公开(公告)号：US08844880B1

公开(公告)日：2014-09-30

申请号：US13199671

申请日：2011-09-07

申请人： McGregor Lee Corliss

发明人： McGregor Lee Corliss

IPC分类号： B64C27/56 ,  B64C13/04

CPC分类号： B64C27/32 ,  B64C13/12 ,  B64C27/025 ,  B64C27/18 ,  B64C27/26 ,  B64C27/48 ,  B64C27/56 ,  B64C27/605 ,  B64C27/72 ,  B64C2027/4736 ,  B64D31/04 ,  F16C33/667 ,  Y10T74/20612

摘要： A heliplane operates with a fixed wing at high velocities, and particularly at high advance ratios, while using a rotary wing maintained in motion at all speeds. At high advance ratios, the rotor wing eventually may be rotated primarily to maintain its stability, rather than depending upon the majority of lift. Meanwhile, a collective pitch control is provided and located between pilot and copilot. A single control provides control of both collective pitch and throttle by both pilots. One pilot will have to operate the control with the left hand, while the other may use their right hand. Nevertheless, both throttles push away from the pilot, regardless of which one is in control of the aircraft, while a single collective lever is relied upon.

摘要翻译： 一个直升机以高速度，特别是高进给速率的固定机翼操作，同时使用在所有速度下保持运动的旋翼。 在高提前比例下，转子翼最终可以主要旋转以保持其稳定性，而不是依赖于大部分升力。 同时，提供集体俯仰控制，位于飞行员和副驾驶之间。 单个控制提供两个飞行员对集体俯仰和油门的控制。 一名飞行员必须用左手操纵控制，而另一名可以使用右手。 尽管如此，无论是哪一个控制着飞机，两个节流阀都从飞行员上推，而依靠单一的集体杠杆。

公开(公告)号：US20140190304A1

公开(公告)日：2014-07-10

申请号：US13500861

申请日：2010-10-05

申请人： Aurelie Besold ,  David ENGLER ,  Sebastien PAUTARD ,  Antoine Besold ,  Stephanie Besold ,  Hafid ELABELLAOUI ,  Marie-Noel Besold ,  Etienne MERLET

发明人： Hafid Elabellaoui ,  Jean-Eric Besold ,  Sebastien Pautard ,  David Engler ,  Etienne Merlet

IPC分类号： B64D31/06

CPC分类号： B64D31/06 ,  B64D31/04 ,  Y10T74/20238

摘要： An aeroengine control device comprising a mount, having pivotally mounted thereon a code wheel together with a main lever and a secondary lever, both for turning the code wheel, each lever being movable between a rest position and a maximum actuation position, the secondary lever being mounted to pivot on the main lever. A connecting rod connects the secondary lever in permanent manner to the code wheel and the main lever is provided with a connection member arranged to co-operate with a portion in relief secured to the code wheel and with a portion in relief secured to the mount in such a manner that the connection member attaches to the code wheel when the main lever is moved while the secondary lever is in its rest position and attaches to the mount, thereby releasing the code wheel to turn, when the secondary lever is moved while the main lever is in its rest position, while movement of either lever is prevented when the other lever is away from its rest position.

摘要翻译： 一种航空发动机控制装置，其包括安装件，其具有与主杠杆和副杠杆一起枢转地安装有代码轮，用于转动代码轮，每个杠杆可在静止位置和最大致动位置之间移动，所述副杠杆为 安装在主杠杆上枢转。 连杆将永久性的方式连接到代码轮，并且主杠杆设置有连接构件，该连接构件布置成与固定到码盘的凸起部分配合，并且其中一部分浮雕固定到底座上 这样一种方式，即当主杆处于其静止位置而移动主杆并连接到安装件上时，连接构件附接到编码轮，从而当副杆移动时释放代码轮以转动，同时主杆 杠杆处于其静止位置，而当另一个杠杆远离其静止位置时，两个杠杆的运动被阻止。

