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1. 发明公开

US20240043115A1 PROPELLER IMPACT DETECTION AND FORCE REDUCTION 审中-公开
公开(公告)号：US20240043115A1
公开(公告)日：2024-02-08
申请号：US18381994
申请日：2023-10-19
申请人： Kitty Hawk Corporation
发明人： Christopher Scott Saunders
IPC分类号： B64C27/00 , B64C27/08 , B64D31/10 , B64D45/00 , B64D17/80
CPC分类号： B64C27/006 , B64C27/08 , B64D31/10 , B64D45/00 , B64D17/80 , B64D2045/0085
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.

2. 发明公开

US20240034478A1 MULTI-DRIVE UNIT POWERPLANT FOR AN AIRCRAFT 审中-公开
公开(公告)号：US20240034478A1
公开(公告)日：2024-02-01
申请号：US17874981
申请日：2022-07-27
申请人： Pratt & Whitney Canada Corp.
发明人： Roja Tabar , Ann Marie Unnippillil
IPC分类号： B64D31/10 , B64D27/12 , B64D27/24 , B64D35/08
CPC分类号： B64D31/10 , B64D27/12 , B64D27/24 , B64D35/08 , B64D2027/026
摘要： A method is provided for operating an aircraft system. During this operating method, a plurality of drive units are provided that include a thermal engine drive unit and an electric machine drive unit. A mechanical load is powered using a first of the drive units. The first of the drive units includes a first rotating structure. A parameter of the first rotating structure is monitored. A failure of the first of the drive units is detected based on the monitored parameter. A switch is made from the first of the drive units to a second of the drive units to power the mechanical load where the failure of the first of the drive units is detected.

3. 发明授权

US11846953B2 System and method for controlling differential thrust of a blown lift aircraft 有权
公开(公告)号：US11846953B2
公开(公告)日：2023-12-19
申请号：US18114828
申请日：2023-02-27
申请人： Electra Aero, Inc.
发明人： Robert John Hansman, Jr. , Christopher B. Courtin , Oliver Masefield
IPC分类号： G05D1/00 , G05D1/08 , 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.

4. 发明授权

US11643219B1 Reconfigurable propulsion mechanisms of a multirotor aerial vehicle 有权
公开(公告)号：US11643219B1
公开(公告)日：2023-05-09
申请号：US16914973
申请日：2020-06-29
申请人： Amazon Technologies, Inc.
发明人： Michael Szmuk , Marco Antonio De Barros Ceze , Max Maria Jacques Opgenoord
IPC分类号： B64D31/10 , B64C39/02 , B64C29/02 , B64C39/06
CPC分类号： B64D31/10 , B64C29/02 , B64C39/024 , B64C39/062 , B64C2201/027 , B64C2201/108 , B64C2201/141
摘要： This disclosure describes example reconfigurable propulsion mechanisms, example multi-rotor aerial vehicle apparatuses, and methods that may be used to alter the yaw torque polarity produced by one or more propulsion mechanisms in response to a detected loss of thrust produced by another propulsion mechanism of the aerial vehicle. For example, each reconfigurable propulsion mechanism may be configured to move between a normal operating position and a reconfigured operating position. When a reconfigurable propulsion mechanism is in a normal operating position, the yaw torque has a first polarity, such as clockwise. In comparison, when the same reconfigurable propulsion mechanism is in the reconfigured operating position, the yaw torque polarity produced by the propulsion mechanism is reversed and has a second polarity, such as counter-clockwise. Reconfiguration may be done to recover an aerial vehicle from a degraded operational state, for example resulting from a motor-out event, to a non-degraded operational state.

