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Supplemental leading edge wear strip for a rotor blade

  • US 5,908,522 A
  • Filed: 11/07/1997
  • Issued: 06/01/1999
  • Est. Priority Date: 11/07/1997
  • Status: Expired due to Term
First Claim
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1. A method for repairing an outboard leading edge of a composite, helicopter rotor blade, comprising the steps of:

  • providing a supplemental leading edge abrasion wear strip formed of nickel;

    preparing the outboard portion of the leading edge of the composite, helicopter rotor blade for bonding;

    preparing an interior bonding surface of a supplemental leading edge abrasion wear strip for bonding;

    hot bonding a structural adhesive film to the interior bonding surface of the supplemental leading edge abrasion wear strip utilizing a high temperature cure;

    thenbonding the structural adhesive film to the outboard portion of the surface of the leading edge of the composite, helicopter rotor blade using a structural adhesive mix and a low temperature cure with positive pressure applied to the supplemental leading edge abrasion wear strip and the composite, helicopter rotor blade to bond the supplemental leading edge wear abrasion strip to the composite, helicopter rotor blade; and

    fairing the run out of the structural adhesive mix to contour a transition section gap extending between a trailing edge of the supplemental leading edge abrasion wear strip and a surface of the composite, helicopter rotor blade which is proximately adjacent to the trailing edge of the leading edge abrasion wear strip.

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