Deformable aircraft window

• US 10,202,183 B2
• Filed: 08/05/2014
• Issued: 02/12/2019
• Est. Priority Date: 08/06/2013
• Status: Active Grant

• Current Assignee: PPG Industries Ohio Incorporated (Nouryon BV)
• Original Assignee: PPG Industries Ohio Incorporated (Nouryon BV)
• Inventors: McCarthy, Dennis P., Blevins, Calvin B., Harris, Caroline S., Goodwin, George B., Gu, YaBei
• Primary Examiner(s): Ihezie, Joshua K
• Application Number:
  US14/451,857
• Publication Number:
  US 20150047275A1
• Time in Patent Office: 1,652 Days
• Field of Search: 2441293, 2441294, 244119
• CPC Class Codes: B29C 33/0011 thin-walled moulds
• CPC Class Codes: B29C 33/0038 with sealing means or the like seals on envelopes used in tyre retreading B29D30/542; for injection moulding footwear B29D35/0045
• CPC Class Codes: B32B 17/10036 comprising two outer glass sheets
• CPC Class Codes: B32B 17/10055 with at least one intermediate air space
• CPC Class Codes: B32B 17/10174 Coatings of a metallic or dielectric material on a constituent layer of glass or polymer
• CPC Class Codes: B32B 17/10761 containing vinyl acetal
• CPC Class Codes: B64C 1/14 Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipersfairings movable in conjunction with undercarriage elements B64C25/16; bomb doors B64D1/06
• CPC Class Codes: B64C 1/1492 Structure and mounting of the transparent elements in the window or windscreen

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.

Claims

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, and

wherein the first panel is an outer panel with an outer surface defining an outer fuselage contour when in the second state.

2. The window assembly of claim 1, wherein the second panel is a cast-to-shape polyurethane panel.

3. The window assembly of claim 1, wherein the first panel is configured to engage a frame such that the outer surface of the first panel is offset from an outer contour of an aircraft fuselage.

4. The window assembly of claim 1, wherein the first cross-sectional shape of the first panel is planar.

5. The window assembly of claim 1, wherein the first cross-sectional shape of the first panel is planar and the second panel has a planar cross-sectional shape.

6. The window assembly of claim 1, wherein the second panel includes at least one pressure equalization hole.

7. The window assembly of claim 1, wherein the first cross-sectional shape of one or more of the first panel and the second panel is planar.

8. The window assembly of claim 1, wherein a first cross-sectional shape of the second panel is inwardly convex.

9. The window assembly of claim 1, wherein the first panel comprises a cast-to-shape rabbeted edge engaging a groove in a seal.

10. The window assembly of claim 1, wherein the functional coating comprises a solar control coating comprising at least one infrared reflective metal layer.

11. The window assembly of claim 10, further comprising a protective coating over the solar control coating, wherein the protective coating is selected from the group consisting of a metal oxide coating and a polymeric coating.

12. The window assembly of claim 1, wherein the functional coating comprises at least one metal oxide layer.

13. The window assembly of claim 1, wherein the first panel comprises a cast-to-shape rabbeted edge and the functional coating further comprises at least one infrared reflective metal layer, the assembly further comprising:

a seal having a groove, wherein the rabbeted edge of the first panel engages the groove; and

a protective coating over the functional coating, wherein the protective coating is selected from the group consisting of a metal oxide coating and a polymeric coating.

14. 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 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.