Actuation device for opening an emergency exit flap of a cockpit door

Patent metadata

Field	Value
Publication number	US-9688379-B2
Application number	US-201213630287-A
Country	US
Kind code	B2
Filing date	Sep 28, 2012
Priority date	Sep 30, 2011
Publication date	Jun 27, 2017
Grant date	Jun 27, 2017

Abstract

An actuation device for opening an emergency exit flap of a cockpit door is provided. The actuation device comprises a support structure, at least two securing elements, an actuation element and a deflection mechanism. The support structure is configured so as to be fastened to the emergency exit flap. The securing elements are integrated into the support structure and are configured so as to fasten the actuation device, and thus the emergency exit flap, to the cockpit door. The actuation element is connected to the support structure. Therein, the deflection mechanism connects the securing elements to the actuation element in such a way that a force which is exerted on the actuation element is diverted in such a way that the securing elements are released from the cockpit door.

First claim

What is claimed is:

1. An actuation device for opening an emergency exit flap of a cockpit door, comprising:
a support structure which is fastenable to the emergency exit flap;
at least two securing elements which are integrated into the support structure and are configured so as to fasten the actuation device and the emergency exit flap to the cockpit door;
an actuation element which is connected to the support structure such that the actuation element is movable towards the emergency exit flap when the support structure is fastened to the emergency exit flap, wherein the actuation element comprises a recess or through hole;
a deflection mechanism which connects the securing elements to the actuation element so that a force, which is exerted on the actuation element, is diverted so that the securing elements are released from the cockpit door, wherein the deflection mechanism further comprises a displacement element that connects the securing elements to the actuation element, and wherein the displacement element pulls the securing elements into the support structure when the force is exerted on the actuation element, and wherein the displacement element is connected to the securing elements through the recess or through hole in the actuation element;
wherein the actuation element is designed as a kicking surface that is at an acute angle to an emergency exit flap surface when the support structure is fastened to the emergency exit flap and no force is exerted on the kicking surface and the actuation element is connected to the support structure in such a way that the angle becomes smaller when the kicking surface is pushed towards the emergency exit flap due to exertion of the force on the kicking surface and the deflection mechanism is actuated as a result.

2. The actuation device according to claim 1 , wherein the deflection mechanism further comprises: a first joint element, a first connecting rod and a second connecting rod.

3. The actuation device according to claim 2 , wherein the first connecting rod and second connecting rod each include a first end and a second end, with the first end of the first connecting rod connectable to the emergency exit flap and the second end of the second connecting rod connectable to the actuation element.

4. The actuation device according to claim 3 , wherein the second end of the first connecting rod and the first end of the second connecting rod are rotatably connected by the first joint element and wherein the force which is exerted on the actuation element is converted into a rotational movement of the first connecting rod and the second connecting rod about the joint element.

5. The actuation device according to claim 4 , wherein the rotational movement of the first connecting rod and the second connecting rod leads to the securing elements being released from the cockpit door.

6. The actuation device according to claim 1 , wherein a first spring element is provided on the actuation element and wherein the first spring element blocks the actuation element in an initial position until a predetermined force is exceeded.

Assignees

• Airbus Operations Gmbh

Inventors

• Koch Maik
• Breuer Matthias

Classifications

• B64C1/1469 Primary

  Doors between cockpit and cabin · CPC title

• B64C1/14

  Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens {accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers}(fairings movable in conjunction with undercarriage elements B64C25/16; bomb doors B64D1/06) · CPC title

• B64C1/32

  Severable or jettisonable parts of fuselage facilitating emergency escape · CPC title

• B64C1/18

  Floors · CPC title