公开(公告)号：US20120234985A1

公开(公告)日：2012-09-20

申请号：US13411950

申请日：2012-03-05

申请人： Romuald Biest ,  Robert Convers

发明人： Romuald Biest ,  Robert Convers

IPC分类号： B64C13/14

CPC分类号： B64C13/04 ,  G05G9/047

摘要： The invention provides a control mechanism for controlling flight of an aircraft, the control mechanism comprising a cyclic control stick (1) that is mounted to tilt (B1, B2) on a carrier structure (4) and that is in engagement with remote mechanical transmission members (2, 3). The stick (1) is arranged as a telescopic member provided with locking means (20) for locking it in a normal-use retracted position, and is equipped with deployment means (21). Unlocking of the locking means (20) and use of the deployment means (21) depend on an assistance device (17) associated with the stick (1) being in a defective state. In the event of such a defective state being detected, the stick (1) is suitable for being deployed so as to increase the comfort of the pilot while manipulating it.

摘要翻译： 本发明提供了一种用于控制飞行器飞行的控制机构，该控制机构包括一个循环控制杆（1），该循环控制杆安装成在载体结构（4）上倾斜（B1，B2）并与远程机械传动 会员（2,3）。 杆（1）被布置为具有用于将其锁定在正常使用的缩回位置的锁定装置（20）的伸缩构件，并且配备有展开装置（21）。 锁定装置（20）的解锁和展开装置（21）的使用取决于与棒（1）相关联的辅助装置（17）处于缺陷状态。 在检测到这样的缺陷状态的情况下，棒（1）适于被部署，以便在操纵该飞行员的同时增加飞行员的舒适性。

公开(公告)号：US20100019097A1

公开(公告)日：2010-01-28

申请号：US12180349

申请日：2008-07-25

申请人： MAX A. PROBASCO ,  MICHAEL J. SCHIPPER ,  STEVE RUZIC

发明人： MAX A. PROBASCO ,  MICHAEL J. SCHIPPER ,  STEVE RUZIC

IPC分类号： B64C13/14

CPC分类号： B64F1/005 ,  Y10T292/228 ,  Y10T292/34 ,  Y10T292/37

摘要： Embodiments of the present disclosure generally provide a device for securing the external control surfaces of an aircraft. A gust lock is described for securing the control surfaces of an aircraft that includes an elongated top plate having a rotably associated strap lock, an elongated bottom plate having a rotably mounted capture piece, and a strap running from the capture piece through the strap lock to a tail section.

摘要翻译： 本公开的实施例通常提供用于固定飞行器的外部控制表面的装置。 描述了一种用于固定飞机的控制表面的阵风锁，其包括具有可旋转相关联的带锁的细长顶板，具有可旋转安装的捕获件的细长底板和从捕获件通过带锁延伸到其上的带 尾部。

公开(公告)号：US07316373B2

公开(公告)日：2008-01-08

申请号：US11038725

申请日：2005-01-19

申请人： Takashi Nagayama ,  Hiroshi Yoneda ,  Kenshi Miyata

发明人： Takashi Nagayama ,  Hiroshi Yoneda ,  Kenshi Miyata

IPC分类号： B64C13/14

CPC分类号： B64C13/24 ,  Y02T50/44

摘要： A disengage device in an aircraft, which prevents a driving force of a drive unit from transmitting to a control surface, having:a first rod having one end portion connected to the drive unit, the other end portion, and a hollow portion formed to have a predetermined length and open at the other end portion;a branch pipe which is connected to a side wall of the first rod and communicates with the hollow portion;a second rod having one end portion connected to the push-pull rod, the other end portion, and a recess portion formed in a part of a side wall of a portion which extends a predetermined length from the other end portion to the one end portion side and is inserted in the hollow portion; andan engaging member arranged to be freely movable in the branch pipe, which is engagable with the recess portion.

摘要翻译： 一种飞机中的脱离装置，其防止驱动单元的驱动力传递到控制表面，具有：第一杆，其具有连接到驱动单元的一个端部，另一个端部，以及形成为具有 预定长度并在另一端部开口; 分支管，其与所述第一杆的侧壁连接并与所述中空部连通; 第二杆，其一端部连接到推拉杆，另一端部，以及形成在从另一端部向一端部延伸预定长度的部分的侧壁的一部分中的凹部 并插入中空部分; 以及接合构件，其布置成在与所述凹部接合的分支管中可自由移动。