公开(公告)号：US20140061389A1

公开(公告)日：2014-03-06

申请号：US14042471

申请日：2013-09-30

申请人： SAGEM DEFENSE SECURITE

发明人： Hafid ELABELLAOUI ,  Jean-Eric BESOLD ,  Sebastien PAUTARD ,  Thierry CARTRY ,  David ENGLER ,  Etienne MERLET

IPC分类号： B64D31/04

CPC分类号： B64D31/04

摘要： An aeroengine control device including a mount and having pivotally mounted thereon a code wheel together with a main lever and a secondary lever, both for turning the code wheel. Each lever is movable between a rest position and a maximum actuation position. The secondary lever is mounted to pivot on the main lever. Cam paths are mounted on the code wheel and on the mount in such a manner that the main lever can move the code wheel when the main lever is moved while the secondary lever is in the rest position. The secondary lever can move the code wheel when the secondary lever is moved while the main lever is in the rest position, with movement of either lever being prevented when the other lever is clearly away from its rest position.

摘要翻译： 一种航空发动机控制装置，包括安装件，并且与主杠杆和副杠杆一起枢转地安装有代码轮，两者用于转动代码轮。 每个杠杆可在静止位置和最大致动位置之间移动。 辅助杠杆安装成在主杠杆上枢转。 凸轮路径以这样的方式安装在代码轮和安装座上，使得当主杆处于静止位置时主杆能够移动代码轮。 当主杆处于静止位置时，辅助杆可以移动代码轮，同时当另一个杆明显远离其静止位置时，两个杆的移动被阻止。

公开(公告)号：US20140042272A1

公开(公告)日：2014-02-13

申请号：US13985024

申请日：2012-01-30

申请人： Bernard Guering

发明人： Bernard Guering

IPC分类号： B64D11/00

CPC分类号： B64D11/00 ,  B64D31/04 ,  B64D43/00

摘要： The invention relates to an aircraft cockpit centre pedestal for the attachment of control and instrumentation equipment for this aircraft, wherein the centre pedestal includes an equipment module including controls connected to at least one first electrical connector, and a single-piece frame including an upper face provided with a recess including at least one second electrical connector installed at the bottom of the recess and connected to computers onboard this aircraft in which this equipment module is installed, the at least one first electrical connector of the equipment module being inserted into at least one second electrical connector so as to connect the controls of the equipment module and these onboard computers. The invention also relates to an aircraft including such a pedestal.

摘要翻译： 本发明涉及一种用于该飞机的控制和仪表设备的安装的飞行器驾驶舱中心基座，其中中心支架包括一个设备模块，该设备模块包括连接至少一个第一电连接器的控制装置，以及一个单件框架， 设置有凹部，所述凹部包括安装在所述凹部的底部处的至少一个第二电连接器，并且连接到所述飞行器上的计算机，所述飞行器中安装有所述设备模块，所述设备模块的所述至少一个第一电连接器插入至少一个 第二电连接器，以便连接设备模块和这些机载计算机的控制。 本发明还涉及包括这种基座的飞行器。

公开(公告)号：US20130190949A1

公开(公告)日：2013-07-25

申请号：US13719693

申请日：2012-12-19

申请人： AIRBUS OPERATIONS (SAS)

发明人： Florian CONSTANS ,  Thierry BOURRET ,  Fabien PERRIN

IPC分类号： B64D31/02 ,  B64D31/04 ,  B64C19/00

CPC分类号： B64C19/00 ,  B64D31/02 ,  B64D31/04 ,  B64D43/02

摘要： A system for controlling energy of a vehicle, for example an aircraft, comprising a control interface able to be in at least one first and one second state, the first state being an instruction state in which the interface generates at least a first instruction for speed of variation of a current energy of the vehicle and the second state being a resting state in which it gives no instruction, the interface furthermore being configured to return into the second state after having been brought into the first state.

