IP Library › Granted Patent US 8,016,235
Granted Patent B2
US 8,016,235 · App. 11/897,007 · Granted Sep 13, 2011

Cover for an aircraft access opening

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Quick Facts
Patent No.
US 8,016,235
App. No.
11/897,007
Granted
Sep 13, 2011
Kind
B2
Abstract

The invention relates to a cover for the access opening in a composite material aircraft structure, characterized in that it comprises the following elements: an outer cover ( 18 ) arranged on the outer part of the aircraft skin ( 28 ), the carbon fiber layers ( 14 ) forming the skin ( 28 ) being deformed towards the inner part of the aircraft structure, leaving enough space between the aircraft structure and the outer part of the skin ( 28 ) for the seating of the outer cover ( 18 ). a composite material plate ( 15 ) arranged in the outer part of the skin ( 28 ) and surrounding the area for installing the outer cover ( 18 ); an inner cover ( 27 ) arranged on the inner part of the aircraft skin ( 28 ).

Claims (9)

1. A cover for an access opening in a composite material aircraft structure, comprising:

an outer cover ( 18 ) arranged on an outer part of an aircraft skin ( 28 ), carbon fiber layers ( 14 ) forming the skin ( 28 ) being deformed towards an inner part of the aircraft structure, leaving enough space between the aircraft structure and the outer part of the skin ( 28 ) for seating the outer cover ( 18 );

a composite material plate ( 15 ) arranged in the outer part of the skin ( 28 ) and surrounding an area for installing the outer cover ( 18 ); and

an inner cover ( 27 ) arranged on the inner part of the aircraft skin ( 28 ).

2. The cover for the access opening in a composite material aircraft structure according to claim 1 , wherein the composite material plate ( 15 ) is cured together with a base of the skin ( 28 ).

3. The cover for the access opening in a composite material aircraft structure according to claim 1 , further comprising an adjusting washer ( 31 ) between the inner cover ( 27 ) and the outer part of the skin ( 28 ) to allow a correct seating of the inner cover ( 27 ).

4. The cover for the access opening in a composite material aircraft structure according to claim 3 , further comprising a sealing profile ( 30 ) between the adjusting washer ( 31 ) and the inner cover ( 27 ) to ensure a correct sealing of the inner cover ( 27 ) and prevent leakages.

5. The cover for the access opening in a composite material aircraft structure according to claim 1 , further comprising a sealing profile ( 17 ) in the outer cover ( 18 ) which seals the outer cover ( 18 ) against the outer part of the skin ( 28 ).

6. The cover for the access opening in a composite material aircraft structure according to claim 1 , wherein said cover is installed by screwing the outer cover ( 18 ) and the inner cover ( 27 ) to one another, the skin ( 28 ) being located between the inner cover ( 27 ) and the outer cover ( 28 ).