Structural panel with carbon composite plies
AssigneesAirbus Helicopters Deutschland GmbH, Airbus SAS
InventorsAxel FINK, Manuel KEMPF, Uwe BEIER
Life of this patent
Estimating the term…
Abstract
A structural panel for use in aeronautical applications. The structural panel includes a composite skin that comprises composite material and a stiffening framework that is rigidly attached to the composite skin. The composite skin is configured as a load bearing monolithic structure with a structure thickness of less than 1 mm. The composite skin comprises a composite laminate with a plurality of carbon composite plies. Each one of the plurality of carbon composite plies comprises a ply thickness in a range from 0.02 mm to 0.05 mm.
Claims15
A structural panel for use in aeronautical applications, including a composite skin that comprises composite material and a stiffening framework that is rigidly attached to the composite skin, wherein the composite skin is configured as a load bearing monolithic structure with a structure thickness of less than 1 mm, and wherein the composite skin comprises a composite laminate with a plurality of carbon composite plies, each one of the plurality of carbon composite plies comprising a ply thickness in a range from 0.02 mm to 0.05 mm.
Dependencies are inferred from the claim text.