公开(公告)号：US20120325958A1

公开(公告)日：2012-12-27

申请号：US12516594

申请日：2007-11-29

申请人： Olivier Cazals ,  Thierry Druot

发明人： Olivier Cazals ,  Thierry Druot

IPC分类号： B64C1/26 ,  B64C5/02 ,  B64D27/20

CPC分类号： B64D27/16 ,  B64C5/02 ,  B64C2039/105 ,  Y02T50/44

摘要： A rear tail assembly for an aircraft, including a fuselage, a wing and at least one propulsion engine attached in the rear portion of the fuselage located behind the wing along the X longitudinal axis of the aircraft, wherein the aforementioned assembly includes aerodynamic surfaces connected in the rear portion of the fuselage. The tail assembly essentially includes horizontal aerodynamic surfaces and essentially vertical aerodynamic surface arranged so as to form an annular structure including at least one ring attached to the fuselage. At lease one engine is held in the ring formed by the tail assembly. In one embodiment, a central fin is used for defining two rings in the annular structure. In particular embodiments of an aircraft including such a tail assembly, one or two engines can be fitted in the ring area.

摘要翻译： 一种用于飞行器的后尾部组件，包括机身，机翼和至少一个推进发动机，其沿机翼的X纵向轴线安装在机身后部的机身的后部，其中上述组件包括连接在飞行器的空气动力学表面 机身的后部。 尾部组件基本上包括水平空气动力学表面和基本垂直的空气动力学表面，其布置成形成包括连接到机身的至少一个环的环形结构。 至少一个发动机被保持在由尾部组件形成的环中。 在一个实施例中，中心翅片用于限定环形结构中的两个环。 在包括这种尾部组件的飞行器的特定实施例中，一个或两个发动机可以安装在环形区域中。

公开(公告)号：US08135399B2

公开(公告)日：2012-03-13

申请号：US12108631

申请日：2008-04-24

申请人： Francois de la Tousche ,  Christine Veron ,  Julia Ulloa-Sanzo ,  Jerome Goyet

发明人： Francois de la Tousche ,  Christine Veron ,  Julia Ulloa-Sanzo ,  Jerome Goyet

IPC分类号： H04W4/00

CPC分类号： H04B7/18506 ,  G01C23/00 ,  H04B7/18508

摘要： A method for the determining, on board an aircraft, of an identifier of a communications center with which an aircraft crew wishes to enter into contact, includes the following operations: a) the writing, by the crew, of a radio-communications frequency to a display unit of the cockpit of the aircraft, b) the determining of surroundings of the aircraft, c) the determining of the communications centers situated in these surroundings, d) the comparing of the frequencies of these communications centers with the frequency displayed on the display unit of the cockpit, and f) when the frequency of a communications center is identical to the displayed frequency, the display on the aircraft display unit of the identifier of said communications center having a frequency identical to the displayed frequency.

摘要翻译： 一种用于在飞机上确定飞机机组希望接触的通信中心的标识符的方法包括以下操作：a）由机组人员将无线电通信频率写入 飞机的驾驶舱的显示单元，b）确定飞行器的周围环境，c）确定位于这些环境中的通信中心，d）将这些通信中心的频率与在 驾驶舱的显示单元，以及f）当通信中心的频率与所显示的频率相同时，所述通信中心的标识符的飞行器显示单元上的显示具有与所显示的频率相同的频率。

公开(公告)号：US08132757B2

公开(公告)日：2012-03-13

申请号：US12168988

申请日：2008-07-08

申请人： Olivier Regis ,  Gregory Sicault ,  Emmanuel Kopp

发明人： Olivier Regis ,  Gregory Sicault ,  Emmanuel Kopp

IPC分类号： B64F1/02

CPC分类号： B64C25/426

摘要： A pitch-oscillation limitation system, applied to an aircraft having main landing gear located toward the center of the aircraft and forward landing gear located under the nose of the aircraft, wherein the system includes means for automatically applying, in the event of sudden braking, time-deferred braking between the wheels of the landing gear under the wings and the wheels of the landing gear under the fuselage, so as to reduce the amplitude of the aircraft's pitching motion.

