-
公开(公告)号：US20240262490A1
公开(公告)日：2024-08-08
申请号：US18609385
申请日：2024-03-19
发明人： Rodrigo Rizzi STARR , Robert Austen FOX , Markus SCHERDEL , Alex Duarte GOMES , Vincente MARTÍNEZ MARTÍNEZ , Fabio Wilson RODRIGUES , Rogério DE CERQUEIRA LARIO
CPC分类号： B64C13/0421 , B64C13/10 , B64C13/12 , B64C13/14 , B64C13/503
摘要： An inceptor apparatus for an aircraft comprises a primary inceptor member provided in the form of a stick member having a grip portion, at which the stick member can be gripped by a pilot's hand, and a secondary inceptor member provided at an upper portion of the primary inceptor member and having an actuating portion, at which the secondary inceptor member can be manually actuated by a pilot's thumb. Both inceptor members have associated a respective sensor assembly which is provided to generate electronic flight control signals or commands in response to at least one of i) pivoting movements of the respective inceptor member around each of two independent maneuvering axes associated to the inceptor member, ii) forces acting on or via the respective inceptor member in pivoting directions with respect to each of the maneuvering axes, and iii) lateral flexing or bending of the respective inceptor member.
-
公开(公告)号：US10676210B2
公开(公告)日：2020-06-09
申请号：US15892992
申请日：2018-02-09
发明人： Milton E. Scott
摘要： A lock-detecting system is configured to be installed in an aircraft to determine if a gust lock is emplaced on a flight control surface. The lock-detecting system includes at least one servo actuator and a computing device. The at least one servo actuator is associated with the flight control surface of the aircraft such that the servo actuator is configured to supply a force to a flight control surface when engaged. The computing device is configured to instruct the at least one servo actuator to actuate the flight control surface, acquire an indication that the flight control surface did not move in response to said actuation by the servo actuator, and alert a pilot to remove the gust lock from the flight control surface.
-
公开(公告)号：US10583915B2
公开(公告)日：2020-03-10
申请号：US15729985
申请日：2017-10-11
申请人： The Boeing Company
摘要： Systems and methods are provided for aircraft spoiler lockout. One embodiment is a system that includes a locking device that removably engages a control member inside a cockpit of an aircraft. The locking device restricts motion of the control member to prevent movement of wing surfaces of the aircraft. The system further includes a controller in communication with a wireless transmitter. The controller determines from a signal sent by the wireless transmitter whether both handheld switches connected to the wireless transmitter are being actively held. If so, the controller directs a supply of power to the locking device thereby causing the locking device to temporarily release the control member. Otherwise, the locking device restricts motion of the control member.
-
公开(公告)号：US10031546B2
公开(公告)日：2018-07-24
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.
-
公开(公告)号：US10017242B2
公开(公告)日：2018-07-10
申请号：US15011288
申请日：2016-01-29
申请人： The Boeing Company
IPC分类号： B64C13/14
CPC分类号： B64C13/14 , B64C13/044 , B64F5/40
摘要： A lockout assembly for first and second rudder pedals of an aircraft includes first and second spacers, each of which is configured to be inserted within a corresponding one of first and second slots disposed in an adjacent rudder pedal housing. A coupling mechanism is configured to couple the first spacer to the second spacer through the rudder pedal housing so as to retain the first and second spacers in corresponding ones of the slots. The lockout mechanism prevents movement of the rudder pedals in a same direction, and hence, movement of the aircraft's rudder.
-
公开(公告)号：US20170217567A1
公开(公告)日：2017-08-03
申请号：US15011288
申请日：2016-01-29
申请人： The Boeing Company
IPC分类号： B64C13/14
CPC分类号： B64C13/14 , B64C13/044 , B64F5/40
摘要： A lockout assembly for first and second rudder pedals of an aircraft includes first and second spacers, each of which is configured to be inserted within a corresponding one of first and second slots disposed in an adjacent rudder pedal housing. A coupling mechanism is configured to couple the first spacer to the second spacer through the rudder pedal housing so as to retain the first and second spacers in corresponding ones of the slots. The lockout mechanism prevents movement of the rudder pedals in a same direction, and hence, movement of the aircraft's rudder.
-
公开(公告)号：US20160083079A1
公开(公告)日：2016-03-24
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.
