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公开(公告)号：EP2318272A2
公开(公告)日：2011-05-11
申请号：EP09790513.7
申请日：2009-07-16
CPC分类号： B64C25/24 , B64C25/12 , B64C25/30 , F16H25/205 , F16H25/2454 , F16H2025/2071 , F16H2025/2081 , H02K7/06
摘要： This disclosure relates to a landing gear system (10) that includes a landing gear strut (14) rotatable between stowed and deployed positions. An actuator (18) is connected to the landing gear strut, and includes main and emergency drives housed within a common body and operable independently from one another. A controller (32) in communication with the actuator (18) is configured to command the actuator between the stowed and deployed positions in response to an input. The controller (32) commands the main drive during a normal operating condition and commands the emergency drive in a failure condition of the main drive. The actuator (18) includes a body supporting emergency and main leadscrews arranged coaxially with one another. Main and emergency motors respectively are coupled to the main and emergency leadscrews. An output rod is supported by and extends from the body. The output rod is threadingly coupled to and is coaxial with the main leadscrew and configured to move axially in response to rotation of the main leadscrew. A brake selectively enables and disables the emergency drive.
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公开(公告)号：EP3418189A1
公开(公告)日：2018-12-26
申请号：EP18179489.2
申请日：2018-06-25
发明人： HOWELL, George , CRANE, Nicholas
摘要： Disclosed is a hydraulic system (300) for an aircraft. The hydraulic system (300) comprises a backup hydraulic pressure source (216) to provide hydraulic pressure to a brake (222) in the event of a failure condition of a primary hydraulic brake pressure source. The hydraulic system (300) also comprises a landing gear backup system to provide hydraulic pressure to enable extension and/or retraction of landing gear (100). The backup hydraulic pressure source (216) is arranged to provide hydraulic pressure to the landing gear backup system in the event of a failure condition of a primary landing gear hydraulic pressure source.
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24.发明授权
公开(公告)号：EP3141477B1
公开(公告)日：2018-11-14
申请号：EP16187980.4
申请日：2016-09-09
申请人： Embraer S.A.
发明人： Rogulski Filho, Carlos , Dias Ferraz, David , Tognozzi Lopes, Graco , Nunes De Mattos, Arilton , De Martino, Claudio
CPC分类号： B64C25/16 , B64C25/10 , B64C25/30 , B64C2025/125
摘要： Landing gear doors may be opened in an emergency event, e.g., a failure of the normal landing gear actuation system that requires a gravity free-fall deployment. The retractable aircraft landing gear door actuation mechanism will include a landing gear door (12-1) and a door support bracket (22) attached to the landing gear door. The support bracket (22) is attached to aircraft structure (10-1) for pivotal movement about a pivot axis (22-1a) between a closed condition whereby the landing gear door covers an aircraft landing gear when retracted relative to the aircraft structure, and an opened condition whereby the landing gear door is moved laterally and upwardly relative to the aircraft landing gear when extended relative to the aircraft structure. A gear door actuation assembly (40) is operatively connected to the door support bracket (22) for moving the door support bracket and the gear door supported thereby between the closed and opened conditions thereof. The gear door actuation assembly will include an over-the-center spring assembly (50) which assists in pivotal movement of the door support bracket (22) and the gear door (12-1) supported thereby from the closed condition into the opened condition thereof.
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公开(公告)号：EP2312721B1
公开(公告)日：2018-05-23
申请号：EP10183215.2
申请日：2010-09-30
CPC分类号： H02J4/00 , B60T2270/414 , B64C25/30 , B64C25/44 , B64D2221/00 , H02J9/00
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公开(公告)号：EP2902315A1
公开(公告)日：2015-08-05
申请号：EP15153618.2
申请日：2015-02-03
摘要： Some embodiments provide apparatuses configured to deploy a landing gear of an aircraft, comprising: a landing gear coupler 312 configured to couple with the landing gear; a release link 314 configured to cooperate the landing gear coupler with a drive shaft 114 that is configured to drive the landing gear between a stowed position and a deployed position; an override driver 316 cooperated with the landing gear coupler; wherein the release link is configured to releasably maintain a relative position of landing gear coupler relative to the drive shaft, and the release link is configured to disengage a coupling between the drive shaft and the landing gear coupler such that the landing gear coupler is configured to move independent of the drive shaft; and wherein the override driver is configured to drive the landing gear coupler to the deployed position.
