公开(公告)号：US20170050738A1

公开(公告)日：2017-02-23

申请号：US14828145

申请日：2015-08-17

Applicant: THE BOEING COMPANY

Inventor： Michael R. BUTCHER ,  Adrian STANESCU

IPC: B64D27/12 ,  F02C7/20 ,  B64D27/26

CPC classification number: B64D27/12 ,  B64D27/26 ,  B64D2027/266 ,  F02C7/20

Abstract: A method and apparatus for suspending a load is provided. A load is connected to a yoke by one or more mounting links. The mounting links are connected to the yoke by a yoke pins and to the load by load mounting pins. The mounting links are connected to the pins by spherical bearings that enable the mounting links to move relative to yoke and to the load to accommodate movement of the load, such as movement caused by thermal expansion of the load. A stop collar is arranged around the load mounting pins to limit free movement of the mounting links about a longitudinal axis so that the mounting links cannot contact the load.

Abstract translation: 提供了一种用于暂停负载的方法和装置。 负载通过一个或多个安装连接件连接到轭。 安装连杆通过轭销连接到轭，并通过负载安装销连接到负载。 安装连杆通过球面轴承连接到销上，使得安装连杆能够相对于轭和负载移动以适应负载的移动，例如由负载的热膨胀引起的运动。 在负载安装销周围布置有止动环，以限制安装连杆围绕纵向轴线的自由移动，使得安装连接件不能接触负载。

公开(公告)号：US20150013306A1

公开(公告)日：2015-01-15

申请号：US14151816

申请日：2014-01-10

Applicant: Rudolph Allen Shelley

Inventor： Rudolph Allen Shelley

IPC: F02K5/00 ,  F02C3/32

CPC classification number: F02K5/00 ,  B64D27/10 ,  B64D27/12 ,  B64D27/14 ,  B64D31/04 ,  B64D2027/026 ,  F01D15/10 ,  F02C7/32 ,  F02K3/06 ,  F05D2220/34 ,  Y02T50/44 ,  Y02T50/64

Abstract: A hybrid aerodynamic thrust system as a prime mover for aircraft or other high-speed vehicles. An arrangement of dual thrust resources to alternately accommodate low and high airspeed regimes. Electromotive force is used in lieu of hot section power turbines to achieve engine air compression or alternately perform thrust work at low velocities.

Abstract translation: 作为飞机或其他高速车辆的原动机的混合气动推力系统。 双重推力资源的布置，以交替地适应低空和高空速制度。 使用电动力代替热段动力涡轮机以实现发动机空气压缩或者以低速交替地执行推力工作。

公开(公告)号：US20140263854A1

公开(公告)日：2014-09-18

申请号：US13797350

申请日：2013-03-12

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Brent C. Ross ,  David R. Bockmiller ,  Mark L. Isaac ,  Brian J. Cox

IPC: B64C27/22

CPC classification number: B64C29/0033 ,  B64D27/12 ,  B64D35/04

Abstract: A rotor system for tilt rotor aircraft comprises an engine disposed at a first fixed position on a wing member, and a prop-rotor pylon mechanically coupled to the engine along a drive path extending through the wing member. The engine is disposed adjacent a fuselage of the tilt rotor aircraft, and the prop-rotor pylon is configured to selectively rotate between a vertical position and a horizontal position. The prop-rotor pylon is coupled to a plurality of rotor blades.

Abstract translation: 用于倾斜转子飞行器的转子系统包括设置在翼构件上的第一固定位置处的发动机和沿着延伸穿过翼构件的驱动路径机械联接到发动机的支柱转子塔架。 发动机邻近倾斜转子飞行器的机身设置，并且支柱转子塔架构造成在垂直位置和水平位置之间选择性地旋转。 支柱转子塔架联接到多个转子叶片。

公开(公告)号：US08616492B2

公开(公告)日：2013-12-31

申请号：US12900790

申请日：2010-10-08

Applicant: Richard David Oliver

Inventor： Richard David Oliver

IPC: B64C29/00

CPC classification number: B64D27/12 ,  B64C29/0033 ,  B64C29/0075 ,  B64C39/08 ,  B64D27/06 ,  Y02T50/44

Abstract: A vertical takeoff and landing aircraft having a fuselage with three wings and six synchronously tilt-able propulsion units, each one mounted above, below, or on each half of the aforementioned three wings. The propulsion units are vertical for vertical flight, and horizontal for forward flight. The aircraft wings are placed such that the rear wing is above the middle wing which is placed above the front wing. The placement of each of the propulsion units relative to the center of gravity of the aircraft about the vertical axis inherently assures continued stability in vertical flight mode, following the loss of thrust from any one propulsion unit. The placement of the propulsion units, viewing the aircraft from the front, is such that each propulsion units' thrust wake does not materially disturb the propulsion unit to its rear. When engine driven propellers or rotors are utilized, flapped wing panels are attached outboard of the forward and/or rearward propulsion units to provide yaw control during vertical flight.

