Method for coating faying surfaces of aluminum-alloy components and faying surfaces coated thereby
AssigneeMcDonnell Douglas Corporation
InventorsSteven G. Keener, Norman R. Byrd
Life of this patent
Estimating the term…
Abstract
An aluminum-alloy, aircraft structural component having a faying surface prepared by treating with one or more curable organic coatings, one or more of which is optionally in an encapsulated state, and delivering a uniform coating on demand by rupturing and curing the encapsulated coating.
Claims10
A treated, aluminum-alloy aircraft component prepared according to a method comprising the steps of:
- providing an aluminum-alloy component having a faying surface, said component selected from the group consisting of wing and fuselage skin panels, stiffeners, frames, and hinges, said precursor curable to a final state;
- providing a first coating material;
- applying the first coating material to the component;
- providing encapsulated second coating material to the first coating, said second coating material selected from the group consisting of phenolics, epoxies, melamines, polyurethanes, and polyureas;
- depositing the second coating material to the component at a thickness of from about 0.0005 to about 0.0015 inch;
- and
- heat-treating the twice-coated component.
An aluminum-alloy, aircraft component prepared according to a method comprising the steps of:
- providing an aluminum-alloy aircraft component having a faying surface, said component selected from the group consisting of wing and fuselage skin panels, stiffeners, frames, and hinges, said component curable to a final state;
- providing a first coating;
- providing an encapsulated second coating made from a material selected from the group consisting of phenolics, epoxies, melamines, polyurethanes, and polyureas;
- applying the first and second coating to the component in sequential order;
- providing a releasable film;
- and
- applying the releasable film to the component to cover the second coating.
An aluminum alloy-aircraft component prepared according to a method comprising the steps of:
- providing an aluminum-alloy aircraft component having a faying surface, said surface selected from the group consisting of wing and fuselage skin panels, stiffeners, frames, and hinges, said precursor curable to a final state;
- providing a first coating made from a material selected from the group consisting of polyurethanes, polyvinyl chlorides, silicones, epoxides, novolaks, acrylates, polyimides, melamines and phenolics;
- applying the first coating to the component;
- heat-treating the component;
- providing an encapsulated second coating made from a material selected from the group consisting of phenolics, epoxies, melamines, polyurethanes, and polyureas;
- applying the second coating to the first coating;
- providing a releasable film;
- and
- applying the releasable film to the component to cover the second coating.
An aluminum-alloy component prepared according to a method comprising the steps of:
- providing an aluminum-alloy aircraft component having faying surfaces, said component selected from the group consisting of wing and fuselage skin panels, stiffeners, frames, and hinges;
- providing a first coating;
- applying the first coating to the component to make a once-coated component;
- providing a first heat-treatment to the component;
- providing an encapsulated second coating;
- applying a second coating to the first coating to make a twice-coated component, said second coating made from a material selected from the group consisting of a polyuethane or a polyurea;
- and
- providing a second heat treatment to the second coating.
An aircraft component comprising:
- an aluminum alloy component having a faying surface, said component selected from the group consisting of wing and fuselage skin panels, stiffeners, frames, and hinges, said precursor curable to a final state;
- a substantially uniformly deposited, encapsulated first corrosion-resistant, organic coating material deposited onto the component, said first coating having a thickness of from about 0.0050 inch to about 0.010 inch;
- and
- an encapsulated second coating made from a material selected from the group consisting of a polyurethane or a polyurea, said second coating substantially uniformly deposited to a thickness of from about 0.0005 inch to about 0.0015 inch onto the first coating.
An aircraft comprising aluminum alloy-containing components selected from the group consisting of wing and fuselage skin panels, stiffeners, frames, and hinges, said precursor curable to a final state, said components having faying surfaces, said components comprising:
- an encapsulated first coating made from a material selected from the group consisting of polyurethanes, polyvinyl chlorides, silicones, epoxides, novolaks, acrylates, polyimides, melamides and phenolics;
- and
- an encapsulated second coating deposited onto the first coating, said second coating made from a material selected from the group consisting of phenolics, epoxies, melamines, polyurethanes and polyureas;
- wherein said coatings and said components are substantially cured in one curing step.
Dependencies are inferred from the claim text.