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公开(公告)号：US20230312080A1
公开(公告)日：2023-10-05
申请号：US18129419
申请日：2023-03-31
发明人： Bernhard SCHLIPF , Florian LORENZ
摘要： A wing for an aircraft is disclosed including a main wing and a trailing edge high lift assembly movably arranged at a trailing edge of the main wing, the trailing edge high lift assembly having a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position. The connection assembly includes an actuator unit for moving the flap between the retracted position and the at least one extended position. The flap includes a leading edge part and a trailing edge part mounted to the leading edge part in a manner pivotable about a pivot axis.
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公开(公告)号：US20190092491A1
公开(公告)日：2019-03-28
申请号：US15721268
申请日：2017-09-29
发明人： Erik Harrington , Christian Miller , Yuniya S. Bishop , Jason B. Kreienheder , Michael Skirtich , Gregory T. Wallen
CPC分类号： B64D45/00 , B64C13/24 , B64C13/28 , B64C13/38 , B64D2045/0085 , G07C5/0808 , G07C5/085
摘要： A method of prognostic health monitoring is provided for use with an aircraft. The method includes generating torque for controlling positions of controllable surfaces at right- and left-hand-sides (RHS and LHS) of the aircraft in a power drive unit (PDU) based on torque-limiter (TL) thresholds, performing real-time monitoring of the torque at the RHS and LHS of the aircraft, generating RHS and LHS torque information from results of the performing of the real-time monitoring, analyzing the RHS and LHS torque information and controlling operations of the PDU based on results of the analysis by at least one of modifying, tuning and defining the TL thresholds.
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公开(公告)号：US09738374B2
公开(公告)日：2017-08-22
申请号：US15120413
申请日：2015-02-04
发明人： Bruno Tilly , Nicolas Ravoux
摘要： The invention relates to a flight control device for an aircraft, the device comprising a mount, a lever pivotally mounted on the mount, and mechanical means for generating a return force for the lever, said means including a spring and a first motor member that are arranged so that a first end of the spring is constrained to move in rotation with the lever and a second end of the spring is constrained to move in rotation with an outlet shaft of the first motor member. According to the invention, the flight control device includes an electrical assistance system for assisting said mechanical means for generating a return force.
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公开(公告)号：US20150105199A9
公开(公告)日：2015-04-16
申请号：US13424884
申请日：2012-03-20
申请人： Terence Ross Golding
发明人： Terence Ross Golding
CPC分类号： F16H3/725 , B64C13/28 , B64C13/38 , B64C13/50 , B64C25/18 , F16H37/065 , F16H49/001 , F16H61/12 , F16H2061/122 , F16H2200/2005 , H02K7/116 , H02K16/00 , Y02T50/44 , Y10T477/23
摘要： An actuator for an aircraft is provided. The actuator comprises a first motor, a second motor and an actuator output, which are interconnected by a gear assembly. The actuator output is driveable by the first motor independently of the second motor; the actuator output is driveable by the second motor independently of the first motor; and the actuator output is driveable by the first and second motors in combination.
摘要翻译： 提供了一种用于飞行器的致动器。 致动器包括通过齿轮组件互连的第一电动机，第二电动机和致动器输出。 致动器输出可由第一电动机独立于第二电动机驱动; 致动器输出可由第二电动机独立于第一电动机驱动; 并且致动器输出可由第一和第二电动机组合驱动。
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公开(公告)号：US08646729B2
公开(公告)日：2014-02-11
申请号：US13150334
申请日：2011-06-01
申请人： Glenn S. Bushnell
发明人： Glenn S. Bushnell
IPC分类号： B64C9/00
CPC分类号： B64C9/02 , B64C9/10 , B64C9/32 , B64C9/323 , B64C9/34 , B64C13/38 , Y02T50/32 , Y02T50/44 , Y10T137/0402 , Y10T137/8593
摘要： Deployable aerodynamic devices with reduced actuator loads, and related systems and methods are disclosed. An external flow system in accordance with a particular embodiment includes an external flow body, a deployable device carried by and movable relative to the external flow body, and a coupling connected between the external flow body and the deployable device. The system can further include an actuator device operatively coupled between the external flow body and the deployable device, with the actuator device positioned to move the deployable device along a motion path between a stowed position and the deployed position. The motion path can have a first portion over which the load delivered by the actuator device increases as the deployed device moves toward the deployed position, and a second portion over which the load delivered by the actuator device decreases as the deployed device moves toward the deployed position.
