公开(公告)号：US20210179253A1

公开(公告)日：2021-06-17

申请号：US16771874

申请日：2018-12-13

Applicant: LATECOERE

Inventor： Christian ROMEC ,  Renaud OTHOMENE

IPC: B64C1/14

Abstract: The invention relates to an opening system (10) for an auxiliary door (20) of an airplane in a fuselage (30), the door and the fuselage having skins in the extension of one another. In one exemplary embodiment, the system (10) includes a framing lintel (11) integrated into the fuselage, an upper beam (2S) of the door structure arranged opposite the lintel (11), and a set of three lever links (4A, 4B, 4C). Each link is connected, on the one hand, to the lintel (11) by a lever articulation (5a, 6a) fixed relative to the fuselage (30) and, on the other hand, to the upper beam (2S) by a lever articulation (5b, 6b) mobile with the door (20), the articulations (5a, 5b; 6a, 6b) being connected respectively to the lintel (11) and to the upper beam (2S) by fittings (41, 43; 42, 44). The set of links includes two types of link mounted alternately, in which the mobile articulation (5b, 6b) remains positioned respectively close to the fuselage skin (30) and further from this skin (30), the articulations (5a, 5b; 6a, 6b) of two adjacent levers (4A, 4B; 4B, 4C) forming an evolving quadrilateral.

公开(公告)号：US20190169915A1

公开(公告)日：2019-06-06

申请号：US16266432

申请日：2019-02-04

Applicant: LATECOERE

Inventor： Cyrille BESSETTES ,  Damien BUCHET ,  Nicolas LUTZI ,  Renaud OTHOMENE

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

Abstract: 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.

公开(公告)号：US20180044969A1

公开(公告)日：2018-02-15

申请号：US15728888

申请日：2017-10-10

Applicant: LATECOERE

Inventor： Cyrille BESSETTES ,  Damien BUCHET ,  Nicolas LUTZI ,  Renaud OTHOMENE

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

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

Abstract: 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.

公开(公告)号：US20160107755A1

公开(公告)日：2016-04-21

申请号：US14897330

申请日：2014-06-13

Applicant: LATECOERE

Inventor： Cyrille BESSETTES ,  Damien BUCHET ,  Renaud OTHOMENE

IPC: B64D25/14 ,  B64C1/14

CPC classification number: B64D25/14 ,  B64C1/1407

Abstract: 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.

Abstract translation: 本发明的目的是用单独的连接来更换门疏散滑块的绳条。 根据优选实施例，用于布置/撤防飞机门排气滑架（1,15,16）的机构包括两个可释放的连接器（21），其设置在门的基座的任一侧，并且每个包括两个半连接器（21s， 21i），刚性地连接到门（1）并且具有用于附接到滑块的附接装置（33）的所谓的上半部连接器（21s，41,4a，42）和所谓的下半连接器 21i）固定在机舱地板（6）上。 每个上半部连接器（21s）包括由环（43）控制并容纳在相应的下半连接器（21i）中的可移动内部部分。 该机构还可以包括耦合到两个杆（31）的电动马达，每个杆（31）能够使每个上半连接器（21s）的控制环（43）在两个角度位置之间旋转：武装位置和撤防 位置。