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公开(公告)号：US4628752A
公开(公告)日：1986-12-16
申请号：US711938
申请日：1985-03-15
申请人： William G. Paxton , Derek Wilkinson
发明人： William G. Paxton , Derek Wilkinson
CPC分类号： F16H25/20 , B64C13/14 , B64C13/50 , F16D59/00 , F16H2025/2068 , F16H2025/2081 , F16H25/2454 , Y10T74/19637
摘要： An actuator assembly has two actuators mounted back-to-back such that their actuator rods are displaced in opposite directions. Each actuator has a spring embracing the rod between two slidable collars. The spring urges the collars apart towards stops on the rod and stops on the actuator housing, so that, on failure of the actuator, the rod is displaced to a central position. The rod is driven by a motor which also rotates two discs of different diameters. Each disc has a notch in its edge which align only at the central position of the rod and allow a roller to drop into the notch. When the actuator fails, a solenoid releases a locking arm which engages the rollers, keeping them in the notches thereby preventing rotation of the discs and displacement of the rod.
摘要翻译： 致动器组件具有背对背安装的两个致动器致动器杆沿相反的方向移位。 每个致动器具有一个包围杆在两个可滑动套环之间的弹簧。 弹簧推动套环朝向杆上的止动件分开，并停在致动器壳体上，使得在致动器故障时，杆移动到中心位置。 杆由马达驱动，马达也旋转两个不同直径的盘。 每个盘在其边缘上具有凹口，其仅在杆的中心位置对准，并允许辊落入凹口中。 当执行器故障时，电磁阀释放与辊接合的锁定臂，将其保持在凹口中，从而防止盘的旋转和杆的移位。
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公开(公告)号：US2459143A
公开(公告)日：1949-01-18
申请号：US63096545
申请日：1945-11-26
申请人： BEIRISE JOHN C
发明人： BEIRISE JOHN C
IPC分类号： B64C13/14
CPC分类号： B64C13/14 , Y10T74/20636
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公开(公告)号：US20180017987A1
公开(公告)日：2018-01-18
申请号：US15209186
申请日：2016-07-13
CPC分类号： G05G5/06 , B64C13/04 , B64C13/0421 , B64C13/10 , B64C13/14 , B64C13/26 , B64C13/50 , G05G1/04 , G05G5/005 , G05G5/18 , G05G2505/00
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：US09771143B2
公开(公告)日：2017-09-26
申请号：US14494992
申请日：2014-09-24
发明人： Cory M. Crandall-Seibert , Andrew N. Baines , Timothy Michael Mayer , Gary L. Voss , Sean Bradshaw , Roger F. Glenn
摘要： A selector lever with redundant detent pins and detent plates and a method for using the selector lever to test for a failure of one or more detent pins. The selector lever includes at least two slides for independently moving the detent pins within the detent plates. The independent slides allow one detent pin to remain engaged. With only one detent pin engaged, the operator may test the ability to move the shaft and conclude whether or not the detent pin has failed.
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公开(公告)号：US20160085259A1
公开(公告)日：2016-03-24
申请号：US14495030
申请日：2014-09-24
发明人： Cory M. Crandall-Seibert , Andrew N. Baines , Timothy Michael Mayer , Gary L. Voss , Sean Bradshaw , Roger F. Glenn
摘要： A selector lever that comprises a shaft rotatably attached to a pivot and arranged between two detent plates, each of the detent plates having a plurality of slots arranged for receiving a detent pin located on the shaft. Each of the plurality of slots on each of the two detent plates is defined by a radial depth. One or more of the plurality of slots is a failure detection slot having an extended radial depth. When one of the detent pins has failed, the opposing detent pin is allowed to travel into the extended radial depth when placed in the failure detection slot. This action reveals a failure indicator, providing a visual indication that one of the detent pins has failed.
摘要翻译： 一种选档杆，包括可旋转地附接到枢轴并布置在两个制动板之间的轴，每个制动板具有多个槽，布置成用于容纳位于轴上的止动销。 两个制动板中的每一个上的多个狭槽中的每一个由径向深度限定。 多个槽中的一个或多个是具有延伸的径向深度的故障检测槽。 当其中一个止动销发生故障时，当置于故障检测槽中时，允许相对的止动销进入延伸的径向深度。 该动作显示故障指示器，提供其中一个止动销失败的视觉指示。
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16.发明授权Non-jamming, fail safe flight control system with non-symmetric load alleviation capability 失效具有非对称负载减轻能力的非干扰，故障安全飞行控制系统公开(公告)号：US06929222B2
公开(公告)日：2005-08-16
申请号：US10657410
申请日：2003-09-08
申请人： Mihailo P. Djuric
发明人： Mihailo P. Djuric
摘要： A non-jamming fail safe flight control system with non-symmetric load alleviation capability includes a dual cable control system one for each side of control surface, like an elevator or an aileron, controlled by a pilot but driven by a driving system which allows control surfaces to even out the load from one side to the other without affecting pilots control while—if one side becomes jammed—enabling the pilot, with no extra action, to continue flying the aircraft utilizing the other side. In another embodiment an automatic lock feature ensures that a pilot is able to continue to complete the flight in case of severance of a control cable due to a discrete damage without interruption attributable to the control system. Yet another embodiment utilizing either the same or a separate locking feature enables the pilot to lock the surfaces upon parking the aircraft.