摘要翻译： 一种俯仰振动限制系统，其应用于具有朝向飞机中心的主起落架和位于飞行器的鼻子下方的前起落架的飞机，其中该系统包括在突然制动的情况下自动应用的装置， 在机翼下的起落架的轮子和机身下的起落架的车轮之间的时间延迟制动，以便减小飞机的俯仰运动的幅度。

公开(公告)号：US08091197B2

公开(公告)日：2012-01-10

申请号：US11577930

申请日：2005-10-07

申请人： Francois Frehel ,  Christian M. Schmit, legal representative ,  Roger Thierry ,  Christophe Gauthier

发明人： Francois Frehel ,  Roger Thierry ,  Christophe Gauthier

IPC分类号： B23P19/10

CPC分类号： B23P19/10 ,  B23K37/0443 ,  B23K2101/06 ,  F16L1/10 ,  Y10T29/53978

摘要： A device and a method for assembling oriented objects, such as parts of a pipeline. The device includes means for rotational displacement about a rotational axis of a first and second base. The first base has a first main axis which is perpendicular to the rotational axis and includes first means for supporting objects that can be displaced in translation along the first main axis. The second base has a second main axis which is perpendicular to the rotational axis and includes second means for supporting objects and a revolving plate device for supporting and orienting one of the objects in an angular manner. The revolving plate device can be displaced in translation in relation to the second supporting means along the second main axis. Visualization means enable at least the rotational angle of the plate and the position of the second base to be visualised.

摘要翻译： 用于组装诸如管道的部件的定向对象的装置和方法。 该装置包括围绕第一和第二基座的旋转轴线旋转移动的装置。 第一基座具有垂直于旋转轴线的第一主轴线，并且包括用于支撑可沿着第一主轴线平移的物体的第一装置。 第二基座具有垂直于旋转轴线的第二主轴线，并且包括用于支撑物体的第二装置和用于以角度方式支撑和定向物体之一的旋转板装置。 旋转板装置可以沿着第二主轴线相对于第二支撑装置平移地移位。 可视化装置至少使得板的旋转角度和第二基座的位置可视化。

公开(公告)号：US08011613B2

公开(公告)日：2011-09-06

申请号：US12106485

申请日：2008-04-21

申请人： Mathieu Belleville

发明人： Mathieu Belleville

IPC分类号： B64C1/40 ,  B64C1/00

CPC分类号： B64D27/14 ,  B64D2027/005 ,  Y02T50/66

摘要： An aircraft includes a fuselage and at least one engine provided with at least one propeller and mounted at a rear part of the fuselage, on the back thereof, with the at least one engine having an axis substantially parallel to the longitudinal axis of the fuselage, where the at least one engine is mounted on the rear part of the fuselage so that the propeller lies forward of the tails, and provided at the rear part of the fuselage, symmetrically with respect to the fuselage, are removable noise masking surfaces configured to occupy either a deployed position in which the removable noise masking surfaces project laterally with respect to the rear part of the fuselage and are positioned plumb with the propeller, or a retracted position in which the removable noise masking surfaces are incorporated into the rear part of the fuselage.

摘要翻译： 飞机包括机身和至少一个设置有至少一个螺旋桨并且安装在机身的后部的后部的至少一个发动机，其中至少一个发动机具有基本上平行于机身的纵向轴线的轴线， 其中至少一个发动机安装在机身的后部，使得螺旋桨位于尾部的前方，并且相对于机身对称地设置在机身的后部，是被构造成占据 无论是展开位置，其中可移除的噪声掩蔽表面相对于机身的后部侧向突出并且与螺旋桨一起放置在铅垂处，或缩回位置，其中可移除的噪声掩蔽表面被结合到机身的后部 。

公开(公告)号：US08010288B2

公开(公告)日：2011-08-30

申请号：US11719134

申请日：2005-11-10

申请人： Christophe Bouchet ,  Jean-Pierre Demortier

发明人： Christophe Bouchet ,  Jean-Pierre Demortier

IPC分类号： G08G11/16

CPC分类号： G08G5/045 ,  G08G5/0086

摘要： An aircraft terrain avoidance system include a device having a first unit knowing a profile of the terrain that is located at the front of the aircraft, a second unit for determining an avoidance trajectory, a third unit which is connected to the first and second units and used to verify if there is a terrain collision risk for the aircraft, a fourth unit for emitting an alarm signal in the event of detection of a collision risk by the third unit, at least one aircraft performance database relating to an avoidance maneuvering gradient which can be flown by the aircraft according to particular flight parameters, and a fifth unit for determining the effective values of the particular parameters during the flight of the aircraft. The third unit is formed such that it is possible to determine the avoidance trajectory according to information received from the database and the fifth unit.