摘要翻译： 一些实施例提供了被配置为展开飞机的起落架的装置，包括：起落架联接器312，其被配置为与起落架联接; 释放连杆314，该释放连杆314构造成将起落架联接器与驱动轴114配合，该驱动轴114构造成在收起位置和展开位置之间驱动起落架; 与起落架联接器配合的超控驱动器316; 其中所述释放连杆被构造成可释放地保持所述起落架连接器相对于所述驱动轴的相对位置，并且所述释放连杆被配置为使所述驱动轴和所述起落架连接器之间的连接脱离，使得所述起落架连接器被构造成 独立于传动轴移动; 并且其中所述超控驱动器被配置为将所述起落架联接器驱动到所述展开位置。
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28.发明公开Emergency gravity free-fall deployment systems for retractable aircraft landing gear assemblies 有权对于收放飞机起落架组件紧急重力自由下落部署系统
公开(公告)号：EP2878534A1
公开(公告)日：2015-06-03
申请号：EP14195780.3
申请日：2014-12-02
申请人： Embraer, S.A.
IPC分类号： B64C25/30
摘要： Systems are disclosed to allow for the landing gear doors to be opened in the event of an emergency gravity free-fall landing gear deployment with little or no contact with the landing gear tires. The emergency gear extension systems according to the embodiments disclosed herein thus permit the free-fall movement of the landing gear to be synchronized with the opening of the associated gear doors. That is, according to the embodiments disclosed herein deployment of the landing gear assembly is time-delayed relative to the opening of the associated gear door(s). In such a manner, the landing gear assembly is synchronously released only after the associated gear door is in a safe position during its opening sequence thereby avoiding the risk that the gear door will jam the full extension of the landing gear during an emergency gear deployment due to contact between the landing gear tires and the gear door.
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公开(公告)号：EP2855261A1
公开(公告)日：2015-04-08
申请号：EP13800839.6
申请日：2013-06-04
CPC分类号： F15B15/14 , B64C25/30 , F15B15/088 , F15B15/19 , F15B2211/8752 , F15B2211/8757 , F16H25/20 , F16H25/2015 , F16H2025/2071 , F16H2025/2081
摘要： An actuator assembly includes an actuation member, a release member, and a source of pressurized gas, wherein during a normal mode of operation, the actuation member and the release member are engaged to move in unison, and wherein during an emergency mode of operation, pressurized gas automatically decouples the actuation member from the release member to move separately. In accordance with yet other aspects of the present disclosure, an electro-mechanical actuator includes an electro-mechanical drive system and an integrated backup system operated by a gas generator, wherein when the backup system is activated, the electro-mechanical drive system is decoupled and the actuator moves to a predetermined position and mechanically locks in place.
摘要翻译： 致动器组件包括致动构件，释放构件和加压气体源，其中在正常操作模式期间，致动构件和释放构件接合以一致地移动，并且其中在紧急操作模式期间， 加压气体将致动构件与释放构件自动分离以单独移动。 根据本公开的其他方面，一种机电致动器包括机电驱动系统和由气体发生器操作的集成备用系统，其中当备用系统被激活时，机电驱动系统被解耦 并且致动器移动到预定位置并且机械锁定就位。
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30.发明公开Procédé de gestion de systèmes liés au train d'atterrissage d'un aéronef 有权Steuerverfahren在Verbindung mit einem Flugzeugfahrwerk
公开(公告)号：EP2604518A1
公开(公告)日：2013-06-19
申请号：EP12195974.6
申请日：2012-12-06
发明人： Frank, David
摘要： L'invention concerne un procédé de gestion d'aéronef comportant des atterrisseurs portant un certain nombre de roues freinées, l'aéronef comportant :
- un système de manoeuvre des atterrisseurs comportant des actionneurs de manoeuvre (105, 205, 305) et d'accrochage (106, 206, 306) des atterrisseurs et de trappes associées,
- un système de freinage comportant des actionneurs de freinage des roues de l'aéronef;
- au moins une unité de commande (A1, A2, B1, B2) pour commander la manoeuvre des atterrisseurs et le freinage ;
- au moins un boîtier de maintenance (BM1) pour commander sélectivement au moins certains des actionneurs desdits systèmes alors que l'aéronef est dans l'état éteint lors d'opérations de maintenance de l'un ou l'autre des systèmes.
Selon l'invention le procédé comporte l'étape d'activer le boîtier de maintenance alors que l'aéronef n'est pas à l'état éteint pour assurer, au moyen du boîtier de maintenance, l'actionnement des actionneurs reliés au boîtier de maintenance, notamment en cas de défaillance de l'unité de commande.摘要翻译： 该方法涉及执行执行器的底盘操作和底架和相关联的门锁的固定操作。 制动器具有用于制动飞行器的车轮的致动器。 提供控制单元来命令起落架的运行和制动。 提供维护案例以选择性地命令系统的执行器，其中飞行器在维护动作时处于熄灭状态。 在控制单元发生故障的情况下，确保连接到维护壳体的致动器的致动。
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