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1. 发明授权

US11192640B2 System for emergency extension of aircraft landing gear 有权
公开(公告)号：US11192640B2
公开(公告)日：2021-12-07
申请号：US15902869
申请日：2018-02-22
申请人： SAFRAN LANDING SYSTEMS
发明人： Raphaël Pierra , Mathieu Rousselet , Vincent Pascal , Jean-Luc Belleval
IPC分类号： B64C25/24 , F15B21/10 , B64C25/30 , B64C25/20 , H02J4/00
摘要： An emergency extension system for extending at least one aircraft undercarriage, the emergency extension system comprising both electromechanical actuators, each electromechanical actuator having an identification component arranged to allocate an identifier to said electromechanical actuator, which identifier depends in particular on a function performed by said electromechanical actuator, and also an electrical card having a delay component arranged to delay actuation of a the electromechanical actuator by an actuation delay that depends on the identifier allocated to the electromechanical actuator, the electromechanical actuators of the emergency extension system thus being arranged to be actuated in succession in an actuation sequence that is defined by the actuation delays.

2. 发明申请

US20190031325A1 EMISSION-CAPTURING APPARATUS AND METHOD FOR CAPTURING EMISSIONS FROM AN EJECTION PORT 审中-公开
公开(公告)号：US20190031325A1
公开(公告)日：2019-01-31
申请号：US16139773
申请日：2018-09-24
申请人： Gulfstream Aerospace Corporation
发明人： James Perdue , Jeffrey Slump , Bret Bell
IPC分类号： B64C25/22 , B64C25/30
摘要： An emission-capturing apparatus includes a tank having an inlet and an outlet. The apparatus further includes a muffler fluidly coupled with the outlet to intercept fluid exiting the outlet, permit passage of gas through the muffler, and inhibit passage of liquid through the muffler. The apparatus further includes a hose having a tank end and a distal end. The tank end is coupled to the inlet. The apparatus further includes a fitting fluidly coupled to the distal end of the hose. The fitting is configured to be fluidly coupled to an end section of an ejection port of a vehicle to receive an emission from the ejection port.

3. 发明授权

US10179644B2 Method for operating a landing gear system 有权
公开(公告)号：US10179644B2
公开(公告)日：2019-01-15
申请号：US15183428
申请日：2016-06-15
申请人： AIRBUS OPERATIONS, S.L. , AIRBUS OPERATIONS S.A.S. , AIRBUS OPERATIONS LTD.
发明人： Ramon Abarca Lopez , Marcus Barth , Norman Wood
IPC分类号： B64C25/18 , B64C25/30 , B64C25/04 , B64C25/16 , B64C25/00
摘要： The present disclosure refers to a method for operating a landing gear system, preferably in a tricycle configuration, wherein main landing gear (MLG) and the nose landing gear (NLG) are operable from a retracted position where they are housed respectively inside landing gear bays, to a fully extended position where they are extended for landing the aircraft. According to the disclosure, the extension of the nose landing gear (NLG) is delayed in time with respect to the extension of the main landing gear (MLG), and the nose landing gear (NLG) is kept retracted during a major part of the time that the main landing gear doors (MLGD) are extended. In this manner, vibrations on the main landing gear doors are reduced and incidents caused by fatigue are also reduced, which in turn implies that the maintenance cost of the aircraft is greatly reduced.

4. 发明授权

US09334046B2 Device for maneuvering, on the ground, a door of an aircraft landing gear 有权
标题翻译：在地面上操纵飞机起落架门的装置
公开(公告)号：US09334046B2
公开(公告)日：2016-05-10
申请号：US13624181
申请日：2012-09-21
申请人： MESSIER-BUGATTI-DOWTY
发明人： Gilbert Lecourtier , Pierre-Yves Liegeois
IPC分类号： B64C25/16 , B64C25/18 , B64C25/26 , B64C25/28 , B64C25/30
CPC分类号： B64C25/30 , B64C25/16 , B64C25/18 , B64C25/26 , B64C25/28
摘要： The invention relates to a device for maneuvering, on the ground, a door of an aircraft landing gear, the door being linked with door maneuvering means and uplock means for locking the door when it reaches the closed position, at least one unlocking electromechanical actuator arranged to act upon the uplock means with a view to deactivating them during opening of the door in flight. According to the invention, the device comprises control means 17 which can be operated by an operator on the ground in order to control at least: an opening sequence during which the unlocking electromechanical actuator is actuated in order to deactivate the uplock means, a closing sequence during which the maneuvering means are actuated in order to close the door again.
摘要翻译：本发明涉及一种用于在地面上操纵飞机起落架的门的装置，该门与门操纵装置相连，门锁装置用于在门到达关闭位置时锁定门，至少一个解锁机电致动器被布置成以起动装置的作用，以便在驾驶舱门打开期间停用它们。根据本发明，该装置包括控制装置17，其可由操作者在地面上操作，以至少至少控制：解锁机电致动器致动以打开上锁装置的打开顺序，关闭顺序在此期间，操纵机构被致动以再次关闭门。