Abstract translation: 垂直起飞和着陆飞机具有机身三翼和六个同步倾斜的推进单元，每个都安装在上述三翼的每一半的上方，下方或上方。 推进单元垂直垂直，垂直方向垂直。 飞机机翼被放置成使后翼位于放置在前翼上方的中间翼的上方。 随着从任何一个推进单元的推力损失，每个推进单元相对于飞机围绕垂直轴的重心的位置固有地确保垂直飞行模式的持续稳定性。 从前方观察飞行器的推进装置的放置使得每个推进装置的推力尾流不会将推进装置重大地打扰到其后部。 当使用发动机驱动的螺旋桨或转子时，翼板翼板被安装在前部和/或后部推进单元的外侧，以在垂直飞行期间提供偏航控制。

公开(公告)号：US08517304B2

公开(公告)日：2013-08-27

申请号：US12894726

申请日：2010-09-30

Applicant: Frédéric Journade ,  Esteban Quiroz-Hernandez ,  Jean-Michel Saucray

Inventor： Frédéric Journade ,  Esteban Quiroz-Hernandez ,  Jean-Michel Saucray

IPC: B64D27/26

CPC classification number: B64D27/12 ,  B64C11/48 ,  B64D2027/026 ,  B64D2027/264 ,  Y02T50/66

Abstract: A device for locking an engine on a pylon includes two systems attaching the engine to the pylon, located in attachment regions spaced out in a longitudinal direction of the engine. A second region is adjacent to a center of gravity plane of the engine and closer to a fan than a first region. A first system attaching to the first region is rigid towards torsional, transverse and vertical engine forces. The first region is located at a separation between two compressors of the engine or two turbines, whether the fan is at a rear or front of the engine respectively, the separation being adjacent to a node of a first engine flexural mode. A second system attaching to the second region is rigid towards transverse and vertical forces but less rigid than the first system. The device also includes a third system withstanding thrust forces in the longitudinal direction.

Abstract translation: 用于将发动机锁定在挂架上的装置包括将发动机附接到塔架的两个系统，所述塔架位于沿发动机的纵向间隔开的附接区域中。 第二区域与发动机的重心平面相邻，并且比第一区域更靠近风扇。 附接到第一区域的第一系统对于扭转，横向和垂直的发动机力是刚性的。 第一区域位于发动机的两个压缩机或两个涡轮机之间的分离处，无论风扇是分别位于发动机的后部还是前部，分离器与第一发动机弯曲模式的节点相邻。 附接到第二区域的第二系统对于横向和垂直力是刚性的，但是比第一系统刚性小。 该装置还包括在纵向上承受推力的第三系统。

公开(公告)号：US08402740B2

公开(公告)日：2013-03-26

申请号：US12379787

申请日：2009-02-27

Applicant: Volker Guemmer

Inventor： Volker Guemmer

IPC: F02K3/02 ,  F02K3/00 ,  B64D27/00 ,  B64D35/00

CPC classification number: F02K3/077 ,  B64D27/12 ,  B64D35/04 ,  F02K3/072

Abstract: An aircraft propulsion unit includes a gas-turbine core engine 10 having at least one compressor, one combustion chamber and one turbine driving a main shaft 11. The main shaft 11 of the gas-turbine core engine 10 is operationally connected to at least two separate fans 6-9 via a mechanical drive connection, each of them being arranged beside the gas-turbine core engine 10.

公开(公告)号：US20120292441A1

公开(公告)日：2012-11-22

申请号：US13111414

申请日：2011-05-19

Applicant: Mark Drela ,  John Gundlach ,  Robert Parks ,  Adam Scott Ehrmantraut

Inventor： Mark Drela ,  John Gundlach ,  Robert Parks ,  Adam Scott Ehrmantraut

IPC: B64C1/40

CPC classification number: B64C21/06 ,  B64C2230/14 ,  B64C2230/28 ,  B64D27/06 ,  B64D27/12 ,  Y02T50/166 ,  Y02T50/66

Abstract: A system and method for reducing the noise penalty of a pusher propeller, allowing an aircraft to retain its advantages for UAV configurations, while allowing acoustic performance similar to that of a tractor propeller by reducing, or eliminating, propeller noise emissions. The system and method provide an airfoil-shaped flight surface with (i) a scoop configured to route boundary layer air and associated wake from said flight surface, and (ii) a suction device configured to provide a suction pressure, wherein the scoop routes boundary layer air from the flight surface to the suction device via an opening in the flight surface.

Abstract translation: 一种用于降低推进器螺旋桨的噪音损失的系统和方法，允许飞机保持其对UAV配置的优点，同时通过减少或消除螺旋桨噪声辐射来允许类似于拖拉机螺旋桨的声学性能。 该系统和方法提供了一种翼型飞行表面，其具有（i）舀配置以将所述飞行表面的边界层空气和相关联的尾流引导，以及（ii）构造成提供吸入压力的抽吸装置，其中所述铲斗路线为边界 通过飞行表面中的开口从飞行表面到吸入装置的层状空气。

公开(公告)号：US08226028B2

公开(公告)日：2012-07-24

申请号：US12602110

申请日：2008-06-02

Applicant: Herve Marche

Inventor： Herve Marche

IPC: F02C7/20

CPC classification number: B64D27/12 ,  B64D2027/264

Abstract: An engine unit for an aircraft including a turboprop engine and its device for mounting on to a wing surface. The device includes a rigid structure and a mechanism for fastening the turboprop engine on to this structure. The fastening mechanism includes six mutually independent hydraulic systems, each one exclusively dedicated to the transfer, to the rigid structure, of forces exerted respectively according to one of the six degrees of freedom of movement. Each hydraulic system includes at least one hydraulic jack with a piston attached to one of the two elements, i.e. either the turboprop engine or the rigid structure, together with a cylinder housing the piston and attached to the other of the two elements.

