Patents by Inventor Guy Bruce Spear

Guy Bruce Spear 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).

  • Propellant test apparatus and method
    Patent number: 6662629
    Abstract: A test apparatus and method for a solid propellant, comprising a combustion chamber for the solid propellant, an igniter for igniting propellant in the combustion chamber, and an exhaust housing having a primary exhaust channel extending from the combustion chamber to an exit nozzle. A supplemental exhaust channel is connected to the primary exhaust channel, and a valve controls the size of the supplemental exhaust channel to selectively vary the flow of propellant gases therethrough, thereby to selectively vary the combustion chamber pressure to enable the testing of the burning characteristics of the propellant over a wide pressure range independent of the burning surface area of the propellant. In a further embodiment, an auxiliary exhaust channel closed by a burst disk is connected to the primary exhaust channel.
    Type: Grant
    Filed: April 12, 2002
    Date of Patent: December 16, 2003
    Assignee: Atlantic Research Corporation
    Inventors: Farid M. Khadduri, Guy Bruce Spear
  • PROPELLANT TEST APPARATUS AND METHOD
    Publication number: 20030192364
    Abstract: A test apparatus and method for a solid propellant, comprising a combustion chamber for the solid propellant, an igniter for igniting propellant in the combustion chamber, and an exhaust housing having a primary exhaust channel extending from the combustion chamber to an exit nozzle. A supplemental exhaust channel is connected to the primary exhaust channel, and a valve controls the size of the supplemental exhaust channel to selectively vary the flow of propellant gases therethrough, thereby to selectively vary the combustion chamber pressure to enable the testing of the burning characteristics of the propellant over a wide pressure range independent of the burning surface area of the propellant. In a further embodiment, an auxiliary exhaust channel closed by a burst disk is connected to the primary exhaust channel.
    Type: Application
    Filed: April 12, 2002
    Publication date: October 16, 2003
    Inventors: Farid M. Khadduri, Guy Bruce Spear