公开(公告)号：US20160340041A1

公开(公告)日：2016-11-24

申请号：US15160251

申请日：2016-05-20

Applicant: DASSAULT AVIATION

Inventor： Denis PEUZIAT

IPC: B64D11/00 ,  F16M13/02 ,  B64D11/06

CPC classification number: B64D11/0015 ,  B60R11/0235 ,  B64D11/06 ,  F16M11/14 ,  F16M11/2064 ,  F16M13/02 ,  F16M2200/065 ,  F16M2200/08

Abstract: A retractable support for a screen, and interior layout assembly for an aircraft cabin comprising such a support are provided. The retractable support for a screen includes a housing for receiving the screen in a retracted position, and an arm movably mounted relatively to the housing between a retracted position inside the housing and a deployed position outside the housing. The arm includes first and second rigid segments jointed with each other so that the second segment pivots relatively to the first segment around a first pivot axis between a compact configuration, in which the second segment is fitted into a recess of the first segment, and an extended configuration, in which the second segment extends out of said recess.

Abstract translation: 提供了一种用于屏幕的伸缩支撑件，以及用于包括这种支撑件的飞机机舱的内部布置组件。 屏幕的可伸缩支撑件包括用于在缩回位置接收屏幕的壳体，以及在壳体内的缩回位置和壳体外部的展开位置之间相对于壳体可移动地安装的臂。 臂包括彼此接合的第一和第二刚性部分，使得第二部分围绕第一枢转轴线相对于第一部分枢转，在紧凑构型之间，第二部分嵌入第一部分的凹部中， 延伸构造，其中第二段延伸出所述凹部。

公开(公告)号：US09483885B2

公开(公告)日：2016-11-01

申请号：US14316441

申请日：2014-06-26

Applicant: DASSAULT AVIATION

Inventor： Francois-Xavier D'Arbonneau ,  Olivier Breton

IPC: G07C5/00 ,  G07C5/08 ,  G01P5/16 ,  G01P21/02 ,  B64D45/00

CPC classification number: G07C5/0816 ,  B64D45/00 ,  G01P5/16 ,  G01P21/025

Abstract: A method for detecting a failure of at least one sensor onboard an aircraft implementing wind detection is provided. The method includes measuring an airspeed of the aircraft; measuring a geographical speed of the aircraft; determining an instantaneous wind vector, based on the measured airspeed and geographical speed; establishing an instantaneous wind variation vector, based on the determined instantaneous wind vector; projecting the instantaneous wind variation vector on the direction of the vector of an air or geographical speed of the aircraft; and determining the presence of a failure based on the obtained projection.

Abstract translation: 提供一种用于检测执行风检测的飞行器上的至少一个传感器的故障的方法。 该方法包括测量飞行器的空速; 测量飞机的地理速度; 基于测量的空速和地理速度确定瞬时风向量; 基于确定的瞬时风矢量建立瞬时风向量; 将瞬时风力变化矢量投影到飞行器的空气或地理速度的矢量的方向上; 以及基于所获得的投影来确定故障的存在。

公开(公告)号：US20160272336A1

公开(公告)日：2016-09-22

申请号：US15063940

申请日：2016-03-08

Applicant: DASSAULT AVIATION

Inventor： Sébastien LEPAGE

IPC: B64D31/08

CPC classification number: G05D1/0066 ,  B64C13/16 ,  B64C19/02 ,  B64D31/08 ,  G01C23/00 ,  G05D1/0055 ,  G05D1/0816

Abstract: A piloting assistance system for an aircraft during manual piloting is provided. The piloting assistance system includes a monitoring module, configured to compare an acceleration of the aircraft to an authorized acceleration that depends on a speed of the aircraft, an acceleration control module, able to be switched between an activated state and a deactivated state, and configured so as, in the activated state, excluding the deactivated state, to generate a control signal of at least one control device of the acceleration of the aircraft to push the acceleration of the aircraft toward the authorized acceleration range, in order to keep or push the speed of the aircraft in a predefined usage speed range, the monitoring module being configured to activate the acceleration control module when the acceleration of the aircraft is not comprised in the authorized acceleration range.

Abstract translation: 提供了在手动驾驶期间为飞机提供驾驶辅助系统。 驾驶辅助系统包括监视模块，其被配置为将飞行器的加速度与取决于飞行器速度的授权加速度进行比较，加速控制模块能够在激活状态和停用状态之间切换，并配置 在激活状态下，除了去激活状态之外，为了产生飞行器的加速度的至少一个控制装置的控制信号，将飞行器的加速度推向授权的加速度范围，以便保持或推动 所述监视模块被配置为当所述飞机的加速度不包括在所述授权的加速度范围内时激活所述加速控制模块。