5. 发明申请

US20150151832A1 EMERGENCY GRAVITY FREE-FALL DEPLOYMENT SYSTEMS FOR RETRACTABLE AIRCRAFT LANDING GEAR ASSEMBLIES 有权
标题翻译：适用于可撤销的飞机起落架组件的紧急重力自由落地系统
公开(公告)号：US20150151832A1
公开(公告)日：2015-06-04
申请号：US14094009
申请日：2013-12-02
申请人： EMBRAER S.A.
发明人： Carlos Rogulski FILHO
IPC分类号： B64C25/30 , B64C25/22 , B64C25/20
CPC分类号： B64C25/30 , B64C25/16 , B64C25/20 , B64C25/22
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.
摘要翻译：系统被公开以允许起落架门在紧急重力自由落体起落架展开而与起落架轮胎接触很少或不接触的情况下打开。因此，根据本文公开的实施例的应急齿轮延伸系统允许起落架的自由下落运动与相关联的齿轮门的开口同步。也就是说，根据本文公开的实施例，起落架组件的部署相对于相关联的齿轮门的打开是延时的。以这种方式，起落架组件仅在相关联的齿轮门在其打开顺序期间处于安全位置之后才同步释放，从而避免了在应急齿轮部署过程中齿轮门将堵塞起落架的完全伸展的风险，在起落架轮胎和齿轮门之间接触。

6. 发明申请

US20150122945A1 PASSENGER AIRCRAFT WITH AUTOMATICALLY DEPLOYABLE AND/OR RETRACTABLE LANDING GEAR 审中-公开
标题翻译：具有自动可分配和/或可回收的起落架的乘客飞机
公开(公告)号：US20150122945A1
公开(公告)日：2015-05-07
申请号：US14088317
申请日：2013-11-22
申请人： Peter Apostolos Kavounas
发明人： Peter Apostolos Kavounas
IPC分类号： B64C25/30
CPC分类号： B64C25/30
摘要： In embodiments, a passenger aircraft includes a body and a landing gear member that is retractable and deployable with respect to the body. The passenger aircraft also includes an altitude detection system. The landing gear member may become deployed automatically if a deploy condition related to the detected altitude is met, and/or retracted automatically if a retract condition related to the detected altitude is met. Accordingly, the action of deploying and/or retracting the landing gear becomes something that the pilot need only supervise, instead of doing. In addition, embodiments may become a helpful safety feature, in the event the pilot has become distracted.
摘要翻译：在实施例中，客机包括主体和起落架构件，其相对于主体可缩回和展开。客机还包括高度检测系统。如果与检测到的高度相关的部署条件得到满足，起落架构件可自动部署，并且/或者如果满足与检测到的高度有关的缩回条件，则自动缩回。因此，部署和/或缩回起落架的动作成为飞行员只需要监督而不是做的事情。此外，在飞行员已经分心的情况下，实施例可以成为有用的安全特征。

7. 发明授权

US08851419B2 Method and apparatus for changing a deployed position for a tail skid assembly 有权
标题翻译：用于改变尾部滑行组件的展开位置的方法和装置
公开(公告)号：US08851419B2
公开(公告)日：2014-10-07
申请号：US13416914
申请日：2012-03-09
申请人： Justin Duane Cottet
发明人： Justin Duane Cottet
IPC分类号： B64C25/30
CPC分类号： B64C25/32 , B64C25/52 , B64C25/58 , B64C2025/005
摘要： A method and apparatus for positioning a tail skid assembly for a maximum rotation angle for an aircraft may be provided. A determination may be made as to whether the tail skid assembly is to be deployed for takeoff or landing. A set of parameters may be identified based on a determination of whether the tail skid assembly is to be deployed for takeoff or landing. A desired maximum rotation angle for the aircraft may be identified using the set of parameters. The tail skid assembly may be deployed to allow the desired maximum rotation angle for the aircraft.
摘要翻译：可以提供一种用于定位用于飞行器的最大旋转角度的尾部滑行组件的方法和装置。可以确定尾部滑行组件是否要用于起飞或着陆。可以基于是否将部署用于起飞或着陆的尾部滑行组件的确定来识别一组参数。可以使用该组参数来识别用于飞行器的期望的最大旋转角度。尾部滑行组件可以被部署以允许飞机的期望的最大旋转角度。

