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公开(公告)号：US20240271695A1
公开(公告)日：2024-08-15
申请号：US18169316
申请日：2023-02-15
申请人： The Boeing Company
发明人： Christopher J. Heiberg , Dong Ngo
CPC分类号： F16H57/0498 , B64C13/34 , F16H1/16 , F16H55/22 , F16H57/0423 , F16H57/0427
摘要： Methods and apparatus to passively lubricate a worm gear assembly are disclosed herein. An example worm gear assembly includes a housing defining an internal cavity, a worm gear in the internal cavity of the housing, and a worm wheel in the internal cavity of the housing. The worm wheel is meshed with the worm gear. The worm wheel includes a first side surface, a second side surface opposite the first side surface, a peripheral edge with a plurality of teeth between the first side surface and the second side surface, and a vane on the first side surface. The vane extends radially between a center of the first side surface and the peripheral edge. The vane is to move lubricant from a bottom of the housing to the worm gear to lubricate an interface between the worm gear and the worm wheel.
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公开(公告)号：US20240092484A1
公开(公告)日：2024-03-21
申请号：US18450097
申请日：2023-08-15
发明人： Jun Ho CHO , Myeong Kyu LEE , Seong Wook CHOI
CPC分类号： B64C29/0033 , B64C13/30 , B64C13/34
摘要： A tilt prop aircraft is provided, including a first longeron and a second longeron capable of tilting relatively to each other, a tilt actuator disposed on the second longeron, a first power transmission member rotated by the tilt actuator, a second power transmission member fixed to the first longeron and coupled to the first power transmission member to transmit a rotational movement of the first power transmission member by turning 90 degrees in different planes, a crank fixed to the second longeron and extending through a slot in the first longeron and protruding inwardly from the first longeron, and a connecting rod connected to the crank so as to be relatively rotatable to the crank, and connected to the pitch control rod.
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公开(公告)号：US11781625B2
公开(公告)日：2023-10-10
申请号：US17420436
申请日：2020-02-24
申请人： MOOG INC.
CPC分类号： F16H35/00 , B64C13/34 , F16H2035/006
摘要： A stop module for non-jamming end-of-stroke stoppage of a rotary drive actuator includes timing gears to articulate a stopping pawl, and a low inertia, deformable stopping disk arranged to safely dissipate excess rotational kinetic energy of the rotary actuator. The stop module does not rely on friction to stop and dissipate the excess kinetic energy, but instead relies on predictable deformation of a metallic stopping disk which may be provided in a stopping cartridge of the stop module. Use of a deformable element to dissipate excess energy allows the disclosed stop module to be lighter and smaller than conventional end-of-stroke stopping mechanisms.
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公开(公告)号：US11780564B2
公开(公告)日：2023-10-10
申请号：US17487798
申请日：2021-09-28
发明人： Benjamin Bishop , Anthony Bryant
摘要： A spoiler for an aircraft wing is movable between a stowed configuration and a deployed configuration in a “pop-up” manner. The spoiler includes a hinged top flap movable between a first position and a second position, wherein in the first position the hinged top flap is constrained by an actuator, and in the second position the hinged top flap is unconstrained by the actuator. When the hinged top flap is in the second position, airflow over the top surface of the aircraft wing acts to pull the spoiler into the deployed position.
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公开(公告)号：US11767100B2
公开(公告)日：2023-09-26
申请号：US17449144
申请日：2021-09-28
发明人： Benjamin Bishop , Anthony Bryant
摘要： An aircraft wing with a wing structure and a spoiler movable between a stowed configuration and a deployed configuration are disclosed. The spoiler includes an actuator configurable between an engaged mode and a disengaged mode. When the actuator is in the engaged mode, the actuator can restrict movement of the spoiler and move the spoiler between the stowed configuration and deployed configuration. In the disengaged mode, the actuator allows free movement of the spoiler, such that the spoiler may pop up due to reduced air pressure on the aircraft wing.
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公开(公告)号：US20230249804A1
公开(公告)日：2023-08-10
申请号：US17668140
申请日：2022-02-09
申请人： The Boeing Company
发明人： Kevin Raylin Tsai
摘要： Actuated assemblies comprise a base object, an actuated object, a rotary actuator, and a joint. The rotary actuator is configured to selectively pivot the actuated object relative to the base object. The rotary actuator comprises a housing that is operatively coupled to the base object, and an output gear that is configured to be selectively rotated relative to the housing. The joint comprises a crowned spline and a joint spherical bearing. The crowned spline is meshed with the output gear of the rotary actuator and is fixed relative to the actuated object. The joint spherical bearing comprises an outer race that is fixed relative to the base object, and an inner race that is positioned for rotational and pivotal movement within the outer race and that is fixed relative to the crowned spline.
