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1. 发明授权

US12116109B2 Aerodynamic control surface 有权
公开(公告)号：US12116109B2
公开(公告)日：2024-10-15
申请号：US17993176
申请日：2022-11-23
申请人： AIRBUS OPERATIONS LIMITED
发明人： Daren Healy
IPC分类号： B64C13/38 , B64C1/00 , B64C9/10 , B64C21/08
CPC分类号： B64C13/38 , B64C1/0009 , B64C9/10 , B64C21/08
摘要： An aerodynamic control surface assembly includes a structure (2) with an aerodynamic surface (8) and a curved aerodynamic control surface (20) configured to move between an extended (24) and a retracted position (22). The aerodynamic control surface is arranged to deploy through an aperture (18) in the aerodynamic surface and into an oncoming airflow (A). An actuation mechanism (52, 152, 252) coupled to the aerodynamic control surface (20) moves the aerodynamic control surface (20) between extended and retracted positions. The actuation mechanism (52, 152, 252) is configured such that the control surface (20) follows a curved kinematic path (40, 140, 240) as the control surface moves between the extended (24) and retracted positions (22). The actuation mechanism (52, 152, 252) remains fully behind the aerodynamic surface (8) throughout the movement of the aerodynamic control surface (20) between the extended (24) and retracted positions (22).

2. 发明申请

US20180082499A1 METHOD OF DETECTING ELEVATOR TAB FAILURE 审中-公开
公开(公告)号：US20180082499A1
公开(公告)日：2018-03-22
申请号：US15810587
申请日：2017-11-13
申请人： UNITED AIRLINES, INC.
发明人： Paul Bowman , Ryan Nurnberger
IPC分类号： G07C5/08 , B64C13/40
CPC分类号： G07C5/0816 , B64C9/10 , B64C9/12 , B64C13/42 , B64D45/00 , B64D45/0005
摘要： A method is provided for verifying proper operation of a left elevator tab disposed at an end portion of a left elevator of an aircraft and a right elevator tab disposed at an end portion of a right elevator of the aircraft. Because proper operation of the elevator tabs cannot be directly verified by existing aircraft instrument, the operation of the elevator tabs can be indirectly verified by analyzing flight data of the aircraft. After identification of a verification event, in which the elevator tabs move relative to the elevators, the positions of the left elevator and right elevator can be measured, and differences in the positions of the left elevator and right elevator can indicate proper operation of the left and right elevator tabs.

3. 发明申请

US20170301155A1 METHOD OF DETECTING ELEVATOR TAB FAILURE 有权
公开(公告)号：US20170301155A1
公开(公告)日：2017-10-19
申请号：US15099547
申请日：2016-04-14
申请人： UNITED AIRLINES, INC.
发明人： Paul Bowman , Ryan Nurnberger
IPC分类号： G07C5/08 , B64C13/40 , B64D45/00
CPC分类号： G07C5/0816 , B64C9/10 , B64C9/12 , B64C13/40 , B64C13/42 , B64D45/00 , B64D45/0005 , B64D2045/0085
摘要： A method is provided for verifying proper operation of a left elevator tab disposed at an end portion of a left elevator of an aircraft and a right elevator tab disposed at an end portion of a right elevator of the aircraft. Because proper operation of the elevator tabs cannot be directly verified by existing aircraft instrument, the operation of the elevator tabs can be indirectly verified by analyzing flight data of the aircraft. After identification of a verification event, in which the elevator tabs move relative to the elevators, the positions of the left elevator and right elevator can be measured, and differences in the positions of the left elevator and right elevator can indicate proper operation of the left and right elevator tabs.

4. 发明授权

US09580168B2 Cove lip door slaved to trailing edge control device 有权
标题翻译：椰子唇门从属于后缘控制装置
公开(公告)号：US09580168B2
公开(公告)日：2017-02-28
申请号：US14577873
申请日：2014-12-19
申请人： The Boeing Company
发明人： Matthew D M Fevergeon , Jan A. Kordel , Victor Liu
IPC分类号： B64C9/04 , B64C9/02 , B64C9/10 , B64C9/16 , B64C9/18 , B64C13/28 , B64C9/00
CPC分类号： B64C9/04 , B64C9/02 , B64C9/10 , B64C9/16 , B64C9/18 , B64C13/28 , B64C2009/005 , Y02T50/32
摘要： A primary flight control device for an aircraft, such as a flaperon attached to an aircraft wing, utilizes independent yet interactive airgap control systems designed to avoid weight penalties associated with conventionally used cam and track systems. An actuator directly controls movements of the flaperon; the flaperon motion is then used to slave separate movements of secondary flight control devices, such as a flaperon hinge panel and a cove lip door, to various positions of the flaperon for indirect control of aerodynamic air gaps during flight. The use of a bell crank for indirectly slaving the flaperon hinge panel movements to the flaperon avoids conventionally used cam and track systems. Although the cove lip door utilizes a separate linkage system, the bell crank and cove lip door linkage systems work in conjunction to assure desired aerodynamic airflows over the aircraft wing and flaperon structures.
摘要翻译：用于飞机的主要飞行控制装置，例如连接到飞行器机翼的襟副翼，利用独立但交互式的气隙控制系统，设计用于避免与常规使用的凸轮和轨道系统相关的重量损失。致动器直接控制襟副翼的运动; 襟副翼运动然后被用于将辅助飞行控制装置（例如襟翼铰链板和海湾唇门）的单独运动从属于襟副翼的各个位置，以间接控制飞行中空气动力学气隙。使用钟形曲柄间接地使襟副翼铰链板移动到襟副翼，避免了常规使用的凸轮和轨道系统。虽然椰腔唇门采用单独的连杆系统，但是曲拐和小腹唇门联动系统协同工作，以确保飞机机翼和襟副翼结构上所需的空气动力学气流。

