An aircraft panel assembly has a panel 22, stiffeners 8, and a rib foot beam 18. Each stiffener has a part (fig.6,25) attached to the panel, and a structural part 26, spaced apart from the panel. The rib foot beam crosses the stiffeners at a series of intersections 23, where the beam passes between the panel and the structural part of the stiffener. Preferably, each stiffener has a pair of feet, with webs (fig.6,28) connecting the feet to a crown; the feet bonded to an inner panel surface, and the beam bonded to the panel and to the stiffeners at the intersections. A layer (fig.9,29) may form the crown of the stiffeners and cover the beam between the stiffeners. An aircraft wing assembly may use the panel as wing covers; with a rib connecting upper and lower covers, and attached to the beam between the intersections. A method of manufacturing an aircraft panel assembly is also claimed, having the steps of providing fibre preforms on a forming tool, which may involve spraying cut fibres onto the forming tool; laying the beam in position; co-infusing the preforms with a matrix material; and curing the matrix material.
Aircraft panel assembly
18.11.2020
Patent
Elektronische Ressource
Englisch
Europäisches Patentamt | 2025
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