公开(公告)号：US09694900B2

公开(公告)日：2017-07-04

申请号：US14228004

申请日：2014-03-27

申请人： Simmonds Precision Products, Inc.

发明人： Martin E. Buttolph

IPC分类号： B64C5/16 ,  B64C9/00 ,  B64C13/28 ,  B64C13/32

CPC分类号： B64C9/00 ,  B64C5/16 ,  B64C13/28 ,  B64C13/32

摘要： An actuator assembly includes an actuator body, a ram, and a cross pin. The actuator body has an internal axial cavity bounded by an actuator body wall and defines a pivot axis. A longitudinal slot extends along a portion of the length of the actuator body wall and is in communication with the internal axial cavity. The ram is slidably received within the axial cavity of the actuator body. The cross pin is mounted to the ram and extends laterally from the ram and into the longitudinal slot for converting linear motion of the ram into rotational motion about the pivot axis for displacing a control surface of an air vehicle.

公开(公告)号：US09527577B2

公开(公告)日：2016-12-27

申请号：US14605097

申请日：2015-01-26

申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

发明人： Martin Embacher

IPC分类号： B64C5/16 ,  B64C3/38 ,  B64C27/04 ,  B64C27/82

CPC分类号： B64C5/16 ,  B64C3/385 ,  B64C27/04 ,  B64C27/82 ,  B64C2027/8236 ,  Y02T50/14

摘要： A rotorcraft with a fuselage and at least one main rotor, the at least one main rotor being drivable for controlling an associated pitch attitude of the rotorcraft in operation, and the fuselage being equipped with at least one passive wing-type aerodynamic device that is adapted for generating independently of the associated pitch attitude a lift force acting on the fuselage, the lift force being oriented perpendicular to an air flow that is directed in operation of the rotorcraft against the passive wing-type aerodynamic device.

摘要翻译： 一种具有机身和至少一个主转子的旋翼航空器，所述至少一个主转子可驱动，用于控制所述旋翼航空器在运行中的相关俯仰姿态，并且所述机身装备有至少一个被动式翼型空气动力学装置， 为了独立于相关联的俯仰姿态产生作用在机身上的提升力，提升力垂直于在旋转航空器的操作中被引导以抵抗被动翼型空气动力学装置的空气流定向。

公开(公告)号：US20160368621A1

公开(公告)日：2016-12-22

申请号：US15183828

申请日：2016-06-16

申请人： Goodrich Lighting Systems GmbH

发明人： Sascha Lueder

IPC分类号： B64D47/06 ,  B64C5/02 ,  B64D45/00 ,  B64C5/16

CPC分类号： B64D47/06 ,  B64C5/02 ,  B64C5/16 ,  B64D45/0005 ,  B64D2203/00

摘要： An aircraft vertical stabilizer illumination light unit, configured for being arranged in a rotatable horizontal stabilizer of an aircraft and for being oriented towards a vertical stabilizer of the aircraft for illuminating the vertical stabilizer, includes an LED group, having a plurality of LEDs, and an optical system, having at least one optical element, the optical system being associated with the LED group for shaping an output light intensity distribution from the light emitted by the LED group.

摘要翻译： 一种飞机垂直稳定器照明灯单元，其构造成布置在飞行器的可旋转水平稳定器中并且朝向飞行器的垂直稳定器定向以照射垂直稳定器，包括具有多个LED的LED组，以及 光学系统，具有至少一个光学元件，所述光学系统与所述LED组相关联，用于对由所述LED组发出的光进行成像输出光强度分布。

