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Fuselage structure using advanced technology fiber reinforced composites

  • US 4,310,132 A
  • Filed: 02/16/1978
  • Issued: 01/12/1982
  • Est. Priority Date: 02/16/1978
  • Status: Expired due to Term
First Claim
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1. A fuselage structure comprising:

  • a fuselage having a longitudinal axis;

    an external skin of alternate layers of composite material, oriented at a biased angle relative to the longitudinal axis and at approximately 90°

    to the biased angle;

    stringers, having outboard and inboard ends;

    frames;

    circumferential pads of composite material located on an inner surface of the external skin between said external skin and said frames and oriented at approximately 90°

    relative to the longitudinal axis;

    first reinforcement means, associated with the outboard ends of the stringers, said first reinforcement means being composite material oriented as approximately 0°

    relative to the longitudinal axis;

    second reinforcement means, associated with the inboard ends of the stringers, said second reinforcement means being composite material oriented at approximately 0°

    relative to the longitudinal axis; and

    third reinforcement means associated with the frames and the external skin whereby the frames are fastened to the external skin through the reinforcement means and through shear ties.

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