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Repairing method for composite material and composite material using the same

  • US 9,993,983 B2
  • Filed: 02/25/2011
  • Issued: 06/12/2018
  • Est. Priority Date: 02/26/2010
  • Status: Expired due to Fees
First Claim
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1. A repairing method for repairing a delamination formed between layers of a hardened composite material,wherein the composite material is used for an aircraft, and is a laminated structure including at least a first layer of the composite material and a second layer which is laminated on the first layer and is a part of the composite material, and is hardened,wherein an object to be repaired by the repairing method is an area define the delamination where the first layer is partially separated from the second layer so as to form a gap between the first layer and the second layer which are cured and bound,wherein the method comprises:

  • drilling a hole in both the first layer and the second layer within the area defining the delamination, in a plan view of the area, so as to penetrate through the first layer and the second layer,joining the partially separated portion by inserting a joining member into the hole and joining the first layer and the second layer by drawing the first layer and the second layer together to eliminate the gap formed by the delamination; and

    applying a bending process to an end portion of the joining member that is inserted through the hole such that the first layer and the second layer remain joined together,wherein a size of a cross section area of the hole is smaller than a size of a cross section area of the partially separated portion, in a plan view of the composite material.

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