公开(公告)号：US08985510B2

公开(公告)日：2015-03-24

申请号：US13678229

申请日：2012-11-15

申请人： Parker-Hannifin Corporation

发明人： Brian Curtis Hale

IPC分类号： B64C3/38 ,  B64C5/10 ,  B64C9/00 ,  B64C13/00 ,  B64C13/28 ,  F16H25/22 ,  B64C5/16

CPC分类号： B64C13/28 ,  B64C5/16 ,  F16H25/2204 ,  Y10T74/18576

摘要： A stabilizer actuator has a first end for connecting to an aircraft support structure and a second end for connecting to a stabilizer. The actuator includes a primary load path for transmittal of loads acting on the stabilizer to the aircraft support structure, and a secondary load path for transmittal of loads acting on the stabilizer to the aircraft support structure upon failure of the primary load path. The secondary load path includes a tie rod extending along a longitudinal axis, a load path locking mechanism coupled to the tie rod, a lock housing having a central bore for receiving the locking mechanism, and at least one radially movable segment that, upon failure of the primary load path, moves radially to lock the tie rod to the lock housing against axial and/or radial movement.

摘要翻译： 稳定器致动器具有用于连接到飞行器支撑结构的第一端和用于连接到稳定器的第二端。 致动器包括用于将作用在稳定器上的负载传递到飞行器支撑结构的主负载路径，以及用于在主负载路径故障时将作用在稳定器上的负载传递到飞行器支撑结构的次级负载路径。 次级负载路径包括沿着纵向轴线延伸的拉杆，联接到拉杆的负载路径锁定机构，具有用于接收锁定机构的中心孔的锁定壳体，以及至少一个可径向移动的段， 主负载路径径向移动以将拉杆锁定到锁壳体以防轴向和/或径向移动。

公开(公告)号：US07874514B2

公开(公告)日：2011-01-25

申请号：US11758404

申请日：2007-06-05

申请人： Brian R. Said

发明人： Brian R. Said

IPC分类号： B64C3/00 ,  B64C3/38 ,  B64C5/16 ,  B64C25/54

CPC分类号： B64C35/00 ,  B64C3/385 ,  B64C29/0033 ,  B64C39/04 ,  B64C39/08

摘要： A multi-wing, multi-engine, multi-hull amphibious aircraft is disclosed. In the illustrative embodiment, the aircraft has an open frame structure without a fuselage.

摘要翻译： 公开了一种多翼，多引擎，多船体两栖飞机。 在说明性实施例中，飞机具有没有机身的开放框架结构。

公开(公告)号：US06929216B2

公开(公告)日：2005-08-16

申请号：US10689972

申请日：2003-10-20

申请人： David L. Bath ,  Salvatore Carta ,  Kelly T. Jones ,  Brian J. Kramer ,  Chester P. Nelson ,  Pieter S. Penhall ,  Joseph R. Pineda ,  Andrew Sheppard

发明人： David L. Bath ,  Salvatore Carta ,  Kelly T. Jones ,  Brian J. Kramer ,  Chester P. Nelson ,  Pieter S. Penhall ,  Joseph R. Pineda ,  Andrew Sheppard

IPC分类号： B64C1/00 ,  B64C1/26 ,  B64C3/38 ,  B64C5/04 ,  B64C5/12 ,  B64C5/16 ,  B64C9/02 ,  B64C13/00 ,  B64C13/30 ,  B64C13/32 ,  B64C39/12 ,  F16C19/50

CPC分类号： F16C19/50 ,  B64C1/26 ,  B64C3/38 ,  B64C3/385 ,  B64C5/04 ,  B64C5/16 ,  B64C9/02 ,  B64C13/30 ,  B64C13/32 ,  B64C39/12 ,  F16C2326/43 ,  Y02T50/44 ,  Y10T29/49545 ,  Y10T29/49638 ,  Y10T29/49643 ,  Y10T29/4973

摘要： Methods and apparatuses for installing and actuating movable airfoils, such as canards. A canard in one embodiment of the invention includes an airfoil positioned external to an aircraft fuselage. The airfoil can include a first portion and a second portion (such as a flight control surface) movable relative to the first portion. A connecting portion depends from the airfoil portion and has an attachment portion configured to attach to an aircraft internal to the aircraft fuselage. A connecting portion can include first and second load paths to carry corresponding first and second load portions between the airfoil portion and the attachment portion. The connecting portion can be rotatable about a rotation axis positioned between the first and second loads paths. Accordingly, the connecting portion can be relatively compact so as to reduce the impact of the connecting portion and the volume of the fuselage.

