Removable closure member for a female portion received in an external opening of an aircraft engine nacelle
A removable closure member is configured to close a female portion received in an external opening formed in the external surface of a nacelle for an aircraft engine. The female portion includes at least one air inlet opening. The closure member includes a base that forms the external contour of the member and that extends beyond the external opening of the nacelle so as to move into abutment against the external surface of the nacelle. The closure member further includes at least one resiliently deformable position retention member that projects from the base and is configured to be inserted into the air inlet opening.
1 . A removable closure member configured to close a female portion received in an external opening made in an external surface of a nacelle for an aircraft engine, said female portion comprising at least one opening that opens into the nacelle, said closure member comprising:
a base forming an external contour of said member and configured to extend beyond the external opening of the nacelle so as to move into abutment against the external surface of said nacelle; and
at least one resiliently deformable position retention member that projects from the base and is configured to be inserted into the opening of the female portion,
wherein said position retention member comprises a stud comprising a lip that projects from the free end of the stud and extends toward a rigid portion of the female portion, said lip being deformable by contact with said rigid portion and configured to snap behind said rigid portion in the corresponding opening of the female portion so as to retain the closure member in position,
wherein said stud is configured to cooperate with a ventilation grid or a scoop that is mounted in the female portion and that defines said opening.
2 . The closure member according to claim 1 , further comprising a gripping means extending from the base that projects towards the exterior, on the side opposite to the position retention member.
3 . The closure member according to claim 1 , further comprising a core made of foam surrounded by a layer of elastomer.
4 . The closure member according to claim 1 , further comprising two inclined portions each configured to cooperate with a fin of the female portion, the retention member of said closure member being configured to cooperate with at least one of the openings of said female portion.
5 . The closure member according to claim 4 , wherein the base of said closure member comprises a first portion extending according to a direction normal to the inclined portions and connected to said inclined portions.
6 . The closure member according to claim 5 , wherein the first portion forms an axis of symmetry of the closure member.
7 . The closure member according to claim 5 , further comprising two lateral portions extending on either side of the first portion and configured to cooperate with portions of fins of the female portion, each of the lateral portions comprising a plurality of the inclined portions.
8 . The closure member according to claim 7 , wherein each of the lateral portions comprises two inclined portions of ends and at least one central inclined portion, the retention member comprising two end studs configured to each cooperate with an end opening of the female portion and at least one central stud configured to cooperate with a central opening of said female portion.
9 . The closure member according to claim 8 , wherein at least the studs of ends each comprise a lip that projects from a free end of said stud and is configured to extend towards an end inclined fin of the female portion.
10 . The closure member according to claim 1 , wherein the position retention member comprises a stud that projects from the base and is configured to extend towards the female portion and includes a lip that projects from a free end of said stud and is configured to be inserted into the opening of said female portion.
11 . A nacelle for an aircraft engine, the nacelle comprising:
an external surface including at least one external opening configured to receive a female portion; and
at least one closure member according to claim 4 , the at least one closure member being configured to temporarily close said female portion.
12 . The nacelle according to claim 11 , wherein the female portion is an air ventilation member comprising a fastening portion configured to be fastened onto the nacelle, at least two ventilation fins connected to the fastening portion and evacuation openings made between two adjacent fins, the air evacuation member being configured to be closed by the at least one first closure member.
13 . The nacelle according to claim 11 , wherein the female portion is an air inlet member comprising a fastening portion configured to be fastened onto the nacelle, a bottom connected on one side to the fastening portion and a rigid wall connected to a second side of the fastening portion and defining with said bottom an air inlet opening, the air inlet member being configured to be closed by the closure member, wherein the position retention member comprises a stud that projects from the base and is configured to extend towards the female portion and includes a lip that projects from a free end of said stud and is configured to be inserted into the opening of said female portion.
14 . The nacelle according to claim 13 , further comprising:
a second closure member;
at least one second opening; and
a second air inlet member received in said second opening and configured to be temporarily closed by the second closure member.
15 . A nacelle for an aircraft engine, the nacelle comprising:
an external surface including:
a first external opening configured to receive a female portion, and
a second external opening configured to form an air inlet for a fan of the engine; and
at least one closure member according to claim 1 , the at least one closure member being configured to temporarily close said female portion received in the first external opening.