摘要翻译： 具有非对称负载减轻能力的非干扰故障安全飞行控制系统包括一个双控制电缆控制系统，一个用于控制表面的每一侧，如电梯或副翼，由飞行员控制，但由驱动系统驱动，允许控制 表面将负载从一侧平衡到另一侧，而不会影响飞行员的控制，而如果一方被卡住 - 使飞行员无需额外的动作就可以利用另一侧继续飞行飞机。 在另一个实施例中，自动锁定功能确保在由于离开的损坏而不会导致控制系统的中断的情况下，飞行员能够继续完成飞行，以防止控制电缆的中断。 利用相同或单独的锁定特征的另一实施例使飞行员能够在停放飞行器时锁定表面。
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公开(公告)号：US06393880B1
公开(公告)日：2002-05-28
申请号：US09512681
申请日：2000-02-25
申请人： David E. Vance, Sr.
发明人： David E. Vance, Sr.
IPC分类号： F16C300
CPC分类号： B64C13/14 , Y10T70/5611 , Y10T70/5646 , Y10T70/565 , Y10T70/5655 , Y10T70/5735
摘要： A aircraft anti-theft device for immobilizing the yoke of an aircraft. The aircraft anti-theft device includes a device for immobilizing the yoke control of an aircraft. The yoke control has a gust lock hole for holding the yoke in a stationary position. The device has a sleeve for wrapping about the yoke control. The sleeve has an interior channel for receiving a portion of the yoke control. The sleeve is divided along its longitudinal axis to form a first and second sections. The first and second sections each have a pair of end edges, a first side edge, and a second side edge. A lock locks the first and second sections in a closed position. A pin for insertion into the gust lock is fixedly coupled to an interior surface of the first section of the sleeve. The pin protrudes from the interior surface of the sleeve. The first and second sections are placed around the yoke control such that the pin enters the gust lock.
摘要翻译： 用于固定飞机轭的飞机防盗装置。 飞机防盗装置包括用于固定飞机的轭控制的装置。 轭控制器具有用于将轭保持在静止位置的阵风锁定孔。 该装置具有用于缠绕轭控制的套筒。 套筒具有用于接收轭控制部分的一部分的内部通道。 套筒沿其纵向轴线分开以形成第一和第二部分。 第一和第二部分各自具有一对端边缘，第一侧边缘和第二侧边缘。 锁将第一和第二部分锁定在关闭位置。 用于插入阵风锁的销固定地联接到套筒的第一部分的内表面。 销从套筒的内表面突出。 第一和第二部分放置在轭控制器周围，使得销进入阵风锁。
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18.发明授权
公开(公告)号：US5082213A
公开(公告)日：1992-01-21
申请号：US551626
申请日：1990-07-10
申请人： Ramon L. Torres
发明人： Ramon L. Torres
IPC分类号： B64C13/14
CPC分类号： B64C13/14 , B64C13/04 , Y10T70/5726
摘要： The use of a center lock bar which telescopingly receives two telescoping arms, each of which has a control column or shaft grip on its remote end is disclosed. The arms are secured to the parallel control columns by at least one gust lock pin. Provision is made for a throttle mixture lock plate to be secured to the lower portion of the radio lock pan which, in turn, has essentially parallel sidewalls with opposed openings through which the center lock bar passes. Optionally folding extension radio lock pans may be employed for a double stack installation. Finally, means are provided in the form of a lock, whether padlock or internally mounted, to lockingly secure the center lock bar to the two telescoping arms. The method of the invention looks to providing a lock for radios, throttles, and gust locks in a dual control aircraft by stabilizing the two control columns by means of a telescoping member which can accommodate differences in the distance between the parallel control columns of the aircraft. The step in addition to the foregoing of locking is done by securing at least one pin to one of the parallel control columns, and thereafter mounting a central radio stack and throttle control centrally of the central portion of the lock. Once these steps have been followed, a lock removably secures the center lock bar against movement relative to the radio lock pan and the flight controls as well as engine controls.
