Latecoere

Rohr, Inc.

Bombardier Inc.

Latecoeye

Short Brothers Plc

Damien Buchet

Cyrille Bessettes

Renaud Othomene

Nicolas Lutzi

John Richard Savidge

Ken Minchau

Keith Wood

Eric Lee

Gildas Martin

Denis Chabot

Michel Tourangeau

An interlock assembly for an aircraft door includes a shaft, an interlock first portion, and an auto-disarm second portion. The shaft is rotatable about the second rotational axis between an armed position and a disarmed position. The shaft includes an interlock cam and an auto-disarming cam. In a first interlock position, the interlock first portion permits rotation of the shaft between the armed position and the disarmed position. In a second interlock position, the interlock first portion prevents rotation of the shaft from the disarmed position to the armed position. In a first auto-disarm position, the auto-disarm second portion permits rotation of the shaft between the armed position and the disarmed position. In a second auto-disarm position, the auto-disarm second portion prevents rotation of the shaft from the disarmed position to the armed position.

Interlock assembly for an aircraft door

A door assembly for an aircraft includes a door, an interior door handle and an exterior door handle, and a clutch assembly. The interior door handle and the exterior door handle are rotatable about a door handle rotational axis. The clutch assembly includes a shaft, an exterior coupling body, an exterior handle body, and a clutch lever. The shaft includes an interface portion. The interface portion includes a handle tooth. The exterior coupling body includes a fixed body portion disposed adjacent the interface portion. The exterior handle body is rotatably mounted to the exterior coupling body. The exterior handle body is rotatable between and to an engaged position and a disengaged position. The clutch lever is rotatably mounted to the exterior coupling body. The clutch lever is pivotable between and to an engaged pivot position and a disengaged pivot position. In the engaged pivot position, the handle tooth is positioned circumferentially between the clutch lever and the fixed body portion.

Clutch assembly for an aircraft door

A door assembly () for an aircraft is moveable between a closed position and a disengaged position and comprises a door frame (), a hinge arm () pivotally coupled to the door frame (), and a door (). A support bracket () pivotally supports the door () on the hinge arm (). The door frame () and door () each comprise at least one stop () configured to engage with each other to retain the door () within the door frame () in the closed position. At least one pin () is mounted on each side of the door () and at least first and second guides () are coupled to the sides of the door frame (). Each guide () comprises a channel () receiving a pin ().

Door mechanism

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.

Locking and moving system for an aircraft electric door

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

Aircraft emergency exit door with integrated mechanisms and method for opening/closing such a door

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.

Apparatus for opening and closing an aircraft electric door

A system for opening a door of an aircraft includes a connection assembly adapted to connect the door to a fuselage section of the aircraft. The connection assembly includes a main hinge pivotally connected to the fuselage section and a link assembly connecting the door to the main hinge and pivotally connected to the fuselage section, the link assembly including one member slidingly and pivotally connected to the door. The system also includes a latch mechanism between the door and the main hinge, the latch mechanism being adapted to be actuated. The system is adapted to move the door upwardly and inwardly along a predetermined path without moving the main hinge through movement of the latch mechanism and, subsequently, to pivot the door around a virtual pivot point located outside of the aircraft by moving the main hinge once the door has reached an end of the predetermined path.

Connection assembly for aircraft door

Method for opening/closing an aircraft electric door for a pressurized airframe and door for implementing same

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 () includes two releasable connectors () disposed to either side of the base of the door and each includes two half connectors (), a so-called upper half connector () rigidly connected to the door () and having an attachment device () for attachment to the slide, and a so-called lower half connector () fixed to the cabin floor (). Each upper half connector () includes a movable inner part controlled by a ring () and housed in the corresponding lower half-connector (). The mechanism can also include an electric motor coupled to two rods (), each rod () being capable of rotating the control ring () of each upper half connector () between two angular positions: an armed position and a disarmed position.

Growing community of inventors

Toulouse, France

Damien Buchet