摘要翻译： 公开了具有减少的致动器负载的可部署的空气动力学装置以及相关的系统和方法。 根据特定实施例的外部流动系统包括外部流动体，由外部流动体承载并可移动的可展开装置，以及连接在外部流动体和可部署装置之间的联接器。 该系统还可以包括可操作地联接在外部流动体和可展开装置之间的致动器装置，致动器装置被定位成沿着收起位置和展开位置之间的运动路径移动可展开装置。 运动路径可以具有第一部分，当被展开的装置朝向展开位置移动时，致动器装置输送的负载增加;以及第二部分，当被展开的装置朝向展开位置移动时，由致动装置输送的负载减小 位置。
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6.发明申请Deployable aerodynamic devices with reduced actuator loads, and related systems and methods 有权减少执行器负载的可部署空气动力装置，以及相关系统和方法公开(公告)号：US20090146000A1
公开(公告)日：2009-06-11
申请号：US11953672
申请日：2007-12-10
申请人： Glenn S. Bushnell
发明人： Glenn S. Bushnell
IPC分类号： B64C3/38
摘要： Deployable aerodynamic devices with reduced actuator loads, and related systems and methods are disclosed. An external flow system in accordance with a particular embodiment includes an external flow body, a deployable device carried by and movable relative to the external flow body, and a coupling connected between the external flow body and the deployable device. The system can further include an actuator device operatively coupled between the external flow body and the deployable device, with the actuator device positioned to move the deployable device along a motion path between a stowed position and the deployed position. The motion path can have a first portion over which the load delivered by the actuator device increases as the deployed device moves toward the deployed position, and a second portion over which the load delivered by the actuator device decreases as the deployed device moves toward the deployed position.
摘要翻译： 公开了具有减少的致动器负载的可部署的空气动力学装置以及相关的系统和方法。 根据特定实施例的外部流动系统包括外部流动体，由外部流动体承载并可移动的可展开装置，以及连接在外部流动体和可部署装置之间的联接器。 该系统还可以包括可操作地联接在外部流动体和可展开装置之间的致动器装置，致动器装置被定位成沿着收起位置和展开位置之间的运动路径移动可展开装置。 运动路径可以具有第一部分，当被展开的装置朝向展开位置移动时，致动器装置输送的负载增加;以及第二部分，当被展开的装置朝向展开位置移动时，由致动装置输送的负载减小 位置。
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公开(公告)号：US5743490A
公开(公告)日：1998-04-28
申请号：US602190
申请日：1996-02-16
申请人： Gary D. Gillingham , Gary L. Miles
发明人： Gary D. Gillingham , Gary L. Miles
CPC分类号： B64D45/0005 , B64C13/38 , B64D2045/001
摘要： The problem of providing a flight control panel actuation system, including asymmetry brakes, which will fit into aircraft wings having narrow supercritical air foil shapes, and yet provide a degree of safety with regard to preventing asymmetry which is as good or better than that provided by prior actuation systems is solved by an actuation system which positions an asymmetry brake inboard of an outermost flight control panel actuator within the aircraft wing. The asymmetry brake utilizes a jaw type clutch coupled to an electrical solenoid through a ball spline mechanism to provide significantly greater braking capacity in a given volume than other types of braking devices. The outermost control panel actuator includes an integral no-back to hold that actuator against further movement, should a driveline connection between the asymmetry brake and the actuator be severed. Where the actuation system includes multiple actuators, only one of the actuators is equipped with end of travel stops, therefore allowing the remaining actuators in the system to be physically smaller because they are not required to react loads incident with limiting end of travel. By making the other actuators in the system physically smaller, they are more readily fitted into supercritical wings.