8. 发明授权

US08827202B2 Method of managing the steering of aircraft wheels, in particular in the event of a tire bursting or deflating 有权
标题翻译：管理飞机轮子的转向的方法，特别是在轮胎爆裂或排气的情况下
公开(公告)号：US08827202B2
公开(公告)日：2014-09-09
申请号：US13546215
申请日：2012-07-11
申请人： Michael Benmoussa , Jerome Fraval
发明人： Michael Benmoussa , Jerome Fraval
IPC分类号： B64C25/50 , B64C25/30
CPC分类号： B64C25/30 , B64C25/50
摘要： A method of managing the steering of aircraft undercarriage wheels carried by a steerable bottom portion of the undercarriage, the bottom portion being associated with steering control including a steering member suitable for steering the bottom portion of the undercarriage in response to a steering order. The method comprises the steps of (1) monitoring the pressures of the tires carried by the wheels, and in response to detecting at least one of the following events: (1A) the pressure of one of the tires is less than a first predetermined threshold, and ( 1B) the difference between the pressures of two of the tires is greater than a second determined threshold; (2) activating the steering control, if the steering control is not activated; and (3) implementing a steering control relationship that is modified compared with a nominal control relationship used when the tires are properly inflated.
摘要翻译：一种管理由起落架的可转向底部承载的飞行器底架系统的转向的方法，底部与转向控制相关联，转向控制包括适于根据转向顺序转向起落架底部的转向构件。该方法包括以下步骤：（1）监测由车轮承载的轮胎的压力，并且响应于检测到以下事件中的至少一个：（1A）轮胎中的一个的压力小于第一预定阈值，（1B）两个轮胎的压力差大于第二确定的阈值; （2）如果转向控制未被激活，则启动转向控制; 和（3）实现与轮胎适当充气时使用的标称控制关系相比被修改的转向控制关系。

9. 发明申请

US20110042511A1 APPARATUS FOR USE ON AN AIRCRAFT 有权
标题翻译：用于飞机的装置
公开(公告)号：US20110042511A1
公开(公告)日：2011-02-24
申请号：US12859324
申请日：2010-08-19
申请人： Nicholas ELLIOTT , Arnaud DIDEY , John W. GRIFFIN
发明人： Nicholas ELLIOTT , Arnaud DIDEY , John W. GRIFFIN
IPC分类号： B64C25/30 , F16H25/20 , F16H25/22
CPC分类号： B64C13/34 , B64C13/42 , B64C25/20 , B64C25/30 , F16H25/20 , F16H2025/2068 , Y10T74/18592 , Y10T74/186
摘要： An actuator is arranged to move an aircraft component such as a landing gear leg, flap or aileron between a first position and a second position, net load from external forces acting on the aircraft component tending to drive it towards the first position. The actuator comprises a threaded screw and a threaded nut. A main prime mover is configured to apply torque to the screw or nut acting in opposition to the net load under normal operating conditions. An emergency prime mover is configured to apply torque to the screw or nut acting in the same sense as the net load under emergency operating conditions in which the interface between the nut and the screw has become partially jammed to the extent that the component cannot be moved from the second position to the first position by operation of the net load alone.
摘要翻译：致动器被布置成在第一位置和第二位置之间移动诸如起落架腿，翼片或副翼的飞行器部件，从作用在飞行器部件上的外力的净载荷倾向于将其驱动到第一位置。致动器包括螺纹螺纹和螺纹螺母。主原动机被配置为在正常操作条件下对与负载负荷相反的螺杆或螺母施加扭矩。紧急原动机被配置为对螺母或螺母施加扭矩，该螺钉或螺母在紧急操作条件下以与净负载相同的意义作用，螺母和螺母在螺母和螺钉之间的界面已经部分地卡塞到组件不能移动的程度从第二个位置到第一个位置，通过净负荷的操作。

10. 发明授权

US11299261B2 Landing gear system operation 有权
公开(公告)号：US11299261B2
公开(公告)日：2022-04-12
申请号：US16799896
申请日：2020-02-25
申请人： AIRBUS OPERATIONS LIMITED
发明人： Sean Kerr , David Marles
IPC分类号： B64C25/30 , B64C13/16 , B64C25/28 , B64D45/04
摘要： An aircraft landing gear control system 1000 configured to be operably connected to one or more landing gear systems 30, 40 of an aircraft. The aircraft landing gear control system includes a controller 20 configured to: send at least one output for initiating operation of the one or more landing gear systems; determine whether at least one landing gear system of the one or more landing gear systems has failed to operate correctly in response to the at least one output; and determine at least one remedial action to be taken, when the controller determines that the at least one landing gear system has failed to operate correctly.

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