of wings. The pair of wings may include at least one flap and at least one roll control device. The aircraft may also include at least two thrust-producing devices. The aircraft may also include a differential thrust control system including a computing device having at least one processor. The at least one processer may be configured to control an attitude of the aircraft by selectively operating the at least two thrust-producing devices, the rudder, and the at least one roll control device based at least in part on a plurality of conditions provided by a plurality of sensors on the aircraft and a selected mode setting of a mode control panel. The computing device may be communicatively coupled to the at least two thrust-producing devices, the rudder, and the at least one roll control device.

90. 发明授权

US12017784B2 In-flight stabilization of an aircraft 有权
公开(公告)号：US12017784B2
公开(公告)日：2024-06-25
申请号：US17373842
申请日：2021-07-13
申请人： BETA AIR, LLC
发明人： Lochie Ferrier , Alexander Hoekje List
IPC分类号： B64D31/10 , B64C15/00 , B64C29/00 , B64D27/24 , B64D45/00
CPC分类号： B64D31/10 , B64C15/00 , B64C29/0016 , B64D27/24 , B64D2045/0085
摘要： A system for in-flight stabilization including a plurality of flight components mechanically coupled to an aircraft, wherein the plurality of flight components includes a first flight component and a second flight component opposing the first flight component. The system further comprises a sensor mechanically coupled to the aircraft, wherein the sensor is configured to detect a failure event of a first flight component. The system comprises a vehicle controller communicatively connected to the sensor and is configured to receive the failure datum of the first flight component from the sensor, generate a failure notification configured to indicate that the vehicle controller received the failure datum from the sensor, and initiate an automatic response as a function of the failure datum. Initiating the automatic response further includes determining an autorotation inducement action for the second flight component to perform and commanding the second flight component to perform the autorotation inducement action.

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