公开(公告)号：US10752331B2

公开(公告)日：2020-08-25

申请号：US15773221

申请日：2016-11-02

申请人： LATECOERE

发明人： Cyrille Bessettes ,  Damien Buchet

IPC分类号： B64C1/14 ,  E05C3/16 ,  E05C17/00

摘要： An aircraft emergency exit door (10) with opening mechanisms integrated by a grouping of the mechanisms into a door beam (3) located on a given side of a window (16) of standard dimensions. In the beam, an inner handle (1) is mounted on a main shaft (102) connected with a locking shaft (8A) on which there is mounted, against return springs (83), a door blocking/locking mechanism (8) comprising a lock (81). A mechanism for conditionally opening the door (100) includes a vent flap (110), a pivot connection (12) for coupling the flap (110) to the inner handle (1), and a blocking shaft (120) that has, at each end, a pressure lever (121) equipped with supports for blocking (122) and unblocking (123) the flap (110). Return springs (32) mounted against the conditional opening mechanism (100) are calibrated to allow the opening of the flap (110) by exerting reduced pressure in residual pressure variation conditions, and to prevent it from opening in overpressure conditions.

公开(公告)号：US10240383B2

公开(公告)日：2019-03-26

申请号：US15728888

申请日：2017-10-10

申请人： LATECOERE

发明人： Cyrille Bessettes ,  Damien Buchet ,  Nicolas Lutzi ,  Renaud Othomene

IPC分类号： E05F15/70 ,  B64C1/14 ,  E05F15/40 ,  E05F15/60 ,  E05F11/54

摘要： An aircraft electric door including a locking system for actuating a safety catch for locking the door, a system for moving the door between open and closed positions, and a single electric motor for actuating both the locking system and the system for moving the door.

公开(公告)号：US10011363B2

公开(公告)日：2018-07-03

申请号：US14897426

申请日：2014-06-14

申请人： LATECOERE ,  JPR

发明人： Christophe Perrier ,  Cyrille Bessettes ,  Bernard Amalric ,  Bertrand Florentz ,  Antoine Torris ,  Olivier Come

IPC分类号： B64D15/12 ,  B64C1/14 ,  F16J15/06 ,  B64D15/04

CPC分类号： B64D15/12 ,  B64C1/1407 ,  B64D15/04 ,  F16J15/064

摘要： The invention aims to make aircraft doors easier to open by preventing ice formation or, at the very least, favoring rapid breaking of the ice on the door edges connected to the skin of the fuselage. To that end, it is provided to supply energy along the door when specific conditions are met. According to one embodiment, an anti-icing/de-icing system for an aircraft door (1) according to the invention includes an excitation energy source and devices (81 to 83) for dissipating such energy extending parallel to a side surface (11) of the aircraft door (1), along a sealing gasket (4) support (5) secured to the door (1) across from a fuselage (2) side surface (21) framing (20) the door (1). The sealing gasket (4) of the door (1) is compressed against bearing (6) from a side surface (25) of the fuselage (2) when the door (1) is closed.

公开(公告)号：US09816307B2

公开(公告)日：2017-11-14

申请号：US14443080

申请日：2013-11-14

申请人： LATECOERE

发明人： Cyrille Bessettes ,  Damien Buchet ,  Nicolas Lutzi ,  Renaud Othomene

IPC分类号： E05F15/70 ,  B64C1/14 ,  E05F15/40 ,  E05F15/60 ,  E05F11/54

CPC分类号： E05F15/70 ,  B64C1/1407 ,  B64C1/1423 ,  B64C1/1446 ,  E05F11/54 ,  E05F15/40 ,  E05F15/60 ,  E05Y2900/502

摘要： An aircraft electric door including a locking system for actuating a safety catch for locking the door, a system for moving the door between open and closed positions, and a single electric motor for actuating both the locking system and the system for moving the door.