5. 发明授权

US08876063B2 Flight control using multiple actuators on primary control surfaces with tabs 有权
标题翻译：使用多个执行器在主控制面上进行飞行控制
公开(公告)号：US08876063B2
公开(公告)日：2014-11-04
申请号：US11953567
申请日：2007-12-10
申请人： James J. Sheahan, Jr. , Charles E. Morris , Jeffrey M. Roach
发明人： James J. Sheahan, Jr. , Charles E. Morris , Jeffrey M. Roach
IPC分类号： B64C9/10
CPC分类号： B64C9/10
摘要： A flight control system for an aircraft directs a primary surface that is pivotable with respect to the aircraft with a moveable tab located at the end of the primary surface. A primary surface actuator maintains a position of the primary surface. A tab actuator moves the tab with respect to the primary flight control surface. A controller configured to coordinate the movement of the primary flight control surface with the movement of the tab by deflecting the tab with respect to the primary flight control surface, thereby allowing aerodynamic forces acting upon the deflected tab to position the primary flight control surface at a desired position. The primary flight control surface can then be maintained at the desired position by the primary surface actuator.
摘要翻译：用于飞行器的飞行控制系统引导主表面，该主表面可相对于飞行器枢转，具有位于主表面的端部的可移动的突片。主表面致动器保持主表面的位置。翼片致动器相对于主飞行控制表面移动翼片。控制器，被配置为通过相对于主飞行控制表面偏转翼片来协调主飞行控制表面与翼片的移动的移动，从而允许作用在偏转翼片上的空气动力力将主飞行控制表面定位在所期望的职位。然后，主飞行控制表面可以由主表面致动器保持在期望的位置。

6. 发明授权

US07954769B2 Deployable aerodynamic devices with reduced actuator loads, and related systems and methods 有权
标题翻译：减少执行器负载的可部署空气动力装置，以及相关系统和方法
公开(公告)号：US07954769B2
公开(公告)日：2011-06-07
申请号：US11953672
申请日：2007-12-10
申请人： Glenn S. Bushnell
发明人： Glenn S. Bushnell
IPC分类号： B64C3/58 , B64C9/00
CPC分类号： B64C9/10 , B64C9/02 , B64C9/32 , B64C9/323 , B64C9/34 , B64C13/38 , Y02T50/32 , Y02T50/44
摘要： Deployable aerodynamic devices with reduced actuator loads, and related systems and methods are disclosed. An external flow system in accordance with a particular embodiment includes an external flow body, a deployable device carried by and movable relative to the external flow body, and a coupling connected between the external flow body and the deployable device. The system can further include an actuator device operatively coupled between the external flow body and the deployable device, with the actuator device positioned to move the deployable device along a motion path between a stowed position and the deployed position. The motion path can have a first portion over which the load delivered by the actuator device increases as the deployed device moves toward the deployed position, and a second portion over which the load delivered by the actuator device decreases as the deployed device moves toward the deployed position.
摘要翻译：公开了具有减少的致动器负载的可部署的空气动力学装置以及相关的系统和方法。根据特定实施例的外部流动系统包括外部流动体，由外部流动体承载并可移动的可展开装置，以及连接在外部流动体和可部署装置之间的联接器。该系统还可以包括可操作地联接在外部流动体和可展开装置之间的致动器装置，致动器装置被定位成沿着收起位置和展开位置之间的运动路径移动可展开装置。运动路径可以具有第一部分，当被展开的装置朝向展开位置移动时，致动器装置输送的负载增加;以及第二部分，当被展开的装置朝向展开位置移动时，由致动装置输送的负载减小位置。

