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公开(公告)号：US07945425B2
公开(公告)日：2011-05-17
申请号：US12253747
申请日：2008-10-17
申请人： Alan D. Marx , Gary A. Emch , Mark J. Gardner , Richard I. Apfel , Michael E. Renzelmann , Christopher D. Feet , Michael R. Finn , Mark S. Good , Gregory J. Seehusen
发明人： Alan D. Marx , Gary A. Emch , Mark J. Gardner , Richard I. Apfel , Michael E. Renzelmann , Christopher D. Feet , Michael R. Finn , Mark S. Good , Gregory J. Seehusen
IPC分类号： G06F11/30
CPC分类号： B64D45/0005 , B64D2045/001
摘要： A method for detecting freewheeling skew failures in the wing flaps of an aircraft includes measuring the outputs of flap skew sensors when the aircraft is in flight (IF) and the flaps are extended to a selected position, and when the aircraft is next on the ground (OG) and the flaps are extended to the selected position. The respective differences between the IF and OG outputs of symmetrical pairs of the flap skew sensors are computed, and then the respective difference between the computed IF output difference and the computed OG output difference of each symmetrical pair of the sensors is computed. The computed IF and OG difference of each symmetrical pair of the sensors is then compared with each of predetermined maximum and minimum threshold value to determine whether a freewheeling skew failure exists in any of the flaps of the aircraft.
摘要翻译： 一种用于检测飞行器翼片中的续流偏斜故障的方法，包括当飞机处于飞行中（IF）时测量襟翼歪斜传感器的输出，并且襟翼延伸到选定的位置，并且当飞机在地面上时 （OG），并且襟翼延伸到所选位置。 计算襟翼偏斜传感器的对称对的IF和OG输出之间的各自的差异，然后计算计算的IF输出差和每对传感器对的计算的OG输出差的相应差。 然后将每个对称的传感器对的计算的IF和OG差与预定的最大和最小阈值中的每一个进行比较，以确定是否存在飞行器的任何襟翼中的空转歪斜故障。
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公开(公告)号：US20080255713A1
公开(公告)日：2008-10-16
申请号：US11734842
申请日：2007-04-13
申请人： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
发明人： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
摘要： The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity, vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.
摘要翻译： 在给定的飞行阶段期间，在变化的条件下，动态地调整影响机翼弧度的可移动表面，以优化机翼弧度以获得最佳升力/牵引比。 在优选实施例中，附加动态调节控制模块提供用于最终定位后缘可移动表面（即，内侧翼片，外侧翼片，副翼和襟翼）的命令信号，其用于代替标准的预定位置 飞行控制系统。 动态调整控制模块利用改变飞行器条件的输入，如高度，马赫数，重量，重心，垂直速度和飞行阶段。 动态调整控制模块用于重新定位机翼的可移动表面的命令通过标准飞行控制系统传输到用于移动飞行控制表面的致动器。
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13.发明授权公开(公告)号：US07770949B2
公开(公告)日：2010-08-10
申请号：US11923238
申请日：2007-10-24
CPC分类号： E05B47/0046 , B64C1/1469 , B64C2001/009 , Y10T292/096 , Y10T292/1021 , Y10T292/68 , Y10T292/696 , Y10T292/699
摘要： An aircraft door mechanism includes a solenoid connected to a support assembly. The solenoid displaces the latch pin between a solenoid energized and a solenoid de-energized position. A catch assembly rotatably connected to the support assembly is positioned to engage a 3½ degree or less taper portion of the latch pin in the solenoid energized position. When the latch pin moves to the solenoid de-energized position, a latch bolt supported by the door rotates the catch assembly. The latch bolt includes a distal bulbous end which multiplies the force applied to the door to rotate the catch assembly. If the latch pin is extended, a substantially greater force is required to force the latch pin to the solenoid de-energized position owing to the reduced taper of the latch pin. Authorized door entry is therefore easier and unauthorized door entry is made more difficult.
