公开(公告)号：US09694901B2

公开(公告)日：2017-07-04

申请号：US12089158

申请日：2006-09-27

Applicant: Volkmar Stenzel ,  Martin Kaune ,  Hubertus Lohner ,  Ottmar Schramm

Inventor： Volkmar Stenzel ,  Martin Kaune ,  Hubertus Lohner ,  Ottmar Schramm

IPC: B64C9/32 ,  B05D5/00 ,  B64C7/00 ,  B64C9/02 ,  B64C9/14 ,  B64C9/16 ,  B64C9/22 ,  C09D175/04 ,  C08K3/22 ,  C08K3/34 ,  C08L23/04

CPC classification number: B64C9/323 ,  B05D5/00 ,  B64C7/00 ,  B64C9/02 ,  B64C9/14 ,  B64C9/16 ,  B64C9/22 ,  B64C9/32 ,  C08K3/22 ,  C08K3/34 ,  C08L23/04 ,  C09D175/04 ,  Y02T50/44 ,  Y10T428/25 ,  C08L2666/54 ,  C08L2666/06

Abstract: An aircraft landing flap includes a flap member having an abrasion-resistant coating coated on an abrasion region exposed to mechanical rubbing contacts with an aircraft spoiler. The coating comprises a polyurethane matrix based on aliphatic components and fillers embedded in the polyurethane matrix so as to increase resistance to abrasion.

公开(公告)号：US20160046375A1

公开(公告)日：2016-02-18

申请号：US14312131

申请日：2014-06-23

Applicant: Edward Parry McNair

Inventor： Edward Parry McNair

IPC: B64C39/12

CPC classification number: B64C39/12 ,  B64C9/32 ,  Y02T50/32

Abstract: An axillary airfoil located as far forward as practicable on the fuselage of an airliner. During high speed cruise, the airfoil can be adjusted to provide supplemental lift to move the center of pressure forward, thereby reducing the amount of downforce needed to be produced by the vertical stabilizer. This would result in saving fuel. Spoilers mounted on the airfoils would be programmed to automatically deploy to return the center of pressure rearward whenever flight conditions require greater longitudinal stability.

Abstract translation: 舷侧翼型在飞机的机身上尽可能远地位于前方。 在高速巡航期间，可以调节翼型以提供补充升力以向前移动压力中心，从而减少由垂直稳定器产生的下压力的量。 这将节省燃料。 安装在翼型上的防护装置将被编程为在飞行条件需要更大的纵向稳定性时自动部署以向后返回压力中心。

公开(公告)号：US09096307B2

公开(公告)日：2015-08-04

申请号：US12713895

申请日：2010-02-26

Applicant: Frédéric Sauvinet

Inventor： Frédéric Sauvinet

IPC: G05D1/00 ,  B64C9/32 ,  B64C13/16

CPC classification number: B64C9/32 ,  B64C13/16 ,  B64C27/008 ,  B64F5/60 ,  G05D1/0083 ,  Y02T50/32 ,  B64F5/0045

Abstract: A process and a device for automatically optimizing on the ground the aerodynamic configuration of an aircraft.The device (1) includes means (7, 8, 10) for determining and applying to the spoilers (6) a command providing the aircraft with an optimum aerodynamic configuration.

Abstract translation: 一种用于在地面上自动优化飞机的空气动力学配置的过程和装置。 装置（1）包括用于确定并向扰流板（6）施加提供飞行器最佳空气动力学构造的命令的装置（7,8,10）。

公开(公告)号：US20140336871A1

公开(公告)日：2014-11-13

申请号：US14066014

申请日：2013-10-29

Applicant: GE Aviation Systems Limited

Inventor： Christopher Joseph Catt ,  Julia Ann Howard

IPC: B60T10/00

CPC classification number: B60T10/00 ,  B60T1/16 ,  B64C9/32 ,  B64D43/00 ,  B64D45/0005 ,  B64F5/60

Abstract: A method of diagnosing a speed brake fault, where the method includes receiving a position signal from the at least one position sensor , determining a variation in the position signal relative to a reference position and diagnosing a fault in the speed brake system based on the variation.

