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1. 发明申请

US20180244366A1 Structural Arrangement and Method of Fabricating a Composite Trailing Edge Control Surface 审中-公开
公开(公告)号：US20180244366A1
公开(公告)日：2018-08-30
申请号：US15957536
申请日：2018-04-19
申请人： The Boeing Company
发明人： David C. Reusch
IPC分类号： B64C9/00 , B64C9/02 , B29C70/30 , B64C3/20 , B64C9/12 , B64F5/10
CPC分类号： B64C9/00 , B29C70/30 , B29C2793/0081 , B64C3/20 , B64C9/02 , B64C9/12 , B64C2009/005 , B64F5/10 , Y02T50/43
摘要： A composite trailing edge control surface includes a contiguous one-piece composite control surface skin wrapped around a plurality of stiffening cores, a plurality of hinge fittings, and a plurality of substantially parallel ribs. The contiguous one-piece composite control surface skin provides a control surface on opposing sides of the trailing edge control surface and substantially distributes bending, shear and torsion loads of the trailing edge control surface to the plurality of hinge fittings and the plurality of substantially parallel ribs. A method of manufacturing the trailing edge control surface includes positioning a contiguous one-piece composite control surface skin on a substantially flat tool. A plurality of stiffener cores having a plurality of thin covering skins are positioned on the contiguous one-piece composite control surface skin and are cured to create a laminate sandwich composite structure skin that is trimmed and has fastener apertures and hinge fitting access apertures provided there-through.

2. 发明授权

US09824513B2 Method of detecting elevator tab failure 有权
公开(公告)号：US09824513B2
公开(公告)日：2017-11-21
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： G06F19/00 , G07C5/08 , B64D45/00 , B64C13/40
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.

3. 发明授权

US09688384B1 Methods and apparatus to control a gap between movable aircraft wing components 有权
公开(公告)号：US09688384B1
公开(公告)日：2017-06-27
申请号：US13623597
申请日：2012-09-20
申请人： Michael A. Balzer , Jan A. Kordel
发明人： Michael A. Balzer , Jan A. Kordel
IPC分类号： B64C3/50 , B64C9/02 , B64C9/16 , B64C13/28 , B64C7/00
CPC分类号： B64C3/50 , B64C7/00 , B64C9/02 , B64C9/12 , B64C9/16 , B64C13/28
摘要： Methods and apparatus to control a gap between movable aircraft wing components are disclosed. An example apparatus includes a body having a trailing edge and a leading edge. The leading edge is to be coupled to an aircraft wing. The trailing edge is to engage a flap of the aircraft wing. The body includes a structure located between the trailing edge and the leading edge. The structure is to engage the flap to maintain a distance between the body and the flap.

4. 发明申请

US20160229522A1 CLOSED LOOP CONTROL OF AIRCRAFT CONTROL SURFACES 有权
标题翻译：飞机控制表面闭环控制
公开(公告)号：US20160229522A1
公开(公告)日：2016-08-11
申请号：US14330824
申请日：2014-07-14
申请人： THE BOEING COMPANY
发明人： Abraham J. Pachikara , Matthew A. Moser , Paul H. Carpenter , Michael R. Finn , Thomas S. Koch , Stefan R. Bieniawski , Brian T. Whitehead
IPC分类号： B64C13/16 , B64C9/00 , B64D45/00 , B64C3/44
CPC分类号： B64C13/16 , B64C3/44 , B64C9/00 , B64C9/12 , B64D45/0005 , G05D1/0825 , Y02T50/32 , Y02T50/44
摘要： Closed loop control of control surfaces is described herein. One disclosed example method includes measuring a flight metric of an aircraft during flight and calculating, using a processor, a deflection of a control surface of the aircraft based on the flight metric. The disclosed example method also includes adjusting the deflection to an effective deflection level based on the calculated deflection to reduce a drag coefficient of the aircraft.
摘要翻译：这里描述了控制表面的闭环控制。一个公开的示例性方法包括在飞行期间测量飞行器的飞行量度，并且使用处理器根据飞行量度来计算飞行器的控制表面的偏转。所公开的示例性方法还包括基于所计算的偏转将偏转调整到有效偏转水平以减少飞行器的阻力系数。

