Patents by Inventor Noboru Kobiki

Noboru Kobiki 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).

  • Patent number: 7757991
    Abstract: In a blade vortex interaction (BVI) noise reduction system for a helicopter a rotor blade, a tab is movable via an actuator from a first position, wherein the tab is within the blade, to a second position, wherein the tab extends outwardly from a trailing edge of the rotor blade. The actuator is operated so that the tab advances and retreats in response to rotating timing of the rotor blade, to reduce the BVI noise of the rotor blade.
    Type: Grant
    Filed: February 28, 2006
    Date of Patent: July 20, 2010
    Assignees: Kawada Industries, Inc., Japan Aerospace Exploration Agency
    Inventors: Yasutada Tanabe, Takeshi Akasaka, Shigeru Saito, Noboru Kobiki
  • Publication number: 20100044505
    Abstract: The present method is characterized by providing the rotor blade with a tab 3, which can advance and retreat with respect to rear of rotating direction of the rotor blade between a position where the tab protrudes from a trailing edge of the rotor blade and a position where the tab does not, and providing an actuator 4, which advances and retreats the tab 3, and operating the actuator 4 so that the tab advances and retreats in response to rotating timing of the rotor blade 2, when reducing the BVI noise of the rotor blade of a helicopter. Thus, the BVI noise of a helicopter can be reduced effectively.
    Type: Application
    Filed: February 28, 2006
    Publication date: February 25, 2010
    Inventors: Yasutada Tanabe, Takeshi Akasaka, Shigeru Saito, Noboru Kobiki
  • Publication number: 20080237395
    Abstract: The present method is characterized by providing the rotor blade with a tab 3, which can advance and retreat with respect to rear of rotating direction of the rotor blade between a position where the tab protrudes from a trailing edge of the rotor blade and a position where the tab does not, and providing an actuator 4, which advances and retreats the tab 3, and operating the actuator 4 so that the tab advances and retreats in response to rotating timing of the rotor blade 2, when reducing the BVI noise of the rotor blade of a helicopter. Thus, the BVI noise of a helicopter can be reduced effectively.
    Type: Application
    Filed: February 28, 2006
    Publication date: October 2, 2008
    Inventors: Yasutada Tanabe, Takeshi Akasaka, Shigeru Saito, Noboru Kobiki
  • Patent number: 5655878
    Abstract: A control system has an HHC actuator having a basal portion and a movable portion. A load acting on the control system is detected by a semiconductor gauge. The load detected by the semiconductor gauge is compared with a threshold value in a computer. If the detected load is larger than the threshold load, the movable portion is fixed to the basal portion by a fixing mechanism. By detecting the sign of stall of blades, the HHC actuator is fixed in a neutral position, allowing safe flight. A fixing switch is provided for allowing the fixing mechanism to operate regardless of the result of the comparison with the computer.
    Type: Grant
    Filed: February 21, 1996
    Date of Patent: August 12, 1997
    Assignee: Advanced Technology Institute of Commuter-Helicopter, Ltd.
    Inventors: Eiichi Yamakawa, Atsushi Murashige, Noboru Kobiki
  • Patent number: 5639215
    Abstract: A blade of the rotor is attached to a main rotor shaft, and is rotated counterclockwise at a high speed when viewed from above. In the vicinity of the blade tip, a flap having a wing shape in section is pivotally supported with a hinge so as to be angularly displaceable and at the end a part of the rear end of the blade is cut out. A hinge line which indicates the center of the angular displacement of the hinge is formed so as to be parallel to a straight line passing through the rotation center of the rotor and the center of gravity of the flap. A helicopter rotor equipped with flaps is provided in which the influence of the centrifugal force acting on the center of gravity of a blade can be largely reduced, and a flap control mechanism can be reduced in size and weight.
    Type: Grant
    Filed: February 26, 1996
    Date of Patent: June 17, 1997
    Assignee: Advanced Technology Institute of Commuter-Helicopter, Ltd.
    Inventors: Eiichi Yamakawa, Noboru Kobiki, Eiji Shima