Abstract translation: 一种诊断速度制动器故障的方法，其中所述方法包括从所述至少一个位置传感器接收位置信号，基于所述变化来确定所述位置信号相对于参考位置的变化并诊断所述速度制动系统中的故障 。

公开(公告)号：US20130144582A1

公开(公告)日：2013-06-06

申请号：US13684175

申请日：2012-11-22

Applicant: Airbus Engineering Centre India

Inventor： TARUN JAIN

IPC: G06F17/50

CPC classification number: G06F17/5095 ,  B64C1/0009 ,  B64C3/14 ,  B64C5/10 ,  B64C9/32 ,  B64C2009/005 ,  G06F17/5018 ,  G06F2217/16

Abstract: A system and method for simulating aerodynamics over an aircraft for a deflected position of a movable aircraft control surface using a structured chimera mesh are disclosed. In one embodiment, a mesh assembly of the aircraft is created by overlapping a background mesh and a structured chimera mesh for the deflected position of the movable aircraft control surface. Further, mesh cell sizes within overlapping boundaries of the background mesh and the structured chimera mesh are analyzed. Furthermore, the structured chimera mesh is regenerated based on the analysis. In addition, the mesh assembly of the aircraft is reformed based on the regenerated structured chimera mesh. Also, a masked mesh of the aircraft is created by auto masking the reformed mesh assembly. Moreover, aerodynamics is simulated over the aircraft for the deflected position of the movable aircraft control surface using the masked mesh.

Abstract translation: 公开了一种使用结构化嵌合网来模拟航空器上空气动力学的系统和方法，用于可移动飞行器控制表面的偏转位置。 在一个实施例中，飞行器的网格组件通过重叠背景网格和用于可移动飞行器控制表面的偏转位置的结构化嵌合网来创建。 此外，分析背景网格和结构化嵌合体网格的重叠边界内的网孔大小。 此外，基于分析再生结构化嵌合网。 另外，基于再生的结构化嵌合网来改变飞行器的网格组件。 此外，通过自动掩蔽重整的网格组件来创建飞机的蒙版网格。 此外，空中动力学是通过使用掩蔽的网状物在飞行器上模拟可移动飞行器控制表面的偏转位置的。

公开(公告)号：US20110226345A1

公开(公告)日：2011-09-22

申请号：US13150334

申请日：2011-06-01

Applicant: Glenn S. Bushnell

Inventor： Glenn S. Bushnell

IPC: F03B11/02 ,  B23P11/00

CPC classification number: B64C9/02 ,  B64C9/10 ,  B64C9/32 ,  B64C9/323 ,  B64C9/34 ,  B64C13/38 ,  Y02T50/32 ,  Y02T50/44 ,  Y10T137/0402 ,  Y10T137/8593

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20110080802A1

公开(公告)日：2011-04-07

申请号：US12897105

申请日：2010-10-04

Applicant: John Christos Vassilicos ,  Richard Elian Seoud

Inventor： John Christos Vassilicos ,  Richard Elian Seoud

IPC: B01F5/06

CPC classification number: B01F5/0601 ,  B01F5/0618 ,  B64C9/32 ,  B64C9/323 ,  F15D1/025 ,  F15D1/10

Abstract: A fluid flow modification apparatus for creating turbulence in a moving fluid includes turbulence-creating elements arranged in a fractal configuration, each element having a first surface portion against which the fluid can flow and a second surface portion along which the fluid can flow, and further includes an insert for arrangement to obstruct the flow of fluid between adjacent second surface portions of at least two turbulence-creating elements. A support holds the turbulence-creating elements in the fluid to allow movement of the fluid relative to the turbulence-creating elements and the insert. The insert may be attachable to at least two turbulence-creating elements, such that the arrangement of the inserts is symmetrical about a centre point of the fluid flow field for improved mixing.

Abstract translation: 用于在移动流体中产生湍流的流体流动改变装置包括以分形构造布置的湍流产生元件，每个元件具有流体可流动的第一表面部分和流体可沿其流动的第二表面部分， 包括用于布置以阻止至少两个湍流产生元件的相邻第二表面部分之间的流体流动的插入件。 支撑件将流体中的湍流产生元件保持以允许流体相对于湍流产生元件和插入件移动。 插入件可以附接到至少两个湍流产生元件，使得插入件的布置关于流体流场的中心点对称以改善混合。

公开(公告)号：US20110031347A1

公开(公告)日：2011-02-10

申请号：US12936750

申请日：2009-04-28

Applicant: Damian Allen

Inventor： Damian Allen

IPC: B64C9/00

CPC classification number: B64C9/32 ,  B64C3/58 ,  B64C9/323 ,  Y10T74/18944

Abstract: An aircraft wing assembly comprising: a wing; a spoiler pivotally attached to the wing; and a spoiler deployment mechanism. The deployment mechanism comprises a scissor linkage mechanism comprising an upper link pivotally attached to the spoiler at an upper pivot, and a lower link pivotally attached to the wing at a lower pivot and to the upper link at a central pivot. An actuator is pivotally attached to the wing at a proximal pivot and to the scissor linkage mechanism at a distal pivot. The actuator is adjustable between expanded and contracted configurations so as to vary the distance between the proximal and distal pivots. This opens up the angle between the upper and lower links of the scissor linkage mechanism and pushes the spoiler up into the air-stream above the wing.