5. 发明授权

US09090325B1 Supplementary control surface structure for airplanes 有权
标题翻译：飞机辅助控制面结构
公开(公告)号：US09090325B1
公开(公告)日：2015-07-28
申请号：US14503345
申请日：2014-09-30
申请人： Ahmad Abdullah Al-Jassem Qanaei
发明人： Ahmad Abdullah Al-Jassem Qanaei
IPC分类号： B64C9/00 , B64C9/02 , B64C5/06 , B64C9/12
CPC分类号： B64C9/02 , B64C5/06 , B64C9/00 , B64C9/12
摘要： A supplementary control surface structure for airplanes is installed atop the fuselage of an airplane to enhance the roll rate of the airplane and thereby assists in reducing bending loads on the wings by enabling a smaller aileron deflection for a given roll rate. The supplementary control surface structure desirably includes a moveable vertically oriented roll control surface member desirably installed in a vertically oriented fin or strake that extends atop the fuselage from the flight deck to the vertically oriented tail fin. The supplementary control surface structure is desirably interconnected with the conventional aileron controls of the airplane in order to operate in concert with the ailerons. The supplementary control surface structure is also adaptable to other roll control systems, such as spoilers and wing warping.
摘要翻译：用于飞机的辅助控制表面结构安装在飞机机身的顶部，以提高飞机的滚动速度，从而通过在给定的滚动速率下实现较小的副翼偏转来帮助减少机翼上的弯曲载荷。辅助控制表面结构理想地包括可移动的垂直定向的辊控制表面构件，其期望地安装在垂直定向的翅片或板条上，该机翼在机身顶部从飞行甲板延伸到垂直定向的尾翼。辅助控制表面结构理想地与飞机的常规副翼控制相互连接，以便与副翼协同工作。补充控制表面结构也适用于其他侧倾控制系统，例如扰流板和机翼翘曲。

6. 发明申请

US20150083852A1 VARIABLE CAMBER FLAP SYSTEM AND METHOD 有权
标题翻译：可变的CAMAP襟翼系统和方法
公开(公告)号：US20150083852A1
公开(公告)日：2015-03-26
申请号：US14034940
申请日：2013-09-24
申请人： The Boeing Company
发明人： Matthew A. Moser , Michael R. Finn , Mark J. Gardner , Mark S. Good , Sarah A. Jones
IPC分类号： B64C13/34
CPC分类号： B64C13/34 , B64C3/50 , B64C9/06 , B64C9/12 , B64C9/14 , B64C13/26 , Y02T50/32
摘要： A variable camber system for an aircraft may include a variable camber trim unit (VCTU) positioned between an inboard device and an outboard device. The inboard device and the outboard device may be mounted to at least one of a leading edge and a trailing edge of a wing. The VCTU may include a speed sum gearbox having an inboard shaft coupled to the inboard device and an outboard shaft coupled to the outboard device. The VCTU may additionally include a VCTU electric motor engaged to the speed sum gearbox. The VCTU electric motor may be selectively operable in conjunction with the speed sum gearbox to rotate the outboard shaft independent of the inboard shaft in a manner causing the outboard device to be actuated independent of the inboard device.
摘要翻译：用于飞行器的可变外倾角系统可以包括位于内侧装置和外侧装置之间的可变外倾角装置单元（VCTU）。内侧装置和外侧装置可以安装到机翼的前缘和后缘中的至少一个。 VCTU可以包括速度和齿轮箱，其具有联接到内侧装置的内侧轴和联接到外侧装置的外侧轴。 VCTU可以另外包括接合到速度和齿轮箱的VCTU电动机。 VCTU电动机可以选择性地与速度总和齿轮箱一起操作，以独立于内侧轴旋转外侧轴，使得外部装置独立于内侧装置被致动。

7. 发明申请

US20130020432A1 SYSTEM AND METHOD FOR AN AIR VEHICLE 有权
标题翻译：空气动力学系统与方法
公开(公告)号：US20130020432A1
公开(公告)日：2013-01-24
申请号：US13552263
申请日：2012-07-18
申请人： Itzhak YOGEV , Michael SHEPSHELOVICH , Danny ABRAMOV
发明人： Itzhak YOGEV , Michael SHEPSHELOVICH , Danny ABRAMOV
IPC分类号： B64C9/32 , B64C15/02 , B64C9/06
CPC分类号： B64C9/12 , B64C9/323 , B64C9/326 , B64C15/02 , Y02T50/32
摘要： A method for providing a controllable side force to an air vehicle having a vertical stabilizer arrangement includes (a) selectively causing the vertical stabilizer arrangement to generate a first side force in a first side direction to provide the controllable side force, the first side force inducing a corresponding first yaw moment in a first yaw direction; and (b) selectively providing to the air vehicle a second yaw moment in a second yaw direction, the second yaw moment being induced by a force component of an auxiliary force applied to the air vehicle, the force component being in a force direction that is non-parallel with respect to the first side direction and the force component being spaced from a center of gravity of the air vehicle; wherein the second yaw direction is opposed to the first yaw direction. Also disclosed is a corresponding auxiliary yaw generating system.
摘要翻译：一种用于向具有垂直稳定器装置的机动车辆提供可控侧力的方法包括：（a）选择性地使垂直稳定器装置在第一侧方向上产生第一侧力以提供可控的侧向力，第一侧向力在第一偏转方向上相应的第一横摆力矩; 以及（b）选择性地向所述空中交通工具提供在第二偏转方向上的第二横摆力矩，所述第二横摆力矩由施加到所述空中车辆的辅助力的力分量感应，所述力分量处于相对于第一侧方向不平行，并且力分量与空中交通工具的重心间隔开; 其中所述第二偏转方向与所述第一偏转方向相对。还公开了相应的辅助偏航产生系统。