Abstract translation: 一种用于飞机的发动机单元，包括涡轮螺旋桨发动机及其装置，用于安装在机翼表面上。 该装置包括刚性结构和用于将涡轮螺旋桨发动机紧固到该结构的机构。 紧固机构包括六个相互独立的液压系统，每个独立的液压系统专门用于分别根据六个运动自由度中的一个自动地施加到刚性结构上的力。 每个液压系统包括至少一个液压千斤顶，其具有连接到两个元件中的一个，即涡轮螺旋桨发动机或刚性结构中的一个的活塞，以及容纳活塞并连接到两个元件中的另一个的柱塞。

公开(公告)号：US20110303795A1

公开(公告)日：2011-12-15

申请号：US13168624

申请日：2011-06-24

Applicant: Richard David Oliver

Inventor： Richard David Oliver

IPC: B64C27/22 ,  B64C29/00

CPC classification number: B64C29/0033 ,  B64C29/0075 ,  B64C39/08 ,  B64D27/06 ,  B64D27/12 ,  Y02T50/44

Abstract: A vertical takeoff and landing aircraft having a fuselage with, preferably, three wings and six synchronously tilt-able propulsion units, each one mounted above, below, or on each half of the aforementioned three wings. The propulsion units are oriented vertically for vertical flight and horizontally for forward flight. Each propulsion unit comprises a propeller having a plurality of blades, where the pitch angle associated with the distal end of each blade and the proximal end of each blade are independently adjustable. As such, each of the propellers can be adjusted to exhibit a first blade pitch angle distribution optimized for vertical flight and a second blade pitch angle distribution optimized for forward flight.

Abstract translation: 具有机身的垂直起飞和着陆飞机，优选地具有三个翼和六个同步倾斜的推进单元，每个都安装在上述三个翼的每一半的上方，下面或之上。 推进单元垂直方向垂直取向，水平方向前进。 每个推进单元包括具有多个叶片的螺旋桨，其中与每个叶片的远端和每个叶片的近端相关联的桨距角可独立调节。 因此，可以调整每个螺旋桨以呈现针对垂直飞行优化的第一叶片俯仰角分布和针对向前飞行优化的第二叶片俯仰角分布。

公开(公告)号：US07950605B2

公开(公告)日：2011-05-31

申请号：US12568442

申请日：2009-09-28

Applicant: John V. Howard ,  Stephen E. Mildenstein

Inventor： John V. Howard ,  Stephen E. Mildenstein

IPC: B64D27/00

CPC classification number: B64D27/26 ,  B64C27/14 ,  B64C27/28 ,  B64C29/0033 ,  B64D27/12 ,  B64D2027/266 ,  B64F5/60 ,  F02C7/20 ,  F02C7/36 ,  Y02T50/44 ,  Y02T50/671

Abstract: A torsionally de-coupled engine mount system for use in tilt rotor aircraft applications is disclosed, in which an engine is mounted at its forward end to a prop rotor gear box by means of a forward mount that is a simple adapter fitting, and at its aft end to a pylon assembly by an aft mount that is a simple bi-pod fitting. The forward mount counteracts forces and moments in six degrees of freedom, but the aft mount only counteracts lateral and vertical loads. The contribution from the engine to the overall dynamic response of the aircraft is tuned by selectively tailoring the size, shape, weight, and material of the forward mount. The engine mount system torsionally de-couples the engines from the prop rotors, thereby preventing rotor torque from being induced into the engines. In addition, the contribution from the engines to the overall dynamic response of the aircraft can be tuned by selectively tailoring the size, shape, weight, and material of the forward mounts between the engines and the transmissions.

Abstract translation: 公开了一种用于倾斜转子飞机应用的扭转解耦发动机安装系统，其中发动机借助于作为简单的适配器配件的前悬架在其前端安装到支柱转子齿轮箱，并且在其 后端通过一个简单的双荚配件的尾座安装在塔架组件上。 前向安装抵消六自由度的力量和力矩，但是后部安装仅抵消横向和垂直载荷。 通过选择性地调整前悬架的尺寸，形状，重量和材料来调整发动机对飞机整体动态响应的贡献。 发动机安装系统使发动机与支承转子扭转地解耦，从而防止转子扭矩被引入发动机。 此外，可以通过选择性地调整发动机和变速器之间的前悬架的尺寸，形状，重量和材料来调节来自发动机对飞行器的整体动态响应的贡献。