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公开(公告)号：US11713108B2
公开(公告)日：2023-08-01
申请号：US17494217
申请日：2021-10-05
发明人： Derick S. Balsiger , Keith Bloxham
CPC分类号： B64C13/34 , B64C9/00 , B64C13/50 , F16H19/08 , B64C2009/005
摘要： A hinge-line actuator has: a drive shaft; first and second ground gears spaced apart along the drive shaft, wherein the first and second output gears include first and second contoured outer gear surfaces; and an output gear disposed on the drive shaft and disposed between the first and second ground gears, wherein the output gear includes a third contoured outer gear surface; an actuator housing that includes: contoured first, second and third gear seats that, respectively, seat the first, second and third outer gear surfaces.
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公开(公告)号：US10017243B2
公开(公告)日：2018-07-10
申请号：US14034946
申请日：2013-09-24
申请人： The Boeing Company
发明人： Matthew A. Moser , Michael R. Finn
摘要： An adaptive trailing edge system for an aircraft may include an adaptive trailing edge element mounted to a trailing edge. An electric motor actuator having an electric motor may be configured to actuate the adaptive trailing edge element. A linkage system may couple the electric motor actuator to the adaptive trailing edge element for actuation thereof.
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公开(公告)号：US20160223038A1
公开(公告)日：2016-08-04
申请号：US14611649
申请日：2015-02-02
申请人： The Boeing Company
发明人： Robert M. Murphy
CPC分类号： F16D67/00 , B64C13/28 , B64C13/34 , F16D65/186 , F16D2125/36 , F16D2127/005 , Y02T50/44
摘要： Provided are half system torque brakes, aircraft utilizing these brakes, and methods of installing these brakes. A half system torque brake includes an input cam assembly slidably disposed on a compression shaft between first and second output cam assemblies. The second output cam assembly is disposed between the input cam assembly and a rotor-stator assembly. When a torque differential between the input cam assembly and either one of the output cam assemblies exceeds its threshold, the same rotor-stator assembly is engaged and prevents further rotation of any cam assembly. Specifically, when the torque differential corresponding to the first output cam assembly exceeds its threshold, this assembly advances away from the input cam assembly and pulls the compression shaft in the same direction, which in turn engages the rotor-stator assembly by advancing the pressure plate to the second output cam assembly. The second output cam engages the rotor-stator assembly directly.
摘要翻译： 提供半系统扭矩制动器，利用这些制动器的飞机以及安装这些制动器的方法。 半系统扭矩制动器包括可滑动地设置在第一和第二输出凸轮组件之间的压缩轴上的输入凸轮组件。 第二输出凸轮组件设置在输入凸轮组件和转子 - 定子组件之间。 当输入凸轮组件和输出凸轮组件中的任一个之间的转矩差超过其阈值时，相同的转子 - 定子组件被接合并防止任何凸轮组件进一步旋转。 具体地说，当对应于第一输出凸轮组件的扭矩差异超过其阈值时，该组件从输入凸轮组件前进，并沿同一方向拉动压缩轴，该相反方向通过使压板前进而接合转子 - 定子组件 到第二输出凸轮组件。 第二输出凸轮直接接合转子 - 定子组件。
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公开(公告)号：US20160221694A1
公开(公告)日：2016-08-04
申请号：US15009242
申请日：2016-01-28
发明人： Jan Haserodt
摘要： A method for adjusting play in a high-lift system of an aircraft with several flaps, moved by a drive unit with the aid of driving stations connected to a driveshaft, includes disengaging the mechanical connections between the driveshaft and the driving stations in the first position, displacing the individual drive levers by mechanically driving a gear input of the associated rotary actuator such that the individual drive levers come into mechanical contact with a stop in a second position, spaced apart from the first position, and are pretensioned by a certain torque, rotationally fixing the gear inputs of the rotary actuators, adapting the length of connecting links between the respective drive levers and a support arm carrying the associated flap such that a position of the associated flap corresponding to the position of the stop is reached, and reconnecting the driving stations to the driveshaft pretensioned to have no play.
摘要翻译： 一种用于在具有多个翼片的飞行器的高升力系统中调节作用的方法，其借助于连接到驱动轴的驱动站由驱动单元移动，包括在第一位置分离驱动轴与驱动站之间的机械连接 通过机械地驱动相关联的旋转致动器的齿轮输入来移动单个驱动杆，使得各个驱动杆在与第一位置间隔开的第二位置中与止动件机械接触，并且以一定的扭矩预张紧， 旋转地固定旋转致动器的齿轮输入，使相应驱动杆之间的连接连杆的长度与承载相关翼片的支撑臂相匹配，使得相应的挡板的位置对应于止挡件的位置，并重新连接 驱动车站到驱动轴预张力不起来。
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