Method of forming a perforated composite panel

Patent metadata

Field	Value
Publication number	US-9610760-B2
Application number	US-201414445366-A
Country	US
Kind code	B2
Filing date	Jul 29, 2014
Priority date	Aug 7, 2013
Publication date	Apr 4, 2017
Grant date	Apr 4, 2017

Abstract

A perforated composite panel comprises a substrate and an applied layer, the substrate having a first surface and an opposite second surface. A method of forming the perforated composite panel comprises the steps of:
i. cutting a plurality of first holes in the substrate; ii. positioning the applied layer against the substrate such that a surface of the applied layer overlays the first surface of the substrate to thereby form the composite panel; iii. locating the composite panel in a fixture, the fixture having one or more datum features; iv. determining the location and axis direction for each of the first holes in the substrate, relative to the or each datum feature; and v. cutting a plurality of second holes in the applied layer, each of the plurality of second holes being coincident and coaxial with a corresponding one of the plurality of first holes.

First claim

The invention claimed is:

1. A method of producing a perforated composite panel, the composite panel comprising a substrate and an applied layer, the substrate having a first surface and an opposite second surface, the method comprising the steps of:
i. cutting a plurality of first holes in the substrate;
ii. positioning the applied layer against the substrate such that a surface of the applied layer overlays the first surface of the substrate to thereby form the composite panel;
iii. locating one or more datum features on the composite panel;
iv. determining the location and axis direction for each of the first holes in the substrate, relative to the or each datum feature; and
v. cutting a plurality of second holes in the applied layer, each of the plurality of second holes being coincident and coaxial with a corresponding one of the plurality of first holes.

2. The method as claimed in claim 1 , wherein step ii. comprises the additional subsequent step of:
ii.′ adhesively bonding the surface of the applied layer to the first surface of the substrate.

3. The method as claimed in claim 1 , wherein step i. comprises the additional initial step of:
i.′ forming the substrate into a predetermined shape.

4. The method as claimed in claim 1 , wherein step i. comprises the additional subsequent step of:
i.′ forming the substrate into a predetermined shape.

5. The method as claimed in claim 1 , wherein the substrate is formed from a first material and the applied layer is formed from a second material, a hardness of the first material being greater than a corresponding hardness of the second material.

6. The method as claimed in claim 1 , wherein the axis of each of the first holes is inclined at an acute angle to the normal to the plane of the substrate.

7. The method as claimed in claim 1 , wherein the diameter of each of the plurality of second holes is smaller than the diameter of the corresponding one of the plurality of first holes.

8. The method as claimed in claim 1 , wherein each of the plurality of second holes is cut from the second surface of the substrate.

9. The method as claimed in claim 1 , wherein two or more of the first holes are cut simultaneously.

10. The method as claimed in claim 1 , wherein two or more of the second holes are cut simultaneously.

Assignees

• Rolls Royce Plc

Inventors

• Hayton Paul Robert

Classifications

• B23B2228/36

  Multi-layered · CPC title

• B32B2038/047

  Perforating · CPC title

• B32B38/0004 Primary

  Cutting, tearing or severing, e.g. bursting; Cutter details (cutting in general B26D; laminating combined with punching or perforating B32B38/04; removing all or part of the layers B32B38/10; cutting in combination with laying up and registration B32B38/185 takes precedence) · CPC title

• Y10T156/1057

  Subsequent to assembly of laminae · CPC title

• B32B2262/106

  Carbon fibres, e.g. graphite fibres · CPC title