摘要翻译： 一种用于控制车辆能量的系统，例如飞行器，其包括能够处于至少一个第一和第二状态的控制接口，所述第一状态是指令状态，其中所述接口至少产生第一速度指令 所述车辆的当前能量的变化和所述第二状态是其不给出指令的静止状态，所述接口还被配置为在已经进入所述第一状态之后返回到所述第二状态。

公开(公告)号：US08223039B2

公开(公告)日：2012-07-17

申请号：US12786180

申请日：2010-05-24

申请人： Pierre Campagne ,  Alexandre Broquet ,  Nicolas Marty

发明人： Pierre Campagne ,  Alexandre Broquet ,  Nicolas Marty

IPC分类号： G01C21/00 ,  G01C23/00

CPC分类号： B64D45/00 ,  B64D31/04

摘要： A method and a device for detecting a thrust dissymmetry of an aircraft during a landing are disclosed. The detection device (6) comprises means (7) for detecting, upon a landing, that at least one of the engine control levers occupies an intermediary position comprised between a position threshold and a maximum speed position, as well as at least another engine control lever occupies an idling position, and means (9, 13) for triggering a warning when a landing condition is validated and at least one of the control levers occupies said intermediary position, at least another control lever occupying said idling position.

摘要翻译： 公开了一种用于在着陆期间检测飞行器的推力不对称性的方法和装置。 检测装置（6）包括用于在着陆时检测发动机控制杆中的至少一个占据位置阈值和最大速度位置之间的中间位置的装置（7），以及至少另一个发动机控制 杠杆占据怠速位置，以及用于当着陆条件被验证并且至少一个控制杆占据所述中间位置时触发警告的装置（9,13），至少另一控制杆占据所述怠速位置。

公开(公告)号：US08109073B2

公开(公告)日：2012-02-07

申请号：US12287500

申请日：2008-10-08

申请人： Glenn B. Foster ,  Roderick A. Hyde ,  Muriel Y. Ishikawa ,  Edward K. Y. Jung ,  Jordin T. Kare ,  Nathan P. Myhrvold ,  Clarence T. Tegreene ,  Thomas Allan Weaver ,  Lowell L. Wood, Jr. ,  Victoria Y. H. Wood

发明人： Glenn B. Foster ,  Roderick A. Hyde ,  Muriel Y. Ishikawa ,  Edward K. Y. Jung ,  Jordin T. Kare ,  Nathan P. Myhrvold ,  Clarence T. Tegreene ,  Thomas Allan Weaver ,  Lowell L. Wood, Jr. ,  Victoria Y. H. Wood

IPC分类号： F02C7/057

CPC分类号： F02C6/206 ,  B64D27/16 ,  B64D27/24 ,  B64D31/04 ,  B64D31/06 ,  B64D33/00 ,  B64D2027/026 ,  F01D5/03 ,  F01D15/10 ,  F01K23/10 ,  F02C6/00 ,  F02C6/08 ,  F02C6/14 ,  F02C6/18 ,  F02C7/36 ,  F02K3/00 ,  F02K3/025 ,  F02K3/077 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2220/326 ,  F05D2220/327 ,  F05D2220/76 ,  F05D2260/408 ,  F05D2260/85 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T50/672 ,  Y02T50/673

摘要： A hybrid propulsive technique includes providing a flow of a working fluid through at least a portion of an at least one jet engine. The hybrid propulsive technique comprises extracting energy from the working fluid that is at least partially converted into electrical power, and converting at least a portion of the electrical power to a torque. The hybrid propulsive technique also comprises rotating an at least one independently rotatable compressor stator at least partially responsive to the converting the at least a portion of the electrical power to the torque.

摘要翻译： 混合推进技术包括通过至少一个喷气发动机的至少一部分提供工作流体的流动。 混合推进技术包括从至少部分地转换成电力的工作流体提取能量，以及将至少一部分电功率转换为扭矩。 混合推进技术还包括至少部分地响应于将至少一部分电功率转换为转矩来旋转至少一个可独立旋转的压缩机定子。

公开(公告)号：US20100302074A1

公开(公告)日：2010-12-02

申请号：US12786180

申请日：2010-05-24

申请人： Pierre Campagne ,  Alexandre Broquet ,  Nicolas Marty

发明人： Pierre Campagne ,  Alexandre Broquet ,  Nicolas Marty

IPC分类号： G01C21/00

CPC分类号： B64D45/00 ,  B64D31/04

摘要： A method and a device for detecting a thrust dissymmetry of an aircraft during a landing are disclosed. The detection device (6) comprises means (7) for detecting, upon a landing, that at least one of the engine control levers occupies an intermediary position comprised between a position threshold and a maximum speed position, as well as at least another engine control lever occupies an idling position, and means (9, 13) for triggering a warning when a landing condition is validated and at least one of the control levers occupies said intermediary position, at least another control lever occupying said idling position.