摘要翻译： 飞机地形回避系统包括具有第一单元的设备，该第一单元知道位于飞机前面的地形的轮廓，用于确定回避轨迹的第二单元，连接到第一和第二单元的第三单元，以及 用于验证飞机是否存在地形碰撞风险;第四单元，用于在检测到第三单元的碰撞风险的情况下发出报警信号;至少一个与回避机动梯度有关的飞机性能数据库，其可以 根据特定飞行参数由飞行器飞行，以及用于确定飞行器飞行期间的特定参数的有效值的第五单元。 第三单元形成为能够根据从数据库和第五单元接收的信息来确定回避轨迹。

公开(公告)号：US08004815B2

公开(公告)日：2011-08-23

申请号：US12331975

申请日：2008-12-10

申请人： Jean-Christophe Loche ,  Francois Guillaumel ,  Lionnel Espagnan ,  Jean-Claude Marty

发明人： Jean-Christophe Loche ,  Francois Guillaumel ,  Lionnel Espagnan ,  Jean-Claude Marty

IPC分类号： H02H1/00

CPC分类号： B64D45/02 ,  H01Q1/42 ,  H02G13/00

摘要： A lightning protection system for a composite structure has an outer surface designed to be subject to an air flow. This system has an electrically conductive strip and fasteners from the strip to the structure.Since the structure has holes designed for the fasteners, at least some of these fasteners have an attachment element from the lightning to this structure. This attachment element is inserted into the hole with its top part approximately even with the outer surface of this structure, and the attachment element is in electrical contact with the electrically conductive strip. At least part of the electrically conductive strip is placed within the thickness of the structure and to be connected to the ground.

摘要翻译： 用于复合结构的防雷系统具有设计为经受空气流动的外表面。 该系统具有导电条和从条到结构的紧固件。 由于该结构具有针对紧固件设计的孔，这些紧固件中的至少一些具有从闪电到该结构的附接元件。 该附接元件插入孔中，其顶部大致均匀地与该结构的外表面相连，并且附接元件与导电条电接触。 至少部分导电条被放置在结构的厚度内并连接到地面上。

公开(公告)号：US08000845B2

公开(公告)日：2011-08-16

申请号：US12038711

申请日：2008-02-27

申请人： Nathalie Fabre-Raimbault ,  Marco Adurno ,  Mathieu Berthereau ,  Stéphane Cote

发明人： Nathalie Fabre-Raimbault ,  Marco Adurno ,  Mathieu Berthereau ,  Stéphane Cote

IPC分类号： B64C13/16 ,  G06F19/00

CPC分类号： G05D1/0623

摘要： A device detects an air disturbance and controls the deflection of aircraft control surfaces when the disturbance is detected.

摘要翻译： 当检测到扰动时，设备检测空气干扰并控制飞机控制表面的偏转。

公开(公告)号：US07996120B2

公开(公告)日：2011-08-09

申请号：US11996339

申请日：2006-07-17

申请人： Stéphane Delannoy

发明人： Stéphane Delannoy

IPC分类号： B60W40/10 ,  G06F17/11

CPC分类号： G05D1/0816

摘要： The device for flying an aircraft includes a first unit for determining a control value corresponding to an instruction value representing the actuation of a control member by a pilot, a second unit for determining an effective control value corresponding to the instruction value which is actually applied to the aircraft, a third unit for automatically controlling the aircraft, a fourth unit for computing an auxiliary control value, which is closer to the effective controlled value, and a fifth unit for monitoring the control value and for detecting a pilot induced oscillation, where the automatic control is carried out with the aid of the controlled effective value and the auxiliary control value in the case of the detection of the pilot induced oscillation.

摘要翻译： 用于飞行飞行器的装置包括：第一单元，用于确定对应于由飞行员表示控制构件的致动的指令值的控制值;第二单元，用于确定与实际应用于指令值的指令值对应的有效控制值 飞行器，用于自动控制飞行器的第三单元，用于计算更接近有效控制值的辅助控制值的第四单元和用于监视控制值和用于检测导频感应振荡的第五单元，其中 在检测导频感应振荡的情况下，借助受控有效值和辅助控制值，进行自动控制。

公开(公告)号：US07996118B2

公开(公告)日：2011-08-09

申请号：US12067778

申请日：2006-09-21

申请人： Cédric Seren ,  François Bommier ,  Laurent Verdier

发明人： Cédric Seren ,  François Bommier ,  Laurent Verdier

IPC分类号： G05D1/00

CPC分类号： G05B17/02 ,  B64F5/60 ,  G01C23/00

摘要： An aircraft device includes a rudder, a control unit that applies a deflection instruction to the rudder, a measuring section that measures a recovery characteristic of aircraft movement in response to the rudder deflection instruction, a recorder that records an applied deflection instruction and a corresponding recovery characteristic, and a servo-control that maintains the recovery characteristic. The control unit receives a recovery instruction for a recovery characteristic, which is identifiable for an aerodynamic effect, and generates the rudder deflection instruction induced by the recovery instruction.

摘要翻译： 飞机装置包括方向舵，向舵施加偏转指示的控制单元，响应于舵偏转指令来测量飞行器运动的恢复特性的测量部分，记录所施加的偏转指令的记录器和相应的恢复 特性，以及维持恢复特性的伺服控制。 控制单元接收恢复特性的恢复指令，该指令可识别为空气动力学效应，并产生由恢复指令引起的方向舵偏转指令。