摘要翻译： 公开了一种可伸缩地容纳两个伸缩臂的中心锁杆的使用，每个伸缩臂在其远端具有控制柱或轴柄。 臂通过至少一个阵风锁定销固定到并行控制柱上。 设置了用于将油门混合物锁定板固定到无线电锁盘的下部，其又具有基本平行的具有相对开口的中间锁定杆通过的侧壁。 可选地，折叠扩展无线电锁盘可用于双堆叠安装。 最后，以锁的形式提供装置，无论是挂锁还是内部安装，以将中心锁定杆锁定到两个伸缩臂上。 本发明的方法寻求通过使伸缩构件稳定两个控制柱来提供双控制飞机中的无线电，节流和阵风锁的锁，该伸缩构件能够适应飞行器的平行控制柱之间的距离的差异 。 通过将至少一个销固定到并行控制柱中的一个上，然后将中央无线电堆叠和节流控制安装在锁的中心部分的中心部分之外，除了上述锁定之外的步骤也是这样。 一旦遵循了这些步骤，锁可以可拆卸地固定中心锁杆相对于无线电锁盘和飞行控制以及发动机控制的运动。
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公开(公告)号：US4930730A
公开(公告)日：1990-06-05
申请号：US134757
申请日：1987-12-18
申请人： David C. Quick
发明人： David C. Quick
摘要： An automatic neutral position locking system for a control surface of an aircraft. A hydraulic prime mover is provided for moving the control surface. A locking device is capable of locking the control surface against movement. A ratchet-and-pawl device is operatively associated with a rotary drive train between the prime mover and the control surface for actuating the locking device in response to the control surface reaching a neutral position. The ratchet-and-pawl device normally is maintained in inactive condition when hydraulic pressure exists in the prime mover. A pneumatic piston-and-cylinder device, when under pressure, maintains the ratchet-and-pawl device in normally inactive condition. With a loss of hydraulic pressure, the ratchet-and-pawl device is effective to actuate the locking device in response to the control surface itself reaching the neutral position as the control surface moves under external loads.
摘要翻译： 一种用于飞机控制面的自动中立位置锁定系统。 提供了用于移动控制表面的液压原动机。 锁定装置能够锁定控制表面以防止移动。 棘爪和棘爪装置与原动机和控制表面之间的旋转传动系可操作地相关联，用于响应于控制表面达到中立位置来致动锁定装置。 当原动机中存在液压时，棘爪和棘爪装置通常保持在非活动状态。 气动活塞和气缸装置在处于压力下时将棘爪和棘爪装置保持在正常的非活动状态。 随着液压的损失，当控制表面在外部载荷下移动时，棘轮和棘爪装置响应于控制表面本身达到中立位置而有效地致动锁定装置。
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公开(公告)号：US4888968A
公开(公告)日：1989-12-26
申请号：US290297
申请日：1988-12-27
申请人： Frank D. Azvedo
发明人： Frank D. Azvedo
CPC分类号： B64D45/0015 , B60R25/007 , B64C13/14 , B60K2350/406 , Y10T70/50 , Y10T70/5562 , Y10T70/558 , Y10T70/5779
摘要： A shield of rigid sheet metal is of a size and shape to substantially cover the instrument panel of an aircraft. A pair of shrouds on the bottom of the shield are spaced so that each fits over one of the control columns of the aircraft, and aligned holes in each shroud are adapted to receive a padlock to lock the shield in place. The shrouds are of a length to fit closely over the control columns when fully extended to prevent any significant movement of the control column axially and pins, which are secured to the shield, extent through openings in the control columns to prevent any accidental or unauthorized turning. A cylindrical housing open at one end is received over the throttle control, and a lock stem extending vertically from the housing is received in a tube, which is fixed to the shield, when the shield is possitioned on the instrument panel so that there can be no manipulation of the throttle.
摘要翻译： 刚性金属板的护罩具有基本覆盖飞行器仪表板的尺寸和形状。 护罩底部的一对护罩间隔开，使得每个护罩均配合在飞行器的一个控制柱上，并且每个护罩中的对准的孔适于接纳挂锁以将护罩锁定在适当的位置。 当完全延伸时，护罩的长度可以紧密地配合在控制柱上，以防止控制柱轴向的任何显着的运动和通过控制柱中的开口固定到屏蔽件上的销，以防止意外或未经授权的转动 。 一端开口的圆柱形壳体被接收在节流控制上，并且当在仪表板上存在屏蔽时，从壳体垂直延伸的锁定杆被容纳在固定到屏蔽件上的管中，从而可以 没有操纵油门。
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