5. 发明申请

US20190047715A1 Precision Operator for an Aircraft Autothrottle or Autopilot System with Engine Performance Adjust 审中-公开
公开(公告)号：US20190047715A1
公开(公告)日：2019-02-14
申请号：US16159348
申请日：2018-10-12
申请人： Geoffrey S.M. HEDRICK
发明人： Geoffrey S.M. HEDRICK
IPC分类号： B64D31/10 , B64D43/00 , F02C9/54 , F02C7/26 , G08G5/00 , G08G5/04 , G05D1/08 , G05D1/00 , G05D3/12
CPC分类号： B64D31/10 , B64D43/00 , F02C7/26 , F02C9/26 , F02C9/54 , F05D2220/323 , F05D2270/051 , F05D2270/093 , F05D2270/12 , F05D2270/13 , F05D2270/20 , F05D2270/303 , G05D1/0072 , G05D1/0816 , G05D3/12 , G08G5/0008 , G08G5/04
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.

6. 发明申请

US20180079519A1 Precision Operator for an Aircraft Autothrottle or Autopilot System 审中-公开
公开(公告)号：US20180079519A1
公开(公告)日：2018-03-22
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： B64D31/14 , B64D31/12 , B64D31/10 , B64C13/10 , B64D31/04
CPC分类号： B64D31/02 , B64C13/10 , B64D31/04 , B64D31/06 , B64D31/08 , B64D31/10 , B64D31/12 , B64D31/14 , B64D45/00 , G07C5/0816
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.

7. 发明申请

US20160214731A1 MULTI-ENGINE AIRCRAFT THRUST BALANCING 审中-公开
标题翻译：多发动机飞机平衡
公开(公告)号：US20160214731A1
公开(公告)日：2016-07-28
申请号：US14913449
申请日：2014-08-27
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Philip A. Schmidt
IPC分类号： B64D31/12 , B64C13/16
CPC分类号： B64D31/12 , B64C13/16 , B64D31/06 , B64D31/10 , F02C9/42 , G05D1/0005 , G05D1/0072 , Y02T50/44
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.
摘要翻译：飞机控制器包括用于存储指令的存储器。指令可操作以使控制器执行推力平衡方法并确保来自飞行器的平衡的推力输出。

8. 发明授权

US08798810B2 Energy protecting device for aircraft 有权
标题翻译：飞机能量保护装置
公开(公告)号：US08798810B2
公开(公告)日：2014-08-05
申请号：US12066599
申请日：2006-09-12
申请人： Franck Delaplace , Didier Ronceray , Jean Muller
发明人： Franck Delaplace , Didier Ronceray , Jean Muller
IPC分类号： G01C23/00 , B64D31/08 , B64D31/06 , B64D31/10 , G05D1/00 , B64D27/02
CPC分类号： B64D31/08 , B64D27/02 , B64D31/06 , B64D31/10 , G05D1/0072
摘要： An energy protecting device for three and four-engined aircraft includes a detecting unit configured to detect failure of each engine. A control unit is configured to provide a protective function by controlling maximum thrust of each engine. A triggering unit is configured to monitor a plurality of parameters and trigger the control unit to provide maximum thrust at predetermined conditions of the monitored parameters. An inhibiting unit is linked to the triggering unit and is configured to inhibit the protective function, when at least one of the engine on the wings of the aircraft has failed. The control unit is also configured to control the engines that have not failed to minimize thrust imbalance.
摘要翻译：用于三发射机和四发射机的能量保护装置包括：检测单元，被配置为检测每个发动机的故障。控制单元被配置为通过控制每个发动机的最大推力来提供保护功能。触发单元被配置为监视多个参数并且触发控制单元以在所监视的参数的预定条件下提供最大推力。禁止单元连接到触发单元并且被配置为当飞行器的机翼上的发动机中的至少一个发生故障时禁止保护功能。控制单元还被配置为控制未失效的发动机以最小化推力不平衡。