摘要翻译： 用于安装和致动可移动翼型件的方法和装置，例如卡车。 在本发明的一个实施例中的鸭子包括位于飞机机身外部的翼型件。 翼型件可以包括可相对于第一部分移动的第一部分和第二部分（例如飞行控制表面）。 连接部分从翼型件部分中取出并且具有被配置为附接到飞行器机身内部的飞行器的附接部分。 连接部分可以包括第一和第二负载路径，以在机翼部分和附接部分之间承载对应的第一和第二负载部分。 连接部分可以围绕位于第一和第二负载路径之间的旋转轴线旋转。 因此，连接部分可以相对紧凑，以减少连接部分的冲击和机身的体积。

公开(公告)号：US20230109822A1

公开(公告)日：2023-04-13

申请号：US17498088

申请日：2021-10-11

申请人： THE BOEING COMPANY

发明人： John Emil Johnson

IPC分类号： B64C1/26 ,  B64C3/54 ,  B64C5/16

摘要： An aircraft includes an airfoil and a hinge member to rotatably couple the airfoil to a structure of an aircraft. The hinge member defines at least a portion of a rotational axis. The aircraft also includes an indexing mechanism coupled to the airfoil and configured to, in a first state, inhibit rotation of the airfoil about the rotational axis, and in a second state, to permit rotation of the airfoil about the rotational axis between a first position and a second position that is angularly indexed relative to the first position. The aircraft further includes an actuator to selectively change a state of the indexing mechanism from the first state to the second state, from the second state to the first state, or both.

公开(公告)号：US11292579B2

公开(公告)日：2022-04-05

申请号：US16141943

申请日：2018-09-25

申请人： The Boeing Company

发明人： Sergey Barmichev ,  Mithra Sankrithi

IPC分类号： B64C5/02 ,  B64C9/06 ,  B64C5/16 ,  B64C7/00

摘要： An aircraft empennage includes a lower vertical fin member attached to a rear portion of a fuselage, and an upper stabilizer assembly connected to the lower vertical member by an articulating mount configured to allow movement of the upper stabilizer assembly relative to the lower vertical member to adjust pitch trim of the fuselage. The upper stabilizer assembly includes first and second horizontal stabilizer portions and at least one upper vertical member.

公开(公告)号：US20200094939A1

公开(公告)日：2020-03-26

申请号：US16141943

申请日：2018-09-25

申请人： The Boeing Company

发明人： Sergey Barmichev ,  Mithra Sankrithi

IPC分类号： B64C5/02 ,  B64C5/16 ,  B64C7/00 ,  B64C9/06

摘要： An aircraft empennage includes a lower vertical fin member attached to a rear portion of a fuselage, and an upper stabilizer assembly connected to the lower vertical member by an articulating mount configured to allow movement of the upper stabilizer assembly relative to the lower vertical member to adjust pitch trim of the fuselage. The upper stabilizer assembly includes first and second horizontal stabilizer portions and at least one upper vertical member.

公开(公告)号：US20190300145A1

公开(公告)日：2019-10-03

申请号：US16367343

申请日：2019-03-28

申请人： BOMBARDIER INC.

发明人： Menahem BENDAYAN

IPC分类号： B64C5/16 ,  B64C5/08

摘要： An airfoil assembly for an aircraft includes an airfoil body having an internal frame and a skin covering the internal frame to define a cavity of the airfoil body. The airfoil body defines a span between a root and a tip and is deflectable in a deflection direction transverse to the span upon experiencing aerodynamic loading. At least one shaft is attached to the airfoil body and disposed within the cavity adjacent to an inner surface of the skin. The shaft extends along at least part of the span. A shaft measuring device is mounted to the airfoil body within the cavity. The shaft measuring device operates to measure a parameter of the shaft caused by deflection of the airfoil body such that the parameter is indicative of the aerodynamic loading on the airfoil body. A method for determining aerodynamic loading on an airfoil body is also disclosed.