METHOD FOR REPAIRING DELAMINATION AND MOISTURE BY HEAT, PRESSURE AND ADHESIVE

Abstract

A method for repairing window laminates in which two plies have become separated to create a void, and wherein moisture may have entered through an edge of the window laminate and into the void. The method includes the steps of: placing the window laminate in a vacuum bag and inserting the vacuum bag containing the window laminate into an oven or autoclave for a minimum of ten minutes at a minimum temperature of 120 degrees Fahrenheit to remove the moisture between the plies; removing the vacuum bag and window laminate from the oven, and removing the window from the vacuum bag; forcing a needle on a syringe through the edge of the window laminate in the area of the void; and injecting an adhesive in the syringe into the void to fill the void with the adhesive.

Claims

1. A method for repairing a window laminate which has been delaminated and wherein moisture has entered into a void created by delamination, comprising the steps of: placing the window laminate into a vacuum bag, sealing the vacuum bag closed and placing the vacuum bag containing the window laminate into an oven or an autoclave for a minimum of ten minutes at a minimum temperature of 120 degrees Fahrenheit to remove moisture between plies of the window laminate; removing the vacuum bag and the window laminate from the oven or the autoclave; and removing the window laminate from the vacuum bag; inspecting the window laminate for damage or defects; removing at least one of an outer nonstructural glass ply or an inner nonstructural glass ply upon determining damage or a defect in an adhesive ply of the window laminate; removing the damaged or defective adhesive ply; replacing a new adhesive ply; and reattaching the removed at least one of the outer nonstructural glass ply or the inner nonstructural glass ply to the window laminate to complete a repair of the window laminate.

2. A method for repairing a window laminate which has been delaminated and wherein moisture has entered into a void created by delamination, comprising the steps of: placing the window laminate into a vacuum bag, sealing the vacuum bag closed and placing the vacuum bag containing the window laminate into an oven or an autoclave for a minimum of ten minutes at a minimum temperature of 120 degrees Fahrenheit to remove moisture between plies of the window laminate; removing the vacuum bag and the window laminate from the oven or the autoclave; and removing the window laminate from the vacuum bag; forcing a needle on a syringe through an edge of the window laminate in an area of delamination so that the needle enters into the void created by delamination; injecting an adhesive in the syringe into the void to fill the void with the adhesive; inspecting the window laminate for damage or defects; removing at least one of an outer nonstructural glass ply or an inner nonstructural glass ply upon determining damage or a defect in an adhesive ply of the window laminate; removing the damaged or defective adhesive ply; replacing a new adhesive ply; and reattaching the removed at least one of the outer nonstructural glass ply or the inner nonstructural glass ply to the window laminate to complete a repair of the window laminate.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0013] For a fuller understanding of the nature of the present invention, reference should be made to the following detailed description taken in conjunction with the accompanying drawings in which:

[0014] FIG. 1 is a perspective view of an aircraft window illustrating the manner in which the syringe and hypodermic needle is inserted through the seal member into the void of the plies of the laminate which have become separated;

[0015] FIG. 2 is an isolated cross-sectional view taken along the plane indicated by the arrows 2-2 in FIG. 1 and illustrating the multiple plies of the laminate structure of the aircraft window including a nonstructural outer glass ply, a center structural glass member and a nonstructural inner glass ply, and wherein a polyvinyl butyral (PVB) layer between the outer ply and the central structural glass member and between the inner glass ply and the central structural glass member is shown to be defective;

[0016] FIG. 3 is an isolated cross-sectional view similar to FIG. 2 and showing the outer glass ply and inner glass ply removed to allow repair of the damaged PVB plies; and

[0017] FIG. 4 is a cross-sectional view similar to FIG. 2 and wherein the PVB layers have been repaired and the outer and inner glass plies replaced.

[0018] Like reference numerals refer to like parts throughout the several views of the drawings.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT

[0019] Referring to FIG. 1, a typical aircraft window 10 comprises a transparent laminate structure 12 having several glass and/or acrylic plies adhered together by means of interposed adhesive plies. A frame structure 16 is secured about a perimeter of the window 12 to secure the laminate plies. In particular, the frame structure holds a peripheral edge 14 of the two or more plies of the window laminate structure 12 tightly together.

[0020] As noted above, one particular problem encountered with window laminates, such as the type shown in FIG. 1, is the tendency of the two or more plies to delaminate. Upon delamination, voids are created between the two or more plies. Sometimes, moisture can enter through the edge 14 of the window laminate structure 12 to fill the voids created by delamination.

[0021] The present invention provides a method for removing moisture within the voids of delaminated window laminate structures and further a method for repairing the delaminated areas. The method for removing moisture includes the steps of: placing the window laminate structure in a vacuum bag and sealing the vacuum bag closed; inserting the vacuum bag containing the window laminate into an oven or autoclave for a minimum of ten minutes at a minimum temperature of 120 degrees Fahrenheit to remove the moisture between the two or more plies of the delaminated aircraft window laminate structure; removing the vacuum bag and the window laminate structure from the oven or autoclave; and removing the window from the vacuum bag. The method further includes the steps of repairing the delaminated areas by forcing a needle on a syringe through the edge 14 of the window laminate structure 12 in the area of delamination and injecting an adhesive in the syringe into the void to fill the void with the adhesive; and removing the needle from the void and from the edge of the window laminate structure.

[0022] Referring to FIGS. 2-4, an isolated cross-section of the transparent laminate structure of the aircraft window 10 of FIG. 1 is shown. The laminate structure of the aircraft window 10 includes the several glass and/or acrylic plies including a central structural glass ply 20, a nonstructural deicing outer glass ply 22 and a nonstructural defogging inner glass ply 24. The glass plies 20, 22 and 24 are bonded together by adhesive layers 26. The adhesive layers are typically formed of a polyvinyl butyral (PVB) material.

[0023] In FIG. 2, the PVB layer is shown to be damaged. According to the method of the present invention, following the step of injecting the adhesive by syringe into the void in the areas of delamination, if, after inspection, the delamination is not fully repaired by heating in the oven/autoclave and the injection of adhesive, and/or the PVB plies are simply damaged, then it is necessary to remove the outer glass ply 22 and/or the inner glass ply 24 in order to repair the damaged adhesive ply 26. Once the outer and/or inner glass plies are removed, the damaged PVB adhesive layer is removed and replaced. Typically, the PVB layer is removed by application of heat that is sufficient to cause the PVB layer to soften and separate from the glass plies.

[0024] FIG. 3 shows the outer and inner glass plies 22, 24 removed to allow removal and replacement of the adhesive PVB plies 26. Once removed, new PVB adhesive ply is installed and the outer and inner glass plies 22 and 24 are replaced, as shown in FIG. 4, thereby fully repairing the previously delaminated laminate structure of the aircraft window 10.

[0025] While the present invention has been shown and described in accordance with a preferred and practical embodiment, it is recognized that departures from the instant disclosure are fully contemplated within the spirit and scope of the present invention which is not to be limited except as defined in the following claims as interpreted under the Doctrine of Equivalents.