Abstract translation: 一种飞机机翼组件，包括：机翼; 枢轴连接到机翼的扰流板; 和扰流器部署机构。 展开机构包括剪刀连杆机构，其包括在上枢轴处枢转地附接到扰流器的上连杆，以及在下枢轴处枢转地附接到翼的下连杆和在中心枢轴处的上连杆。 致动器在近端枢轴处枢转地附接到机翼并且在远端枢轴处枢转地附接到剪刀连杆机构。 致动器可在扩张和收缩构型之间调节，以便改变近端和远端枢轴之间的距离。 这打开了剪刀连杆机构的上连杆和下连杆之间的角度，并将扰流器向上推入机翼上方的气流中。

公开(公告)号：US07878459B2

公开(公告)日：2011-02-01

申请号：US11771489

申请日：2007-06-29

Applicant: James H. Mabe ,  Frederick T. Calkins ,  Glenn S. Bushnell ,  Stefan R. Bieniawski

Inventor： James H. Mabe ,  Frederick T. Calkins ,  Glenn S. Bushnell ,  Stefan R. Bieniawski

IPC: B64C3/58

CPC classification number: B64C27/615 ,  B64C9/32 ,  B64C9/323 ,  B64C13/28 ,  B64C2027/7288 ,  F03G7/065 ,  F05C2251/08 ,  Y02T50/34

Abstract: Aircraft systems with shape memory alloy (SMA) actuators, and associated methods are disclosed. A system in accordance with one embodiment includes an airfoil, a deployable device coupled to the airfoil, and a shape memory alloy actuator coupled between the airfoil and the deployable device. In one embodiment, the deployable device can be coupled to the airfoil with a hinge having a hinge load path supporting the deployable device relative to the airfoil, and the actuator can be movable along a motion path different than the hinge load path between a first position with the deployable device deployed relative to the airfoil, and a second position with the deployable device stowed relative to the airfoil. In another embodiment, an activatable link can be positioned between the actuator and the deployable device, and can have an engaged configuration in which motion of the actuator is transmitted to the deployable device, and a disengaged configuration in which motion of the actuator is not transmitted to the deployable device.

Abstract translation: 公开了具有形状记忆合金（SMA）致动器的飞机系统及相关方法。 根据一个实施例的系统包括翼型件，联接到翼型件的可展开装置以及耦合在翼型件和可展开装置之间的形状记忆合金致动器。 在一个实施例中，可展开装置可以利用具有支撑相对于翼型件的可展开装置的铰链加载路径的铰链联接到翼型件，并且致动器可以沿着不同于铰链加载路径的运动路径在第一位置 其中所述可部署设备相对于所述翼型部署，并且所述可部署设备相对于所述翼型件被收起的第二位置。 在另一个实施例中，可激活的连杆可位于致动器和可展开装置之间，并且可以具有接合构造，其中致动器的运动传递到可部署装置，以及分离构造，致动器的运动不被传递 到可部署设备。

公开(公告)号：US20100219298A1

公开(公告)日：2010-09-02

申请号：US12713782

申请日：2010-02-26

Applicant: Frederic Sauvinet

Inventor： Frederic Sauvinet

IPC: G05D1/00 ,  B64C13/18 ,  G05D1/04

CPC classification number: B64C9/32 ,  B64C13/16

Abstract: A process and device for the automatic flight optimisation of the aerodynamic configuration of an aircraft.The device (1) includes means (7, 8, 10) for determining and applying to the spoilers (6) of the aircraft commands for providing the aircraft with an optimum aerodynamic configuration.

Abstract translation: 用于飞行器空气动力学结构的自动飞行优化的过程和装置。 装置（1）包括用于确定和应用于用于为飞行器提供最佳空气动力学构造的飞行器命令的扰流板（6）的装置（7,8,10）。