公开(公告)号：US09444391B2

公开(公告)日：2016-09-13

申请号：US14495445

申请日：2014-09-24

Applicant: DASSAULT AVIATION

Inventor： Jean-Marc Le Peuvedic

IPC: H02P6/10 ,  H02P29/02 ,  F01D15/10 ,  F02C7/32

CPC classification number: H02P29/02 ,  F01D15/10 ,  F02C7/32 ,  F05D2220/76 ,  F05D2270/335 ,  Y02T50/671

Abstract: A protective method is provided against torque peaks between a motor adapted for setting a shaft of the motor into rotation and an electric source adapted for electrically powering an electric assembly and including a fixed section and a rotating adapted for rotating with the shaft. The method includes a step for controlling the operation of the electric source forcing the rotary movement of the rotating section with the shaft to observe an instruction relating to the torque of the rotating section applied to the shaft of the motor, the instruction being adapted depending on at least one element characterizing a current operating state of the motor.

Abstract translation: 提供了一种保护方法，用于在适于将电机的轴设置为旋转的电动机和适于为电气组件供电并包括固定部分和适于与轴一起旋转的旋转的电源之间的扭矩峰值。 该方法包括用于控制电源的操作的步骤，用于迫使旋转部分与轴的旋转运动，以观察与施加到电动机的轴的旋转部分的转矩相关的指令，该指令根据 至少一个表征电动机的当前操作状态的元件。

公开(公告)号：US20160234309A1

公开(公告)日：2016-08-11

申请号：US15010668

申请日：2016-01-29

Applicant: DASSAULT AVIATION

Inventor： Hugues ABRASSART

IPC: H04L29/08 ,  G06F15/167

CPC classification number: H04L67/1097 ,  G06F15/167 ,  H04L67/1095 ,  H04W4/046

Abstract: A method for exchanging data between a storage system on the ground-based and an onboard storage system of an aircraft is provided. The method includes a first step for synchronization of a set of data contained in the ground-based storage system with a corresponding set of data of a storage memory of a data exchange device, through a communications network, a step for coupling the data exchange device to a local internal network of the aircraft connected to the storage system, and then a second step for synchronization of the set of data of the storage memory with a corresponding set of data of the onboard storage system, through the local internal network.

Abstract translation: 提供了一种用于在飞机的基于地面的存储系统和机载存储系统之间交换数据的方法。 该方法包括：第一步骤，用于通过通信网络将包含在地面存储系统中的一组数据与数据交换设备的存储存储器的相应数据集同步，用于将数据交换设备 连接到存储系统的飞行器的本地内部网络，然后通过本地内部网络，将存储存储器的一组数据与车载存储系统的相应的一组数据同步的第二步骤。

公开(公告)号：US20160221678A1

公开(公告)日：2016-08-04

申请号：US15010722

申请日：2016-01-29

Applicant: DASSAULT AVIATION

Inventor： Yann MAILLAUT

IPC: B64D11/06

CPC classification number: B64D11/0638 ,  B64D11/0605

Abstract: An interior layout assembly of an aircraft cabin, and related method are provided. The assembly includes a table, a console defining a receiving housing and a cover mounted on the console. The cover in the closed configuration and the console define a passage slot between them. The assembly also includes a flap closing off the passage slot, movable by the table from an active configuration closing the passage slot to a retracted configuration freeing the passage slot during the passage of the table from its retracted position to the deployed position.

Abstract translation: 提供飞机机舱的内部布局组件及相关方法。 该组件包括一个桌子，一个限定接收外壳的控制台和一个安装在控制台上的盖子。 封闭配置中的盖子和控制台在它们之间定义通道槽。 该组件还包括一封闭通道槽的挡板，其可通过将工作台从关闭通道槽的活动构件移动到在桌子从其缩回位置到展开位置通过期间释放通道槽的缩回构型而移动。

公开(公告)号：US20160221677A1

公开(公告)日：2016-08-04

申请号：US15010696

申请日：2016-01-29

Applicant: DASSAULT AVIATION

Inventor： Nicolas HANCE

IPC: B64D11/06

CPC classification number: B64D11/0605 ,  B64D11/0638

Abstract: A supporting device for an interior layout assembly of an aircraft cabin, a related assembly and method are provided. The device includes a stationary frame; a table that can be deployed relative to the frame between a retracted position and a horizontal deployed position; a mechanism for guiding the movement of the table relative to the frame between the retracted position and the deployed horizontal position. The guide mechanism defines at least one bearing point for the table during its passage from the retracted position to the deployed horizontal position, the bearing point having a globally invariable position relative to the frame, the table being configured to pivot on the bearing point while moving laterally away relative to the bearing point, by sliding on the bearing point, to the deployed position.

