Internal fixed structure for an aircraft nacelle
AssigneeAirbus Operations GmbH
InventorsLaurent Cazeaux, Laurent Caliman, Nicolas Charton
Life of this patent
Estimating the term…
Abstract
An internal fixed structure for a nacelle, comprising end panels, an intermediate panel in the form of a half-cylinder between the end panels, splice plates between the intermediate panel and each end panel, wherein each splice plate is made up of a skin with an inner face fastened to the panels and at least one indentation protruding with respect to an outer face, and a pad fastened to each fastening surface of an indentation, wherein each pad of the upper splice plate bears against a surface of an engine pylon, and wherein each pad of the lower splice plate bears against a pad of a lower splice plate of another internal fixed structure.
Claims10
An internal fixed structure for a nacelle of an aircraft comprising an engine pylon, said internal fixed structure comprising:
- an upper end panel,
- a lower end panel,
- an intermediate panel in a form of a half-cylinder and disposed between the upper end panel and the lower end panel,
- an upper splice plate between the upper end panel and the intermediate panel,
- a lower splice plate between the intermediate panel and the lower end panel, wherein each splice plate is made up of a skin with an inner face and an outer face, wherein the inner face is fastened to the intermediate panel and to the respective end panel, and wherein each skin comprises at least one indentation protruding with respect to the outer face, wherein each indentation has a fastening surface, and
- for each fastening surface, a pad fastened to said fastening surface, wherein each pad of the upper splice plate is configured to bear against a surface of the engine pylon, and wherein each pad of the lower splice plate is configured to bear against a pad of a lower splice plate of another internal fixed structure.
Dependencies are inferred from the claim text.