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1. 发明授权

US11685515B2 Active horizontal stabilizer for high speed rotorcraft 有权
公开(公告)号：US11685515B2
公开(公告)日：2023-06-27
申请号：US17069816
申请日：2020-10-13
申请人： Bell Textron Inc.
发明人： Luke Dafydd Gillett , James Rigsby , Jeffrey Kirkman , Craig Lovell , Andrew Carter , Aaron Alexander Acee
IPC分类号： B64C5/16 , B64C13/16 , B64C5/02 , B64C27/06 , B64C27/82
CPC分类号： B64C13/16 , B64C5/02 , B64C5/16 , B64C27/06 , B64C2027/8281
摘要： A rotorcraft has a horizontal stabilizer movable about an axis of rotation and a horizontal stabilizer control system configured to control the horizontal stabilizer to at least one of move the rotorcraft into a minimum drag position, maintain the aircraft in a minimum drag position, efficiently achieve a maneuver, enter efficient autorotation, and maintain efficient autorotation.

2. 发明授权

US09902487B2 Aerial vehicle with deployable components 有权
公开(公告)号：US09902487B2
公开(公告)日：2018-02-27
申请号：US15388478
申请日：2016-12-22
申请人： Area- I Inc.
发明人： Nicholas Robert Alley , Joshua Lemming Steele , Jesse Owen Williams , Daniel Kuehme , Jonathan Caleb Phillips
IPC分类号： B64C3/40 , B64C3/54 , B64C39/02 , B64C3/56 , B64C13/30
CPC分类号： B64C3/40 , B64C1/36 , B64C3/54 , B64C3/546 , B64C3/56 , B64C5/02 , B64C5/12 , B64C5/16 , B64C11/28 , B64C13/24 , B64C13/30 , B64C39/024 , B64C2201/021 , B64C2201/102 , B64C2201/12 , B64C2201/123 , B64C2201/127 , B64C2211/00 , Y02T50/14 , Y02T50/44
摘要： An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

3. 发明申请

US20170291685A1 AERIAL VEHICLE WITH DEPLOYABLE COMPONENTS 审中-公开
公开(公告)号：US20170291685A1
公开(公告)日：2017-10-12
申请号：US15388396
申请日：2016-12-22
申请人： Area- I Inc.
发明人： Nicholas Robert Alley , Joshua Lemming Steele , Jesse Owen Williams , Daniel Kuehme , Jonathan Caleb Phillips
IPC分类号： B64C3/54 , B64C13/30 , B64C3/56 , B64C39/02
CPC分类号： B64C3/40 , B64C1/36 , B64C3/54 , B64C3/546 , B64C3/56 , B64C5/02 , B64C5/12 , B64C5/16 , B64C11/28 , B64C13/24 , B64C13/30 , B64C39/024 , B64C2201/021 , B64C2201/102 , B64C2201/12 , B64C2201/123 , B64C2201/127 , B64C2211/00 , Y02T50/14 , Y02T50/44
摘要： An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

4. 发明授权

US09694900B2 Actuators for flight control surfaces 有权
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.

5. 发明授权

US09555873B1 Aerial vehicle with deployable components 有权
公开(公告)号：US09555873B1
公开(公告)日：2017-01-31
申请号：US15092237
申请日：2016-04-06
申请人： Area- I Inc.
发明人： Nicholas Robert Alley , Joshua Lemming Steele , Jesse Owen Williams , Daniel Kuehme , Jonathan Caleb Phillips
IPC分类号： B64C3/56 , B64C3/54 , B64C39/02
CPC分类号： B64C3/40 , B64C1/36 , B64C3/54 , B64C3/546 , B64C3/56 , B64C5/02 , B64C5/12 , B64C5/16 , B64C11/28 , B64C13/24 , B64C13/30 , B64C39/024 , B64C2201/021 , B64C2201/102 , B64C2201/12 , B64C2201/123 , B64C2201/127 , B64C2211/00 , Y02T50/14 , Y02T50/44
摘要： An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

6. 发明授权

US09527577B2 Rotorcraft with a fuselage and at least one main rotor 有权
标题翻译：转子陀飞轮与机身和至少一个主转子
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。

7. 发明申请

US20160368621A1 AIRCRAFT VERTICAL STABILIZER ILLUMINATION LIGHT UNIT AND METHOD OF OPERATING AN AIRCRAFT VERTICAL STABILIZER ILLUMINATION LIGHT UNIT 审中-公开
标题翻译：航空器垂直稳定器照明灯单元和操作航空器垂直稳定器照明灯单元的方法
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。

8. 发明授权

US08985510B2 Tie rod lock 有权
标题翻译：领带锁
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。

9. 发明授权

US08814100B2 Continuous moldline technology (CMT) elastomeric control surface 有权
标题翻译：连续模具技术（CMT）弹性控制面
公开(公告)号：US08814100B2
公开(公告)日：2014-08-26
申请号：US13451456
申请日：2012-04-19
申请人： Paul F. Geders
发明人： Paul F. Geders
IPC分类号： B64C9/16
CPC分类号： B64C3/48 , B64C5/16 , B64C5/18 , B64C7/00 , B64C9/02 , Y02T50/14 , Y02T50/32 , Y02T50/44 , Y10T137/0318 , Y10T137/2514
摘要： A continuous moldline technology elastomeric control surface and methods are presented. A control surface is coupled to a fluid-dynamic body. An elastomer interface is coupled to the control surface and the fluid-dynamic body such that a joint gap caused by movement of the control surface relative to the fluid-dynamic body is filled.
摘要翻译：提出了一种连续的模具技术弹性控制表面和方法。控制表面联接到流体动力体上。弹性体界面被耦合到控制表面和流体动态体，使得由控制表面相对于流体动力体的运动引起的关节间隙被填充。

10. 发明授权

US06929216B2 Method and apparatus for installing and actuating movable airfoils, including canards 失效
标题翻译：用于安装和致动可移动翼片（包括挡板）的方法和装置
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。

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