Deformable aircraft window
First Claim
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1. A deformable aircraft window assembly, comprising:
- a cast-to-shape polyurethane first panel having an outwardly-facing first surface and a second surface, wherein in a first state in which there is no pressure difference between the first surface and the second surface the first panel has a first cross-sectional shape, and wherein in a second state in which a cabin of an aircraft is pressurized and the aircraft is at a cruising altitude so that there is a pressure difference between the first surface and the second surface, the first panel has an outwardly convex shape;
a second panel spaced from the first panel; and
a functional coating positioned on one or more of the first and the second surface of the first panel,wherein the functional coating comprises a gradient coating having a thickness that varies across a width of the gradient coating, such that the gradient coating is thicker at a periphery of the first panel and thinner toward a center of the first panel, the gradient coating being configured to counteract a lensing effect caused by deformation of the first panel when the first panel is in one or more of the first state and the second state,wherein the first cross-sectional shape of the first panel is selected from the group consisting of planar and outwardly convex, andwherein the first panel is an outer panel with an outer surface defining an outer fuselage contour when in the second state.
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Abstract
An aircraft window assembly (10) includes a first panel (12) having a first surface (14) and a second surface (16). In a first state in which there is no pressure difference between the first surface (14) and the second surface (16), the first panel (12) has a cross-sectional shape selected from planar, outwardly convex, or inwardly convex. In a second state in which there is a pressure difference between first surface (14) and the second surface (16), the first panel (12) has an outwardly convex cross-sectional shape.
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Citations
14 Claims
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1. A deformable aircraft window assembly, comprising:
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a cast-to-shape polyurethane first panel having an outwardly-facing first surface and a second surface, wherein in a first state in which there is no pressure difference between the first surface and the second surface the first panel has a first cross-sectional shape, and wherein in a second state in which a cabin of an aircraft is pressurized and the aircraft is at a cruising altitude so that there is a pressure difference between the first surface and the second surface, the first panel has an outwardly convex shape; a second panel spaced from the first panel; and a functional coating positioned on one or more of the first and the second surface of the first panel, wherein the functional coating comprises a gradient coating having a thickness that varies across a width of the gradient coating, such that the gradient coating is thicker at a periphery of the first panel and thinner toward a center of the first panel, the gradient coating being configured to counteract a lensing effect caused by deformation of the first panel when the first panel is in one or more of the first state and the second state, wherein the first cross-sectional shape of the first panel is selected from the group consisting of planar and outwardly convex, and wherein the first panel is an outer panel with an outer surface defining an outer fuselage contour when in the second state. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13)
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14. A deformable aircraft window assembly, comprising:
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a cast-to-shape polyurethane first panel having an outwardly-facing first surface and a second surface, wherein in a first state in which there is no pressure difference between the first surface and the second surface the first panel has a planar cross-sectional shape, and wherein in a second state in which a cabin of an aircraft is pressurized and the aircraft is at a cruising altitude so that there is a pressure difference between the first surface and the second surface, the first panel has an outwardly convex shape; a second panel spaced from the first panel; and a functional coating positioned on one or more of the first and the second surface of the first panel, wherein the functional coating comprises a gradient coating having a thickness that varies across a width of the gradient coating, such that the gradient coating is thicker at a periphery of the first panel and thinner toward a center of the first panel, the gradient coating being configured to counteract a lensing effect caused by deformation of the first panel when the first panel is in one or more of the first state and the second state, and wherein the first panel is an outer panel with an outer surface defining an outer fuselage contour when in the second state.
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Specification