8. 发明授权

US08191820B1 Flying wing aircraft 有权
标题翻译：飞翼飞机
公开(公告)号：US08191820B1
公开(公告)日：2012-06-05
申请号：US12001218
申请日：2007-12-11
申请人： Bryan Wayne Westra , Roxanne Marie Sato , Douglas Ellwood Shultz , James Franklin Kerswell , Perry Bruce Petersen , Scott Walter Collins
发明人： Bryan Wayne Westra , Roxanne Marie Sato , Douglas Ellwood Shultz , James Franklin Kerswell , Perry Bruce Petersen , Scott Walter Collins
IPC分类号： B64C39/10 , B64C5/04 , B64C5/12 , B64C21/04
CPC分类号： B64C39/10 , B64C5/12 , B64C9/12 , B64C21/04 , B64C21/08 , B64C39/12 , B64D27/20 , Y02T50/166
摘要： The invention is an aircraft that includes a flying wing having a plurality of extendable flaps mounted on the trailing edge of the flying wing. A canard is mounted on the nose of said flying wing. A system is mounted in the flying wing for providing high pressure air over the canard and the flaps. A second system is provided for controlling the flow of air over the canard to provide pitch control of the aircraft.
摘要翻译：本发明是一种飞行器，其包括具有安装在飞翼的后缘上的多个可延伸翼片的飞翼。鸭子安装在飞行翼的鼻子上。系统安装在飞翼中，用于在鸭舌和襟翼上提供高压空气。提供了一种第二系统，用于控制在鸭子上的空气流动，以提供飞行器的俯仰控制。

9. 发明授权

US06863242B2 Method and system for controlling an aircraft control surface 有权
标题翻译：用于控制飞机控制面的方法和系统
公开(公告)号：US06863242B2
公开(公告)日：2005-03-08
申请号：US10631009
申请日：2003-07-31
申请人： Marc Van De Kreeke , Guillaume Cassein
发明人： Marc Van De Kreeke , Guillaume Cassein
IPC分类号： B64C9/12 , B64C13/50 , B64C9/06
CPC分类号： B64C9/12 , B64C13/503
摘要： A system for controlling an aircraft control surface may include a control surface having at least two control surface elements mounted to rotate about an axis on a stabilizer element of the aircraft. An actuator with at least two actuating devices moves the control surface elements according to individual turn commands. Also, a first device determines a particular phase of flight of the aircraft. When the particular phase of flight is determined to exist by the first device, a second device generates differentiated individual turn commands for the actuating devices, according to an overall turn command received from a control unit, to provide prioritized control of the control surface element that generates the lowest force on the stabilizer element.
摘要翻译：用于控制飞机控制表面的系统可以包括具有至少两个控制表面元件的控制表面，所述至少两个控制表面元件被安装成围绕飞行器的稳定器元件上的轴线旋转。具有至少两个致动装置的致动器根据各个转动指令移动控制表面元件。此外，第一装置确定飞机的特定飞行阶段。当飞行的特定阶段被第一装置确定为存在时，第二装置根据从控制单元接收到的整体转向命令，为致动装置产生不同的单独转弯命令，以提供控制表面元件的优先控制，在稳定器元件上产生最小的力。

10. 发明授权

US06241183B1 Method for controlling an aeroplane control surfaces to counter ground lateral drift 有权
标题翻译：控制飞机控制面以抵抗地面横向漂移的方法
公开(公告)号：US06241183B1
公开(公告)日：2001-06-05
申请号：US09341292
申请日：1999-09-14
申请人： Gérard Mathieu
发明人： Gérard Mathieu
IPC分类号： B64C1300
CPC分类号： G05D1/0204 , B64C9/12 , B64C13/16 , G05D1/0083
摘要： A control process for the control surfaces of an aircraft to prevent lateral deviation of the trajectory on the ground during a landing or interrupted takeoff, in which the spoilers are extended asymmetrically.
摘要翻译：用于飞机的控制表面的控制过程，以防止在着陆或中断起飞期间地面上的轨迹的横向偏移，其中扰流板不对称地延伸。

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