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US 12,583,601 B2Granted
Assembly comprising a nacelle panel and a housing
AssigneeSafran Nacelles
InventorsJean-Baptiste Delarue, Laurent Georges Valleroy, Vianney Hus, Hugo Boistelle
Life of this patent
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Abstract
An assembly includes a nacelle panel of an aircraft engine, the nacelle panel including an outer skin, an inner skin and a central layer interposed between the outer and inner skins. The central layer has a housing, the outer skin has an opening which opens into the housing, and a linking member extends in the opening and in the housing, the linking member to be connected to an actuator.
Claims16
An assembly comprising:
- a nacelle panel of an aircraft engine, the nacelle panel comprising:
- an outer skin having a first outer face and a first inner face opposite to each other;
- an inner skin having a second outer face and a second inner face opposite to each other;
- and
- a central layer having a third outer face and a third inner face opposite to each other, the central layer being interposed between the outer skin and the inner skin such that the first inner face contacts the third outer face, the second outer face contacts the third inner face, and the second inner face faces an air flow path of the aircraft engine,
- wherein:
- the outer skin has an opening which extends between the first outer face and the first inner face,
- the central layer has a housing which extends between the third outer face and the third inner face,
- the opening opens into the housing, and
- the opening is closed by the second outer face;
- and
- a linking member that extends in the opening and in the housing, the linking member configured to be connected to an actuator.
9 more elements
A method for manufacturing an assembly for a nacelle of an aircraft engine, the method comprising:
- disposing a linking member into an opening of an outer skin of a nacelle panel and within a housing in a central layer of the nacelle panel, the nacelle panel comprising:
- the outer skin having a first outer face and a first inner face opposite to each other;
- an inner skin having a second outer face and a second inner face opposite to each other;
- and
- the central layer having a third outer face and a third inner face opposite to each other, the central layer being interposed between the outer skin and the inner skin such that the first inner face contacts the third outer face, the second outer face contacts the third inner face, and the second inner face faces an air flow path of the aircraft engine,
- wherein:
- the opening extends between the first outer face and the first inner face,
- the housing extends between the third outer face and the third inner face,
- the opening opens into the housing,
- the opening is closed by the second outer face, and
- the linking member is configured for connection of an actuator thereto.
8 more elements
An assembly comprising:
- a nacelle panel of an aircraft engine, the nacelle panel comprising:
- an outer skin having a first outer face and a first inner face opposite to each other;
- an inner skin having a second outer face and a second inner face opposite to each other;
- and
- a central layer having a third outer face and a third inner face opposite to each other, the central layer being interposed between the outer skin and the inner skin such that the first inner face contacts the third outer face, the second outer face contacts the third inner face, and the second inner face faces an air flow path of the aircraft engine,
- wherein:
- the outer skin has an opening which extends between the first outer face and the first inner face,
- the central layer has a housing which extends between the third outer face and the third inner face,
- the opening opens into the housing, and
- the opening is closed by the second outer face;
- and
- a linking member that extends in the opening and in the housing, the linking member configured to be connected to an actuator,
- wherein the nacelle panel further comprises a box delimiting the housing.
10 more elements
Dependencies are inferred from the claim text.