9. 发明申请

US20080208398A1 Energy Protecting Device for Aircraft 有权
标题翻译：飞机能量保护装置
公开(公告)号：US20080208398A1
公开(公告)日：2008-08-28
申请号：US12066599
申请日：2006-09-12
申请人： Franck Delaplace , Didier Ronceray , Jean Muller
发明人： Franck Delaplace , Didier Ronceray , Jean Muller
IPC分类号： B64D31/10
CPC分类号： B64D31/08 , B64D27/02 , B64D31/06 , B64D31/10 , G05D1/0072
摘要： The invention concerns a device (1) comprising control means (3) for activating a protective function which consists in automatically controlling the engines (M1 to M4) so that they supply maximum power when the triggering conditions are fulfilled, and inhibiting means (8) for inhibiting the protective function solely when all the engines which are arranged on a common wing of the aircraft have simultaneously broken down.
摘要翻译：本发明涉及一种装置（1），包括用于启动保护功能的控制装置（3），该保护功能包括自动控制发动机（M 1至M 4），使得它们在触发条件满足时提供最大功率;以及禁止装置 8）用于仅当布置在飞机的共同翼上的所有发动机已经同时分解时才抑制保护功能。

10. 发明授权

US6126111A Emergency flight control system using one engine and fuel transfer 失效
标题翻译：应急飞行控制系统采用一台发动机和燃油传输
公开(公告)号：US6126111A
公开(公告)日：2000-10-03
申请号：US112067
申请日：1998-07-08
申请人： Frank W. Burcham, Jr. , John J. Burken , Jeanette Le
发明人： Frank W. Burcham, Jr. , John J. Burken , Jeanette Le
IPC分类号： B64C17/10 , B64D31/10 , B64C15/02
CPC分类号： B64D31/10 , B64C17/10
摘要： A system for emergency aircraft control uses at least one engine and lateral fuel transfer that allows a pilot to regain control over an aircraft under emergency conditions. Where aircraft propulsion is available only through engines on one side of the aircraft, lateral fuel transfer provides means by which the center of gravity of the aircraft can be moved over to the wing associated with the operating engine, thus inducing a moment that balances the moment from the remaining engine, allowing the pilot to regain control over the aircraft. By implementing the present invention in flight control programming associated with a flight control computer (FCC), control of the aircraft under emergency conditions can be linked to the yoke or autopilot knob of the aircraft. Additionally, the center of gravity of the aircraft can be shifted in order to effect maneuvers and turns by spacing such center of gravity either closer to or farther away from the propelling engine or engines. In an alternative embodiment, aircraft having a third engine associated with the tail section or otherwise are accommodated and implemented by the present invention by appropriately shifting the center of gravity of the aircraft. Alternatively, where a four-engine aircraft has suffered loss of engine control on one side of the plane, the lateral fuel transfer may deliver the center of gravity closer to the two remaining engines. Differential thrust between the two can then control the pitch and roll of the aircraft in conjunction with lateral fuel transfer.
摘要翻译：用于应急飞机控制的系统使用至少一个发动机和侧向燃料传输，其允许飞行员在紧急情况下重新获得对飞行器的控制。在飞机推进仅通过飞机一侧的发动机可用的情况下，侧向燃料传输提供了使飞机的重心能够移动到与操作发动机相关联的机翼的手段，从而引起平衡瞬间的时刻从其余的发动机，允许飞行员重新获得对飞机的控制。通过将本发明应用于与飞行控制计算机（FCC）相关联的飞行控制程序中，在紧急情况下飞行器的控制可以连接到飞机的轭或自动驾驶仪旋钮。此外，飞行器的重心可以移动，以便通过将这样的重心与推进的发动机或发动机更接近或更远离来实现机动和转动。在替代实施例中，具有与尾部相关联的第三发动机或以其他方式的飞行器通过适当地移动飞行器的重心由本发明容纳和实现。或者，如果四引擎飞机在飞机的一侧遭受发动机控制的损失，则侧向燃料传输可能使重心更靠近两个剩余的发动机。两者之间的差压可以随着侧向燃料转移而控制飞机的俯仰和滚动。

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