7. 发明授权

US5913492A System for controlling an aircraft control surface tab 失效
标题翻译：用于控制飞机控制表面标签的系统
公开(公告)号：US5913492A
公开(公告)日：1999-06-22
申请号：US855190
申请日：1997-05-13
申请人： Michel Durandeau , Etienne Foch
发明人： Michel Durandeau , Etienne Foch
IPC分类号： B64C9/10 , B64C9/04
CPC分类号： B64C9/10
摘要： A system for controlling the tab (6) of an aircraft control surface (3) having a pair of position sensors (12 and 15) that supply information regarding the turning of the control surface (3) and the position of a jack (13), respectively, on the basis of signals generated by the sensors (12 and 15) as well as possibly on the basis of at least one parameter (p) originating from the aircraft, such as airspeed, positions of lift-augmenting devices, forces exerted by the pilot on a control, etc., and which formulates a command for the jack (13).
摘要翻译：一种用于控制飞行器控制表面（3）的突片（6）的系统，具有一对位置传感器（12和15），所述位置传感器提供关于控制表面（3）的转动和插孔（13）的位置的信息，分别基于由传感器（12和15）产生的信号，以及可能基于来自飞行器的至少一个参数（p），例如空速，升力增强装置的位置，施加的力由飞行员进行控制等，并且制定用于千斤顶（13）的命令。

8. 发明授权

US5823471A System for controlling a control surface articulated to a structure of a vehicle 失效
标题翻译：用于控制铰接到车辆结构的控制表面的系统
公开(公告)号：US5823471A
公开(公告)日：1998-10-20
申请号：US688095
申请日：1996-07-29
申请人： Francis Dazet
发明人： Francis Dazet
IPC分类号： B64C9/10 , B64C13/30 , B64C13/04
CPC分类号： B64C13/30 , B64C9/10 , Y10T74/18856 , Y10T74/18944 , Y10T74/20636
摘要： A system for controlling a control surface articulated to a structure of a vehicle about a first axis includes a tab articulated to the trailing edge of the control surface about a second axis parallel to the first axis, an elastic link provided between the control surface and the tab, a pilot input control mechanism to which the elastic link is connected and which acts on the tab, and an actuating member provided between the control surface and the link for keeping the tab/control surface assembly in any position whatever. The elastic link and the actuating member are arranged to be at least substantially parallel to the first axis of articulation of the control surface. The first axis is disposed near, and upstream from, the elastic link and the actuating member.
摘要翻译：用于控制围绕第一轴线铰接到车辆结构的控制表面的系统包括：关于平行于第一轴线的第二轴线连接到控制表面的后缘的突片，设置在控制表面和弹簧连杆被连接并作用在翼片上的先导输入控制机构以及设置在控制表面和连杆之间的致动构件，用于将翼片/控制面组件保持在任何位置。弹性连杆和致动构件布置成至少基本上平行于控制表面的第一铰接轴。第一轴设置在弹性连杆和致动件附近和上游。

9. 发明授权

US4043523A Apparatus for aircraft pitch trim 失效
标题翻译：飞机螺距调整装置
公开(公告)号：US4043523A
公开(公告)日：1977-08-23
申请号：US665833
申请日：1976-03-11
申请人： Otto E. Bartoe, Jr.
发明人： Otto E. Bartoe, Jr.
IPC分类号： B64C5/16 , B64C9/10 , B64C13/30
CPC分类号： B64C13/30 , B64C5/16 , B64C9/10
摘要： Apparatus for providing extreme pitch trim configurations for aircraft capable of flying at low-speeds, and particularly aircraft having blown primary lift-producing surfaces. The apparatus includes a movable horizontal stabilizer to provide pitch trim and an elevator pivotally attached to the horizontal stabilizer to provide transient pitch control. Control of the elevator movement is provided by a control tube extending from a horn attached to the elevator to a bell crank member attached to the horizontal stabilizer. The bell crank is also connected to a push tube movably attached to the airframe and arranged to be aligned with the pivot axis of the horizontal stabilizer in the neutral position. Thus, the horizontal stabilizer may be pivoted around its mounting axis to provide substantial pitch trim while concurrently maintaining the range and symmetry of elevator movement.
摘要翻译：用于为能够以低速飞行的飞机提供极端俯仰装置配置的设备，特别是具有吹出的主升力产生表面的飞机。该装置包括可移动的水平稳定器以提供俯仰修剪和枢转地附接到水平稳定器的电梯以提供瞬时俯仰控制。电梯运动的控制由从附接到电梯的喇叭延伸到连接到水平稳定器的钟形曲柄构件的控制管提供。钟形曲柄还连接到可移动地附接到机身并且布置成在水平稳定器的枢转轴线处于中立位置的推动管。因此，水平稳定器可围绕其安装轴线枢转以提供实质的俯仰修剪，同时保持电梯运动的范围和对称性。

10. 发明授权

US3369781A Aircraft flight control system 失效
公开(公告)号：US3369781A
公开(公告)日：1968-02-20
申请号：US60082866
申请日：1966-12-12
申请人： NORTH AMERICAN ROCKWELL
发明人： CICHY DANIEL R , DENNISTON JAMES L , MACKAY JAMES K L
IPC分类号： B64C9/10 , B64C13/00 , B64C13/30
CPC分类号： B64C13/30 , B64C9/10 , B64C13/00

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