摘要翻译： 具有冗余定位销和定位板的选档杆以及使用选档杆测试一个或多个定位销故障的方法。 选档杆包括至少两个滑块，用于独立地移动制动板内的止动销。 独立的滑块允许一个止动销保持接合。 只有一个止动销接合，操作员可以测试移动轴的能力并得出结论是否止动销是否失败。
-
公开(公告)号：US20100038493A1
公开(公告)日：2010-02-18
申请号：US12228595
申请日：2008-08-14
申请人： David J. Lang , James M. Regan
发明人： David J. Lang , James M. Regan
IPC分类号： B64C13/14
CPC分类号： B64D45/0005 , B64D2045/001 , F16D2121/22 , F16D2125/38 , F16D2127/12
摘要： An asymmetry brake includes a housing, a shaft, a pilot brake, a primary brake, and a ball ramp assembly. The shaft of the asymmetry brake is rotatable relative to the housing about an axis of rotation. The primary brake is movably connected with the shaft. The pilot brake is configured to selectively engage the housing to generate a triggering torque. The triggering torque is transferred through the ball ramp assembly to the primary brake, which in response engages the housing to generate a braking torque on the shaft. The disposition of the ball ramp assembly between the pilot brake and the primary brake allows the ball ramp assembly to return to an operative non-separated condition when the pilot brake is disengaged from the housing. The return of the ball ramp assembly to the operative non-separated condition allows the primary brake to disengage from the housing which releases the shaft to rotate.
摘要翻译： 不对称制动器包括壳体，轴，先导制动器，主制动器和球道斜坡组件。 不对称制动器的轴可相对于壳体围绕旋转轴线旋转。 主制动器与轴可移动地连接。 先导制动器构造成选择性地接合壳体以产生触发扭矩。 触发扭矩通过滚珠坡道组件传递到主制动器，主制动器响应于壳体以在轴上产生制动转矩。 在先导制动器和主制动器之间的滚珠坡道组件的配置允许滚珠坡道组件在先导制动器从壳体脱离时返回到操作的非分离状态。 将球栅组件返回到操作的非分离状态允许主制动器与释放轴旋转的壳体分离。
-
19.发明申请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：US20050051671A1
公开(公告)日：2005-03-10
申请号：US10657410
申请日：2003-09-08
申请人： Mihailo Djuric
发明人： Mihailo 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的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， 控制表面将负载从一侧平衡到另一侧，而不影响飞行员控制，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：US5911391A
公开(公告)日：1999-06-15
申请号：US878382
申请日：1997-06-18
CPC分类号： B64C13/14 , B60R25/0221 , Y10T70/5717 , Y10T70/5726 , Y10T70/5739 , Y10T70/5889
摘要： A locking apparatus in combination with a locking pin and method for rigidly interlocking a control wheel and the rudder pedals of an aircraft is provided for securing the control surfaces of the aircraft operated by the control wheel and the rudder pedals in a stable position. The locking pin is adapted to be disposed through aligned locking pin receiving holes of the control column and the control panel collar and has a recess formed therein for lockingly receiving a portion of the control column. The locking apparatus includes a pair of control wheel retaining members rigidly connected to one end of a rod member for retainingly engaging the control wheel and a rudder pedal engaging bar rigidly connected to one end of another rod member. The rudder pedal engaging bar is positionable in a V-shaped notch of each of the rudder pedals so as to engage each of the rudder pedals and so as to secure the rudder pedal engaging bar on the rudder pedals. The rod members are disposed in a telescoping relationship with respect to one another and are adjustably securable whereby the control wheel retaining members are rigidly locked in a selected position relative to the rudder pedal retaining bar wherein the control wheel retaining members cooperate with the rudder pedal retaining bar to support the control column in a pin locking position wherein the control column is lockingly disposed in the recess of the locking pin.
摘要翻译： 与锁定销结合的锁定装置和用于将控制轮和飞行器的舵踏板刚性联锁的方法被提供用于将由控制轮和舵踏板操纵的飞行器的控制表面固定在稳定的位置。 锁定销适于通过控制柱和控制面板轴环的对准的锁定销接收孔设置，并且具有形成在其中的凹部，用于锁定地接收控制柱的一部分。 锁定装置包括一对控制轮保持构件，其刚性地连接到杆构件的一端，用于保持接合控制轮和刚性地连接到另一杆构件的一端的舵踏板接合杆。 方向舵踏板接合杆可定位在每个舵踏板的V形槽口中，以便与每个方向舵踏板接合，以便将方向舵踏板接合杆固定在方向舵踏板上。 杆构件相对于彼此以伸缩关系设置并且可调节地固定，由此控制轮保持构件相对于舵踏板保持杆刚性地锁定在选定位置，其中控制轮保持构件与方向舵踏板保持配合 以将控制柱支撑在销锁定位置，其中控制柱被锁定地设置在锁定销的凹部中。
-
-
-
-
-
-
-
-
-
搜索结果
85 条记录 (耗时 0.035 秒)