Abstract translation: 提供了一种用于飞机机舱的内部布置组件的支撑装置，相关组件和方法。 该装置包括固定框架; 可以在缩回位置和水平展开位置之间相对于框架部署的桌子; 用于在缩回位置和展开的水平位置之间引导桌子相对于框架的运动的机构。 引导机构在其从缩回位置到展开的水平位置的过程中定义了桌子的至少一个支承点，所述支承点相对于所述框架具有全局不变的位置，所述工作台构造成在移动时在所述支承点上枢转 通过在支承点上滑动到相对于支承点的横向远离到展开位置。

公开(公告)号：US20150329195A1

公开(公告)日：2015-11-19

申请号：US14711699

申请日：2015-05-13

Applicant: DASSAULT AVIATION

Inventor： Eugène WIELGOSZ

IPC: B64C1/14

CPC classification number: B64C1/1453 ,  F01D25/32 ,  Y10T137/0318 ,  Y10T137/6906

Abstract: A drain mast or discharging fluids from an aircraft and associated method are provided. This drain mast includes a fairing including a base including an upstream section intended to be attached on an outer surface of the aircraft and a downstream section. The drain mast also includes a discharge nozzle including a discharge end opening onto the outside of the fairing, the discharge nozzle protruding from the downstream section in a first direction with respect to the base, the base and the discharge nozzle defining a tubular through-cavity, extending from the upstream section as far as the discharge end. The fairing also includes a profiled section for guiding air, protruding from the downstream section, in a direction opposite to the first direction, and configured for orienting an incident mass of air on the profiled section towards the discharge end.

Abstract translation: 提供排水桅杆或从飞机排出流体和相关方法。 这种排水桅杆包括整流罩，其包括底座，其包括旨在附接在飞行器的外表面上的上游部分和下游部分。 排水桅杆还包括排出喷嘴，该喷嘴包括在整流罩的外侧上的排出端开口，排出喷嘴相对于底座在第一方向上从下游部分突出，基部和排出喷嘴限定管状通孔 ，从上游部分延伸到排放端。 整流罩还包括用于引导空气的成型部分，其从下游部分沿与第一方向相反的方向突出，并且构造成用于将异型件上的入射空气质量定向到排出端。

公开(公告)号：US20150006021A1

公开(公告)日：2015-01-01

申请号：US14316441

申请日：2014-06-26

Applicant: DASSAULT AVIATION

Inventor： Francois-Xavier D'ARBONNEAU ,  Olivier Breton

IPC: G07C5/08 ,  B64D45/00

CPC classification number: G07C5/0816 ,  B64D45/00 ,  G01P5/16 ,  G01P21/025

Abstract: A method for detecting a failure of at least one sensor onboard an aircraft implementing wind detection is provided. The method includes measuring an airspeed of the aircraft; measuring a geographical speed of the aircraft; determining an instantaneous wind vector, based on the measured airspeed and geographical speed; establishing an instantaneous wind variation vector, based on the determined instantaneous wind vector; projecting the instantaneous wind variation vector on the direction of the vector of an air or geographical speed of the aircraft; and determining the presence of a failure based on the obtained projection.

Abstract translation: 提供一种用于检测执行风检测的飞行器上的至少一个传感器的故障的方法。 该方法包括测量飞行器的空速; 测量飞机的地理速度; 基于测量的空速和地理速度确定瞬时风向量; 基于确定的瞬时风矢量建立瞬时风向量; 将瞬时风力变化矢量投影到飞行器的空气或地理速度的矢量的方向上; 以及基于所获得的投影来确定故障的存在。

公开(公告)号：US20150006020A1

公开(公告)日：2015-01-01

申请号：US14316459

申请日：2014-06-26

Applicant: DASSAULT AVIATION

Inventor： Francois-Xavier D'ARBONNEAU

IPC: B64F5/00

CPC classification number: B64F5/60 ,  G01C5/005 ,  G01C5/06 ,  G01C21/165 ,  G01P5/14 ,  G01P7/00 ,  G01P21/025 ,  G05D1/042

Abstract: A method for detecting a failure of at least one sensor onboard an aircraft implementing a baro-inertial loop is provided. The method includes implementing a baro-inertial loop including obtaining a computed vertical speed, then a short-term baro-inertial altitude, based on a double integration of the measured vertical acceleration; and developing at least one intermediate loop parameter based on a deviation between the short-term baro-inertial altitude and the pressure altitude. The method also includes observing at least one failure detection parameter obtained from one of the intermediate parameters of the baro-inertial loop; and determining the presence of a failure on one of the sensors of the aircraft based on the value of the observed failure detection parameter.

Abstract translation: 提供了一种用于检测执行压力 - 惯性环路的飞行器上的至少一个传感器故障的方法。 该方法包括基于所测量的垂直加速度的双重积分来实现巴洛惯性循环，包括获得计算的垂直速度，然后是短期压力惯性高度; 并且基于短期压力 - 惯性高度和压力高度之间的偏差来开发至少一个中间回路参数。 该方法还包括观察从压力 - 惯性环路的一个中间参数获得的至少一个故障检测参数; 并且基于观察到的故障检测参数的值来确定飞机的一个传感器上的故障的存在。