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AssigneeLes Stratifies
InventorsLoïc Le Lay, Laurent Baclet, Julien Scagnetti
Estimating the term…
The aim of the invention is to propose an edging method that is quick, effective, easy to implement and makes it possible to obtain a lightweight panel. To this end, the aim of the invention is a method for sealingly edging a composite panel comprising; *a step (a) of providing a composite panel of redefined thickness having two planar faces and a side to be edged, and of providing a sealing strip made from a polymer material having a width greater than the thickness of the composite panel, and comprising a first face, referred to as the “inner” face, and a second face, referred to as the “outer” face, in reference to the position of use of same: *a step (b) of applying the strip and an adhesive to the side and to a peripheral portion of the planar faces of the composite panel in such a way that the adhesive is located between the composite panel and the inner face of the strip, which sealingly protects the composite panel against dust, foreign bodies and the absorption of moisture.
Method of sealingly edging a composite panel comprising the steps of:
Dependencies are inferred from the claim text.
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From the US filing history. Foreign family members aren’t listed.
Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing…
Between relatively-stationary surfaces: without packing between the surfaces, e.g. with ground surfaces, with cutting edge
Working veneer or plywood: other working of veneer or plywood specially adapted
Other working of veneer or plywood specially adapted to veneer or plywood: securing a veneer strip to a panel edge
About 7 years 8 months of term left · ends 12 Jun 2034 (estimated)
The invention relates to a sealing edging method for composite panels that can be used as flooring or lining elements of inner aircraft walls. The invention also relates to a sealing strip for the implementation of the method and a panel obtained by this method.
In many sectors, especially aerospace, reduced weight is of major concern for improving the energy efficiency of aircraft.
Reduced weight is usually at odds with the other major concern in these sectors: mechanical strength.
Other features of the invention emerge from the detailed description given hereinafter with reference to the appended drawings which represent, respectively:
FIG. 1 shows a schematic sectional view of a composite panel used in the edging method according to the invention;
FIG. 2 shows a schematic sectional view of a polymer material strip for the implementation of the method according to the invention;
The invention is based on the idea of replacing the edging resin by a strip stuck on the side, but also on a peripheral portion of the panel. This strip may be pre-stuck during manufacture, or it may be deposited on a layer of adhesive deposited on the side and on a peripheral portion of the panel during the edging.
The method of edging a composite panel according to the invention comprises a step (a) providing a composite panel having a specified thickness e, having two planar surfaces and a side to be edged, and providing a polymer material strip with a width LR greater than the thickness e of the composite panel.
As shown in FIG. 2, the strip 20 has a first surface 21, called “inner” and a second face 22, called “outer” in reference to the position of use.