摘要翻译： 提供飞行控制面板致动系统的问题，其包括不对称制动器，其将适合具有窄超临界空气箔形状的飞机机翼，并且在防止不对称性方面提供一定程度的安全性，其优于或优于由 先前的致动系统通过致动系统来解决，该致动系统将飞行器机翼内的最外面的飞行控制面板致动器的内部的不对称制动器定位。 不对称制动器使用通过滚珠花键机构耦合到电螺线管的钳式离合器，以在给定的体积中提供比其它类型的制动装置显着更大的制动能力。 如果不对称制动器和致动器之间的传动系连接被切断，则最外面的控制面板致动器包括一体的不后退以保持该致动器不被进一步移动。 在致动系统包括多个致动器的情况下，只有一个致动器配备有行程停止端，从而允许系统中剩余的致动器物理上更小，因为它们不需要对入射限制行程的负载作出反应。 通过使系统中的其他执行器物理上较小，它们更容易装入超临界机翼。
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公开(公告)号：US4903578A
公开(公告)日：1990-02-27
申请号：US216753
申请日：1988-07-08
申请人： Leslie S. Terp
发明人： Leslie S. Terp
CPC分类号： B64C13/40 , B64C13/38 , F15B9/09 , H01F7/1615 , H01F7/122 , Y10T137/86614
摘要： An electropneumatic rotary actuator has proportional fluid valving providing introduction and exhaust of pressurized fluid to and from a working chamber of the actuator. By control of the admission angle and venting angle of the fluid pressure and flow with respect to top dead center and bottom dead center of a working piston of the actuator both the torque level and gas consumption rates of the actuator may be controlled. Further by modulating the average working fluid pressure within the actuator the stiffness or resistance to backdriving of the actuator may be controlled. A proportional linear electrical solenoid is disclosed and employed in the actuator of the present invention to drive a double-acting closed-centered valve device. Because of its lightweight, relatively simplicity, high stiffness to backdriving, and relatively low gas consumption rate, the present actuator is expected to find application in airborne vehicles.
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公开(公告)号：US4228386A
公开(公告)日：1980-10-14
申请号：US912165
申请日：1978-06-02
申请人： Carl D. Griffith
发明人： Carl D. Griffith
摘要： A single actuator unit is installed in an aircraft, for example, a helicopter, and is coupled to the control linkage from the pilot's stick to perform the functions of series actuation, trim actuation, artificial feel, control position sensing, control limits and, if needed, force boost. Although the device performs as a series actuator, it is installed in and connected to the vehicle surface control linkages in the conventional parallel actuator manner and therefore greatly simplifies control system installation and reduces problems associated with control rod vibration resonances normally encountered with series actuator installations.
摘要翻译： 单个致动器单元安装在飞机中，例如直升机，并且从飞行员的杆连接到控制联动装置，以执行串联致动，调整致动，人造感觉，控制位置感测，控制极限的功能，以及如果 需要，力量提升。 虽然该装置作为串联致动器，但是以常规并行致动器方式安装在车辆表面控制联动器中并且连接到车辆表面控制联动装置上，因此大大简化了控制系统的安装，并且减少了与串联执行器装置通常遇到的控制杆振动共振有关的问题。
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10.发明授权
公开(公告)号：US4079906A
公开(公告)日：1978-03-21
申请号：US779513
申请日：1977-03-21
CPC分类号： B64C13/38
摘要： In a servocontrol device for controlling a control surface of an aircraft, which device is associated with a mechanical control member such as control column, wheel, pedals, and which comprises two identical double-acting hydraulic rams, integral with each other and each controlled by means of a slide valve, the slide valves each being controlled by a servovalve, whilst each servovalve is controlled by an electrical chain associated therewith, emitting an electrical control signal taking into account the displacements of said control member, the chains are connected to each other by crossed connections and they comprise apparatus for delivering equal signals to said servovalves.The invention is directed to the control of the control surfaces of an aircraft.
摘要翻译： 在用于控制飞行器的控制表面的伺服控制装置中，哪个装置与机械控制构件（例如控制柱，车轮，踏板）相关联，并且包括两个相同的双作用液压柱塞，它们彼此成一体，并且各自由 滑阀的装置，每个由伺服阀控制的滑阀，而每个伺服阀由与其相关联的电链控制，发射电控制信号，考虑到所述控制构件的位移，链条彼此连接 通过交叉连接，并且它们包括用于向所述伺服阀输送相等信号的装置。
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