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11.发明授权公开(公告)号：US10737799B2
公开(公告)日：2020-08-11
申请号：US16159348
申请日：2018-10-12
IPC分类号： B64C13/00 , B64D31/10 , F02C9/54 , F02C7/26 , G08G5/00 , G08G5/04 , G05D1/08 , G05D1/00 , G05D3/12 , B64D43/00 , F02C9/26
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.
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公开(公告)号：US10737798B2
公开(公告)日：2020-08-11
申请号：US15700172
申请日：2017-09-10
申请人： Ansel Misfeldt
发明人： Ansel Misfeldt
摘要： A method and system for providing corrective action to a rotorcraft experiencing motor failure is provided. Included in the method and system are embodiments that receive feedback from sensors directed at measuring a state of motors used to provide lift to the rotorcraft. The method and system also describe embodiments for determining that there is a malfunctioning motor, and furthermore, the appropriate corrective action for responding to the malfunctioning motor. In some embodiments, the method and system are configured to reduce power to the malfunctioning motor while simultaneously adjusting power supplied to the remaining motors such that changes in total thrust and net torque are minimized.
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公开(公告)号：US10703498B2
公开(公告)日：2020-07-07
申请号：US15801486
申请日：2017-11-02
申请人： The Boeing Company
摘要： An example method of optimizing reverse thrust operation on an aircraft having two or more engines while landing the aircraft is described. The method includes operating the two or more engines on the aircraft in a reverse idle during a landing rollout of the aircraft, responsively causing deployment of a thrust reverser on each of the engines causing a first reverse idle thrust for slowing the aircraft, monitoring each of the engines for failure of deployment of the thrust reverser, and based on detection of a failure of deployment of a respective thrust reverser on one of the engines, operating the one of the engines on the aircraft at a second reverse idle thrust optimized for a direction of an applied thrust of the one of the engines. The second reverse idle thrust is lower than the first reverse idle thrust.
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公开(公告)号：US10513342B2
公开(公告)日：2019-12-24
申请号：US15955264
申请日：2018-04-17
申请人： Airbus (S.A.S.)
摘要： A method for managing unbalanced thrusts caused by engine failures in an aircraft provided with a distributed propulsion system, the distributed propulsion system including 2N powertrains (PTi), with N a strictly positive integer and i an integer lying between 1 and 2N inclusive, distributed symmetrically in relation to a plane of symmetry of the aircraft, according to which the power of at least one powertrain belonging to a first side of the plane of symmetry is reduced when a failure occurs in a powertrain belonging to the opposite side, such that the sum of the moments of the thrusts generated by the powertrains in relation to the center of gravity of the aircraft is nil, to within regulatory tolerances.
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15.发明申请公开(公告)号：US20190047715A1
公开(公告)日：2019-02-14
申请号：US16159348
申请日：2018-10-12
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.
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公开(公告)号：US20180079519A1
公开(公告)日：2018-03-22
申请号：US15554642
申请日：2016-08-01
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.
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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
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。
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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。
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公开(公告)号：US6126111A
公开(公告)日：2000-10-03
申请号：US112067
申请日：1998-07-08
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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公开(公告)号：US5927655A
公开(公告)日：1999-07-27
申请号：US925605
申请日：1997-09-08
CPC分类号： B64D31/10 , F02C9/42 , G05D1/0072 , Y02T50/671
摘要： The present invention relates to a device for controlling the thrust of an aircraft, with several engines (M1, M4), comprising calculation units (UC1, UC4) that formulate first commands for controlling the engine speeds. According to the invention, said device (1) additionally comprises means (CONT1, CONT4) of controlling the two outer engines (M1, M4), calculation means that formulate second commands for controlling the speed of the outer engines (M1, M4) making it possible to obtain a reduction in thrust, and switching means which, during normal operation of the outer engines (M1, M4) send the first commands to these engines and, when one outer engine (M1) fails, send the second commands to the opposite outer engine (M4).
摘要翻译： 本发明涉及一种用于控制飞机的推力的装置，其中包括计算单元（UC1，UC4）的几个发动机（M1，M4），其配置用于控制发动机速度的第一命令。 根据本发明，所述装置（1）还包括控制两个外部发动机（M1，M4）的装置（CONT1，CONT4），制定用于控制外部发动机（M1，M4）的速度的第二命令的计算装置 可以获得推力的减小，以及在外部发动机（M1，M4）的正常操作期间向这些发动机发送第一命令的切换装置，并且当一个外部发动机（M1）失效时，将第二个命令发送到 对面的外引擎（M4）。
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