公开(公告)号：US20240076923A1

公开(公告)日：2024-03-07

申请号：US18262022

申请日：2022-01-14

Applicant: LATECOERE

Inventor： Martin Gildas

IPC: E05F7/00 ,  B64C1/14

CPC classification number: E05F7/005 ,  B64C1/143 ,  E05Y2201/638 ,  E05Y2201/686 ,  E05Y2900/502

Abstract: An assembly for providing stabilising guidance to a semi-plug aircraft door equipped with an opening/closing mechanism. The door frame (3) is provided with stops (7) at the front and at the rear of the door with its stops (8) bears when it is closed. A door arm (4) links the door (2) to the door frame (3). A guiding connecting rod (6), referred to as a stabilising guiding connecting rod and located on a door edge (2h) extending parallel to the longitudinal axis of the vehicle, is mobile, being able to move in translation at one of its ends in relation to the door in the longitudinal direction of the aircraft during the phases of disengaging and re-engaging the stops (7, 8). During the swivelling and swivelling return phases, the stabilising rod (6) is locked to the door by a lever locking mechanism (9) being actuated by a return device.

公开(公告)号：US20210323654A1

公开(公告)日：2021-10-21

申请号：US17284733

申请日：2019-10-16

Applicant: LATECOERE

Inventor： Martin Gildas

IPC: B64C1/14

Abstract: Aircraft door (1) including an opening (4), a frame (3), a hinge structure (5) and a circular translation guide device designed to maintain the orientation of the opening (4) during the opening or closing thereof. The hinge structure (5) is connected to the opening (4) by a lifting arm (8) allowing a lifting movement of the opening (4) relative to the hinge structure (5). The circular translation guide device includes a single link (11) connected to the frame (3) by one of the ends thereof and by the other of the ends thereof to a lever (13) which is attached to the hinge structure (5).

公开(公告)号：US11718382B2

公开(公告)日：2023-08-08

申请号：US17284738

申请日：2019-10-16

Applicant: LATECOERE

Inventor： Martin Gildas

IPC: B64C1/14 ,  E05F7/02

CPC classification number: B64C1/1461 ,  B64C1/143 ,  E05F7/02 ,  E05Y2900/502 ,  E05Y2900/531

Abstract: Aircraft door (1) having: an opening panel (2) provided with engagement abutments (26); a frame (3) intended to be attached to the fuselage (4) of the aircraft and including engagement counter-abutments (27); a hinge arm (5); a lifting lever (10); and a rotary control lever (20) which can be operated in a disengagement direction in order to unlock the opening panel (2). The door includes a one-way operating rod (18) which connects the control lever (20) to the lifting lever (10) and is designed to drive the lifting lever (10) only when the control lever (20) is actuated in the direction of disengagement.

公开(公告)号：US11597493B2

公开(公告)日：2023-03-07

申请号：US17284733

申请日：2019-10-16

Applicant: LATECOERE

Inventor： Martin Gildas

IPC: B64C1/14

Abstract: Aircraft door (1) including an opening (4), a frame (3), a hinge structure (5) and a circular translation guide device designed to maintain the orientation of the opening (4) during the opening or closing thereof. The hinge structure (5) is connected to the opening (4) by a lifting arm (8) allowing a lifting movement of the opening (4) relative to the hinge structure (5). The circular translation guide device includes a single link (11) connected to the frame (3) by one of the ends thereof and by the other of the ends thereof to a lever (13) which is attached to the hinge structure (5).

公开(公告)号：US20210323655A1

公开(公告)日：2021-10-21

申请号：US17284738

申请日：2019-10-16

Applicant: LATECOERE

Inventor： Martin Gildas

IPC: B64C1/14 ,  E05F7/02

Abstract: Aircraft door (1) having: an opening panel (2) provided with engagement abutments (26); a frame (3) intended to be attached to the fuselage (4) of the aircraft and including engagement counter-abutments (27); a hinge arm (5); a lifting lever (10); and a rotary control lever (20) which can be operated in a disengagement direction in order to unlock the opening panel (2). The door includes a one-way operating rod (18) which connects the control lever (20) to the lifting lever (10) and is designed to drive the lifting lever (10) only when the control lever (20) is actuated in the direction of disengagement.