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

IPC分类号： B64C13/14 ,  B64C13/30

CPC分类号： B64C13/30 ,  B64C13/14 ,  Y02T50/44

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。

公开(公告)号：US5984241A

公开(公告)日：1999-11-16

申请号：US924963

申请日：1997-09-08

申请人： Gary A. Sparks

发明人： Gary A. Sparks

IPC分类号： B64C13/04 ,  B64C13/14

CPC分类号： B64D31/04

摘要： An electrical lock for a moving part prevents the part from moving unless a device controlled by the part is in a safe mode. The invention may find a use in many different environments. The specific example here described is a set of reverse thruster doors on a jet engine. The lock prevents a throttle from applying or removing power unless the reverse thruster doors are properly set for such application or removal of power. The lock is removed when the doors reach full deployment or retraction, respectively, which is appropriate for the direction in which said throttle is moved. These functions are provided under the control of a single solenoid.

摘要翻译： 用于移动部件的电锁防止部件移动，除非由部件控制的装置处于安全模式。 本发明可以在许多不同的环境中使用。 这里描述的具体示例是喷气发动机上的一组反向推进器门。 除非反向推进器门适当地设置用于这种应用或移除电源，否则锁可防止油门施加或移除动力。 当门分别达到完全展开或缩回时，锁被去除，这适合于所述节气门移动的方向。 这些功能在单个电磁阀的控制下提供。

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。

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

IPC分类号： B64C13/14 ,  B64C13/16 ,  B64C13/28

CPC分类号： B64C13/28 ,  B64C13/14 ,  B64C13/16

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。

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

IPC分类号： B60R25/00 ,  B64C13/14 ,  B64D45/00

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。

公开(公告)号：US4475366A

公开(公告)日：1984-10-09

申请号：US268841

申请日：1981-06-01

申请人： Michael Marneris

发明人： Michael Marneris

IPC分类号： B60R25/00 ,  B64D43/00 ,  B60R25/02 ,  B64C13/12 ,  B64C13/14 ,  E05B65/12

CPC分类号： B64D43/00 ,  B60R25/007 ,  Y10T70/409 ,  Y10T70/493 ,  Y10T70/50 ,  Y10T70/565 ,  Y10T70/5726 ,  Y10T70/5779 ,  Y10T70/5894 ,  Y10T70/5982 ,  Y10T70/8838

摘要： A device for protecting the navigational instruments and radio equipment mounted on an instrument panel in the cockpit of an aircraft against theft. The device includes a protective cover mounted immediately adjacent the instrument panel and means for locking the potective cover to the control column of the aircraft in a manner such that the aircraft controls will not be damaged in the event that the protective cover is tampered with.

摘要翻译： 一种用于保护安装在飞机驾驶舱中的仪表板上的导航仪器和无线电设备的装置，用于防盗。 该装置包括紧邻仪表板安装的保护盖，以及用于以可使防护罩被篡改的情况下飞机控制不会被损坏的方式将潜水罩锁定到飞行器的控制柱的装置。

公开(公告)号：US4473203A

公开(公告)日：1984-09-25

申请号：US482172

申请日：1983-04-05

申请人： Pierre Barnoin ,  Jacques M. Cas

发明人： Pierre Barnoin ,  Jacques M. Cas

IPC分类号： B64C13/12 ,  G05G9/047 ,  G05G11/00 ,  B64C13/14

CPC分类号： B64C13/12 ,  G05G11/00 ,  G05G9/047 ,  G05G2009/04718 ,  Y10T74/20213 ,  Y10T74/20636

摘要： The invention relates to a control column (2) for a copilot of an aircraft, coupled for control of roll and pitch by a linkage (5) to the pilot's control column (1). This linkage comprises two parallel rods (6,7) pivoted on the one hand to the column (1) and on the other hand to a member (13) connected to the column (2) by a double universal joint (14, 17). When operative, the column (2) is locked to the member (13) by a lock bolt (19). This control column can be put out of action by releasing the said bolt and can be secured by hooking to a fixed point, in which case the double universal joint (14, 17) ensures its disconnection from the column (1) and thus prevents any misoperation.

摘要翻译： 本发明涉及一种用于飞机的副驾驶的控制柱（2），其通过联动装置（5）与飞行员的控制塔（1）联接以控制滚动和俯仰。 该联动装置包括两个平行的杆（6,7），一方面枢转到柱（1），另一方面由两个万向节（14,17）连接到柱（2）的构件（13） 。 当操作时，柱（2）通过锁定螺栓（19）锁定到构件（13）。 该控制柱可以通过释放所述螺栓而失去作用，并且可以通过钩住固定点来固定，在这种情况下，双万向接头（14,17）确保其与柱（1）断开，从而防止任何 误操作