Patents by Inventor Gilbert F. A. Beziac

Gilbert F. A. Beziac has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Method of manufacturing a helicopter rotor blade
    Patent number: 4298417
    Abstract: A rotor blade, specially for a helicopter rotor, which blade is made of reinforced plastics and a process for making this blade in a single molding operation.This blade comprises: a solid one-piece leading edge spar embodied by strands of glass fibre filaments extending lengthwise over the whole length of the blade; a core made of a lightweight cellular substance and placed contiguous with the spar rear face; a thick sheet-like member extending around the spar and the core and comprising at least one layer of a fabric consisting of parallel glass fibres disposed askew of the blade longitudinal axis so as to form a torque-tube; a rear filling element, and a covering extending around the torque-tube and the rear filling element. The airfoil portion of this blade is centered substantially in the front quarter of the chord of the blade cross-section and it has a very high torsional stiffness.
    Type: Grant
    Filed: February 8, 1980
    Date of Patent: November 3, 1981
    Assignee: Societe Nationale Industrielle Aerospatiale
    Inventors: August H. L. Euler, Gilbert F. A. Beziac
  • Helicopter rotor blade
    Patent number: 4213739
    Abstract: A rotor blade, specially for a helicopter rotor, which blade is made of reinforced plastics.This blade comprises: a solid one-piece leading edge spar embodied by strands of glass fibre filaments extending lengthwise over the whole length of the blade; a core made of a lightweight cellular substance and placed contiguous with the spar rear face; a thick sheet-like member extending around the spar and the core and comprising at least one layer of a fabric consisting of parallel glass fibres disposed askew of the blade longitudinal axis so as to form a torque-tube; a rear filling element, and a covering extending around the torque-tube and the rear filling element. The airfoil portion of this blade is centered substantially in the front quarter of the chord of the blade cross-section and it has a very high torsional stiffness.
    Type: Grant
    Filed: February 22, 1978
    Date of Patent: July 22, 1980
    Assignee: Societe Nationale Industrielle Aerospatiale
    Inventors: August H. L. Euler, Gilbert F. A. Beziac