Patents by Inventor Shinichiro Tokudome

Shinichiro Tokudome 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).

  • Rocket engine system for realizing high-speed response
    Patent number: 8943795
    Abstract: Disclosed is a turbo pump in which a pump impeller is connected to one end of a rotary shaft and a turbine is connected to the other end of the rotary shaft. The turbo pump is designed such that an equivalent region, between a turbine efficiency curve obtained on the basis of a conditional expression where the number of rotations of the rotary shaft is maintained constant regardless of a pump flow rate and a turbine efficiency curve of an actual machine, becomes an operation region.
    Type: Grant
    Filed: September 3, 2010
    Date of Patent: February 3, 2015
    Assignees: IHI Corporation, Japan Aerospace Exploration Agency
    Inventors: Hatsuo Mori, Yoshihiro Naruo, Shinichiro Tokudome, Tsuyoshi Yagishita, Takayuki Yamamoto, Yoshifumi Inatani
  • ROCKET ENGINE SYSTEM FOR REALIZING HIGH-SPEED RESPONSE
    Publication number: 20120167552
    Abstract: Disclosed is a turbo pump in which a pump impeller is connected to one end of a rotary shaft and a turbine is connected to the other end of the rotary shaft. The turbo pump is designed such that an equivalent region, between a turbine efficiency curve obtained on the basis of a conditional expression where the number of rotations of the rotary shaft is maintained constant regardless of a pump flow rate and a turbine efficiency curve of an actual machine, becomes an operation region.
    Type: Application
    Filed: September 3, 2010
    Publication date: July 5, 2012
    Inventors: Hatsuo Mori, Yoshihiro Naruo, Shinichiro Tokudome, Tsuyoshi Yagishita, Takayuki Yamamoto, Yoshifumi Inatani
  • THRUSTER USING NITROUS OXIDE
    Publication number: 20090007541
    Abstract: A thruster is provided that makes it possible to reduce and eventually eliminate the toxicity of storable liquid propellant and improve the low-temperature environment adaptability of propulsion system using the storable liquid propellant. The thruster produces thrust by using catalytic decomposition gas obtained by catalytically decomposing nitrous oxide with a nitrous oxide decomposition catalyst.
    Type: Application
    Filed: December 5, 2007
    Publication date: January 8, 2009
    Applicants: Japan Aerospace Exploration Agency, Showa Denko K.K.
    Inventors: Junichiro Kawaguchi, Shinichiro Tokudome, Hiroto Habu, Tsuyoshi Yagishita, Masatoshi Hotta