摘要翻译： 公开了一种用于在着陆期间检测飞行器的推力不对称性的方法和装置。 检测装置（6）包括用于在着陆时检测发动机控制杆中的至少一个占据位置阈值和最大速度位置之间的中间位置的装置（7），以及至少另一个发动机控制 杠杆占据怠速位置，以及用于当着陆条件被验证并且至少一个控制杆占据所述中间位置时触发警告的装置（9,13），至少另一控制杆占据所述怠速位置。

公开(公告)号：US20100301174A1

公开(公告)日：2010-12-02

申请号：US12787272

申请日：2010-05-25

申请人： Brice Fernandez ,  Vincent Lamonzie

发明人： Brice Fernandez ,  Vincent Lamonzie

IPC分类号： B64D31/06

CPC分类号： B64D31/04 ,  B64D31/06

摘要： A system for controlling at least one aircraft engine and an aircraft comprising such a control system. The system (4) comprises a control lever (5) of the engine, the intermediary range of automatic regulation thereof of the engine speed of which comprises a single marked position (II) with which there is associated a plurality of speeds, corresponding to each one of the flight phases of the aircraft (AC) such as take-off and climbing phases.

摘要翻译： 一种用于控制至少一个飞机发动机和包括这种控制系统的飞行器的系统。 系统（4）包括发动机的控制杆（5），其发动机速度的自动调节的中间范围包括单个标记位置（II），与此相对应的多个速度相对应， 飞机（AC）的飞行阶段之一，如起飞和攀登阶段。

公开(公告)号：US20100083668A1

公开(公告)日：2010-04-08

申请号：US12287500

申请日：2008-10-08

申请人： Glenn B. Foster ,  Roderick A. Hyde ,  Muriel Y. Ishikawa ,  Edward K.Y. Jung ,  Jordin T. Kare ,  Nathan P. Myhrvold ,  Clarence T. Tegreene ,  Thomas Allan Weaver ,  Lowell L. Wood, JR. ,  Victoria Y.H. Wood

发明人： Glenn B. Foster ,  Roderick A. Hyde ,  Muriel Y. Ishikawa ,  Edward K.Y. Jung ,  Jordin T. Kare ,  Nathan P. Myhrvold ,  Clarence T. Tegreene ,  Thomas Allan Weaver ,  Lowell L. Wood, JR. ,  Victoria Y.H. Wood

IPC分类号： F02C6/00 ,  F02K7/10 ,  F01D25/24 ,  H02K44/08

CPC分类号： F02C6/206 ,  B64D27/16 ,  B64D27/24 ,  B64D31/04 ,  B64D31/06 ,  B64D33/00 ,  B64D2027/026 ,  F01D5/03 ,  F01D15/10 ,  F01K23/10 ,  F02C6/00 ,  F02C6/08 ,  F02C6/14 ,  F02C6/18 ,  F02C7/36 ,  F02K3/00 ,  F02K3/025 ,  F02K3/077 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2220/326 ,  F05D2220/327 ,  F05D2220/76 ,  F05D2260/408 ,  F05D2260/85 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T50/672 ,  Y02T50/673

摘要： One aspect relates to a hybrid propulsive technique, comprising providing a flow of a working fluid through at least a portion of an at least one jet engine. The hybrid propulsive technique comprises extracting energy from the working fluid that is at least partially converted into electrical power, and converting at least a portion of the electrical power to a torque. The hybrid propulsive technique also comprises rotating an at least one independently rotatable compressor stator at least partially responsive to the converting the at least a portion of the electrical power to the torque.