摘要翻译： 飞机门机构包括连接到支撑组件的螺线管。 电磁阀在螺线管通电和螺线管断电位置之间移动闩锁销。 可旋转地连接到支撑组件的卡盘组件被定位成在螺线管激励位置中接合闩锁销的3½度或更小的锥形部分。 当闩锁销移动到螺线管断电位置时，由门支撑的闩锁螺栓使锁扣组件旋转。 闩锁螺栓包括远端球形端，其将施加到门的力相乘以使捕捉组件旋转。 如果闩锁销延伸，则由于闩锁销的锥度减小，所以需要大大的力来将闩锁销强制到螺线管断电位置。 因此，门禁进入更为容易，未经授权的门禁进入更加困难。
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14.发明申请公开(公告)号：US20080135684A1
公开(公告)日：2008-06-12
申请号：US11923238
申请日：2007-10-24
CPC分类号： E05B47/0046 , B64C1/1469 , B64C2001/009 , Y10T292/096 , Y10T292/1021 , Y10T292/68 , Y10T292/696 , Y10T292/699
摘要： An aircraft door mechanism includes a solenoid connected to a support assembly. The solenoid displaces the latch pin between a solenoid energized and a solenoid de-energized position. A catch assembly rotatably connected to the support assembly is positioned to engage a 3½ degree or less taper portion of the latch pin in the solenoid energized position. When the latch pin moves to the solenoid de-energized position, a latch bolt supported by the door rotates the catch assembly. The latch bolt includes a distal bulbous end which multiplies the force applied to the door to rotate the catch assembly. If the latch pin is extended, a substantially greater force is required to force the latch pin to the solenoid de-energized position owing to the reduced taper of the latch pin. Authorized door entry is therefore easier and unauthorized door entry is made more difficult.
摘要翻译： 飞机门机构包括连接到支撑组件的螺线管。 电磁阀在螺线管通电和螺线管断电位置之间移动闩锁销。 可旋转地连接到支撑组件的卡盘组件被定位成在螺线管激励位置中接合闩锁销的3½度或更小的锥形部分。 当闩锁销移动到螺线管断电位置时，由门支撑的闩锁螺栓使锁扣组件旋转。 闩锁螺栓包括远端球形端，其将施加到门的力相乘以使捕捉组件旋转。 如果闩锁销延伸，则由于锁销的锥度减小，所以需要大大的力来迫使闩锁销到螺线管去激励位置。 因此，门禁进入更为容易，未经授权的门禁进入更加困难。
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公开(公告)号：US5201479A
公开(公告)日：1993-04-13
申请号：US828308
申请日：1992-01-30
IPC分类号： B64C3/56
CPC分类号： B64C3/56
摘要： A latch pin and locking system for use in connection with an aircraft having folding wings or wing tips. The system includes a plurality of individual latch pin units, each of which has a pin that is hydraulically driven in extension and retraction. When extended, the pins cooperatively lock wing tip hinge structure which prevents wing tip folding movement. Each latch pin unit has a locking body that prevents pin retraction of its respective pin after extension thereof for wing tip locking. The locking bodies of all of the latch pin units are drivingly interlinked, so that all lock and/or unlock as a single network. The network is driven by a single power drive unit. In the event any one locking body in the network fails, the network is broken, and thereby provides an indication that maintenance is required.
摘要翻译： 用于与具有折叠翼或翼尖的飞行器相关联的闩锁销和锁定系统。 该系统包括多个单独的销销单元，每个单独的销销单元具有以伸缩方式液压驱动的销。 当延伸时，销钉协同锁定翼尖铰链结构，防止翼尖折叠运动。 每个闩锁销单元具有锁定体，该锁定体在其延伸之后防止其相应销的销缩回用于翼尖锁定。 所有闩锁销单元的锁定体被驱动地互连，使得所有锁定和/或解锁为单个网络。 网络由单个驱动单元驱动。 如果网络中的任何一个锁定主体出现故障，网络都将断开，从而提供维护所需的指示。
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