公开(公告)号：US09783311B2

公开(公告)日：2017-10-10

申请号：US14897330

申请日：2014-06-13

申请人： LATECOERE

发明人： Cyrille Bessettes ,  Damien Buchet ,  Renaud Othomene

IPC分类号： B64C1/00 ,  B64D25/14 ,  B64C1/14

CPC分类号： B64D25/14 ,  B64C1/1407

摘要： The objective of the invention is to replace the rope bar of the door evacuation slide with individual connections. According to a preferred embodiment, the mechanism for arming/disarming an aircraft door evacuation slide (1, 15, 16) includes two releasable connectors (21) disposed to either side of the base of the door and each includes two half connectors (21s, 21i), a so-called upper half connector (21s, 41, 4a, 42) rigidly connected to the door (1) and having an attachment device (33) for attachment to the slide, and a so-called lower half connector (21i) fixed to the cabin floor (6). Each upper half connector (21s) includes a movable inner part controlled by a ring (43) and housed in the corresponding lower half-connector (21i). The mechanism can also include an electric motor coupled to two rods (31), each rod (31) being capable of rotating the control ring (43) of each upper half connector (21s) between two angular positions: an armed position and a disarmed position.

公开(公告)号：US11066864B2

公开(公告)日：2021-07-20

申请号：US16266432

申请日：2019-02-04

申请人： LATECOERE

发明人： Cyrille Bessettes ,  Damien Buchet ,  Nicolas Lutzi ,  Renaud Othomene

IPC分类号： E05F15/70 ,  B64C1/14 ,  E05F15/40 ,  E05F15/60 ,  E05F11/54

摘要： An aircraft electric door for a pressurized airframe having a locking system for locking a safety catch, a system for moving a door arm, and an electric motor activated by a door computer to actuate both systems. The system for moving the door arm includes a guideway linked to the door arm. The guideway is in a mobile cylindrical support rotated by the electric motor. A fixed guide is fitted in a cylindrical sleeve around the cylindrical support. The fixed guide includes a vertical camway and a horizontal camway. The door arm pivots around a vertical hinge and is linked with door lifting devices. The door lifting devices are mounted between a shaft of the safety catch and the door arm.

公开(公告)号：US20150292254A1

公开(公告)日：2015-10-15

申请号：US14443080

申请日：2013-11-14

申请人： LATECOERE

发明人： Cyrille Bessettes ,  Damien Buchet ,  Nicolas Lutzi ,  Renaud Othomene

IPC分类号： E05F15/70 ,  E05F15/60 ,  E05F15/40 ,  E05F11/54 ,  B64C1/14

CPC分类号： E05F15/70 ,  B64C1/1407 ,  B64C1/1423 ,  B64C1/1446 ,  E05F11/54 ,  E05F15/40 ,  E05F15/60 ,  E05Y2900/502

摘要： The invention aims to integrate the activation of the opening/closing phases around a single electric motor, including the treatment of the external window that may be present. An airplane electric door according to the invention has a locking system provided with means for locking a safety catch and a system (200) for coordinating door movements having a single actuating electric motor (2), a cylindrical support (501) having a vertical rotation axis (Z′Z), said support (501) being intended to be rotated by the motor (2), and a fixed guide (91). The support (501) has at least one guideway (511) connected to the arm (6), this guideway (511) being at least partially helical along the vertical axis (Z′Z) of the support (501). The fixed guide (9), which is likewise cylindrical with a vertical axis (Z′Z), possesses at least one double, vertical (91v) and horizontal (91h), camway for guiding the arm (6) successively in these two directions in a manner connected to the arm (6) in order to prevent it from lifting vertically and then to pivot it.

摘要翻译： 本发明旨在将打开/关闭阶段的激活集成在单个电动机周围，包括处理可能存在的外部窗口。 根据本发明的飞机电动门具有锁定系统，其具有用于锁定安全锁扣的装置和用于协调具有单个致动电动机（2）的门运动的系统（200），具有垂直旋转的圆柱形支撑件（501） 轴（Z'Z），所述支撑件（501）旨在由马达（2）旋转，以及固定引导件（91）。 支撑件（501）具有连接到臂（6）的至少一个导轨（511），该导轨（511）沿支撑件（501）的垂直轴线（Z'Z）至少部分地是螺旋形的。 同样圆柱形的具有垂直轴线（Z'Z）的固定引导件（9）具有至少一个用于在这两个方向上连续地引导臂（6）的双垂直（91v）和水平（91h） 以与臂（6）连接的方式，以防止其垂直提升然后使其枢转。