Dekompressionsanordnung mit Zwei Dekompressionsöffnungen

Details

Veröffentlichungs-Nr.

EP3170739

Aktenzeichen

EP15195571

Anmeldetag

20. November 2015

Veröffentlichung

27. Februar 2019

Erteilung

27. Februar 2019

Rechtsraum

EP

IPC

B64C1/06B64D13/04B64C1/00

Abstract

A decompression assembly (10) for use in an aircraft, the decompression assembly (10) comprises a cabin lining element (12), an opening (18) formed in the cabin lining element (12) and an air channel (22) which is arranged adjacent to a rear face (24) of the cabin lining element (12) and connected to the opening (18) formed in the cabin lining element (12). The air channel (22) is provided with an air outlet (28) which, during normal operation of the decompression assembly (10), is adapted to discharge air exiting an aircraft cabin region (26) delimited by the cabin lining element (12) through the opening (18) formed in the cabin lining element (12) into an aircraft area (30) located between the cabin lining element (12) and an aircraft outer skin (32), a first decompression opening (36), and a first decompression flap (40) which, during normal operation of the decompression assembly (10), is adapted to close the first decompression opening (36) provided in the air channel (22) and which, in the event of a rapid decompression, is adapted to open the first decompression opening (36) so as to allow a pressure equalization between the aircraft cabin region (26) delimited by the cabin lining element (12) and the aircraft area (30) located between the cabin lining element (12) and the aircraft outer skin (32). The decompression assembly (10) further comprises a second decompression opening (50) formed in the cabin lining element (12), and a second decompression flap (52) which, during normal operation of the decompression assembly (10), is adapted to close the second decompression opening (50) formed in the cabin lining element (12) and which, in the event of a rapid decompression, is adapted to open the second decompression opening (50) so as to allow a pressure equalization between the aircraft cabin region (26) delimited by the cabin lining element (12) and the aircraft area (30) located between the cabin lining element (12) and the aircraft outer skin (32).

Anmelder

Firma

Airbus Operations GmbH

Land

🇩🇪 Deutschland

Fachgebiete