Aircraft with integrated jettison mechanism

Patent metadata

Field	Value
Publication number	US-9527574-B2
Application number	US-201414217853-A
Country	US
Kind code	B2
Filing date	Mar 18, 2014
Priority date	Mar 18, 2013
Publication date	Dec 27, 2016
Grant date	Dec 27, 2016

Abstract

An aircraft ( 1 ) with jettison mechanism, particularly a helicopter, comprising an airframe ( 2 ), at least one door ( 5 ) movably mounted to the airframe ( 2 ), at least one door lock mechanism ( 9 ) at an interface of said at least one door ( 5 ) with the airframe ( 2 ) to releasable mount the at least one door ( 5 ) relative to the airframe ( 2 ) and actuation means ( 11 ) for the at least one door lock mechanism ( 9 ). An emergency jettison button ( 20, 38 ) is integrated into handles ( 11, 12 ) of said actuation means.

First claim

What is claimed is:

1. An aircraft with jettison mechanism, comprising:
an airframe;
at least one door with connection means comprising at least one of a guide arm and a hinge to movably mount the door to the airframe;
at least one door lock mechanism mounted to the door at an interface of the door with the airframe to releasably lock the door to the airframe; and
actuation means comprising at least one handle mounted to the door for actuation of the door lock mechanism;
at least one emergency button integrated in and moveable relative to the handle, the emergency button in communication with the connection means to jettison the door from the aircraft upon actuation by severing all connections of the door to the airframe;
wherein the handle has a hollow casing, a pin and a spring disposed inside the hollow casing; the pin being mounted to slide relative to the handle upon actuation of the emergency button against the spring; and the emergency button being for activation of the pin for completely separating at least one of the guide arm and the hinges of the connection means from the airframe for jettisoning of the door.

2. The aircraft according to claim 1 , wherein the handle comprises a protective cover and the emergency button is behind the protective cover.

3. The aircraft according to claim 1 , wherein the actuation means comprises at least one of: an internal handle and an external.

4. The aircraft according to claim 3 , wherein the external handle has an aerodynamic cover.

5. The aircraft according to claim 1 , wherein the emergency button is connected to the actuation means of the connection means, from the handle to the connection means by at least one of: a Bowden cable or push-pull-rod.

6. The aircraft according to claim 1 , wherein the handle casing is provided with a lateral cover for insertion of the emergency button, the pin and the further spring.

7. The aircraft according to claim 1 , wherein the aircraft is a helicopter.

8. An aircraft comprising:
an airframe;
a door connected to the airframe by a hinge to move the door relative to the airframe between an opening position and a closed position;
a door lock mechanism mounted to the door to releasably lock the door to in the closed position;
a handle mounted to the door for actuation of the door lock mechanism; and
an emergency button disposed on the handle and movable relative to the handle, the emergency button in communication with the hinge when actuated,
wherein actuation of the emergency button operatively connects the handle to the hinge so that actuation of the handle unlocks the door lock mechanism and separates the hinge from at least one of the door and the airframe to jettison the door from the aircraft, thereby completely separating the door from the airframe.

9. The aircraft according to claim 8 wherein the handle is mounted to rotate about a shaft, wherein rotating the handle about the shaft actuates the door lock mechanism.

10. The aircraft according to claim 8 further comprising a pin and a spring disposed inside a handle casing, the pin mounted to slide relative to the handle casing between first and second positions in response to actuation of the emergency button against the spring, wherein when emergency button moves the pin to the second position, the handle is operatively connected to the hinge.

11. The aircraft according to claim 10 wherein further comprising a jettison linkage connected to the hinge, wherein in the first position the handle is not connected to the hinge, and in the second position, the handle is operatively connected to the hinge via the linkage.

12. The aircraft according to claim 11 wherein the jettison mechanism further comprises at least one of a cable and a push-pull rod operatively connected between the handle and the hinge, wherein rotation of the handle moves the at least one of the cable and the push-pull rod to separate the hinge from the at least one of the door and airframe.

13. The aircraft according to claim 11 wherein the jettison mechanism further comprises a second shaft mounted coaxially with the handle shaft, wherein the second shaft is locked to the handle shaft when the pin is in the second position.

14. The aircraft according to claim 8 further comprising a protective cover removeably mounted on the handle, wherein the emergency button is covered by the protective cover, wherein actuation of the button requires the protective cover to be removed.

15. An aircraft comprising:
an airframe;
a door connected to the airframe by a hinge to move the door relative to the airframe between an opening position and a closed position;
a door lock mechanism mounted to the door to releasably lock the door in the closed position;
a handle mounted to rotate on a handle shaft, wherein rotating the handle and thereby the handle shaft actuates the door lock mechanism; and
a door jettison mechanism comprising:
an emergency button disposed on the handle and movable relative a casing of the handle;
a pin and a spring disposed inside the handle casing, the pin mounted to slide relative to the handle casing between first and second positions in response to actuation of the emergency button against the spring;
a linkage operatively connected to the hinge, wherein when the pin is in the second position, the handle is operatively connected to the hinge via the linkage,

wherein actuation of the emergency button with rotation of the handle unlocks the door and separates the hinge from at least one of the door and the airframe, thereby completely separating the door from the airframe allowing the door to be jettisoned from the aircraft.

16. The aircraft according to claim 15 wherein the linkage further comprises a second shaft mounted coaxially with the handle shaft, wherein the second shaft is locked to the handle shaft when the pin is in the second position.

17. The aircraft according to claim 16 wherein the linkage further comprises a cable operatively connected between the second shaft and the hinge, wherein rotation of the second shaft moves the cable to separate the hinge from the at least one of the door and airframe.

18. The aircraft according to claim 16 wherein the linkage further comprises a push-pull rod operatively connected between the second shaft and the hinge, wherein rotation of the second shaft moves the push-pull rod to separate the hinge from the at least one of the door and airframe.

19. The aircraft according to claim 15 wherein the second shaft comprises a notch formed along a periphery, the pin engaging the notch when the pin is in the second position.

20. The aircraft according to claim 15 , further comprising a protective cover removeably mounted on the handle casing, wherein the emergency button is covered by the protective cover, wherein actuation of the button requires the protective cover to be removed.

Assignees

• Airbus Helicopters Deutschland GmbH

Inventors

• Steger Justus
• Gorlich Stefan

Classifications

• B64C1/1461

  Structures of doors or surrounding frames · CPC title

• B64C1/32 Primary

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

• B64C1/1423

  Passenger doors · CPC title