Patents by Inventor Ryan Earl Roberts

Ryan Earl Roberts 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).

  • Hybrid injection thrust vector control
    Patent number: 6470669
    Abstract: A rocket engine (10) generates a flow of hot propulsion fluid through a nozzle (14N) for generating propulsive thrust along a thrust vector 8. Hybrid exhaust gas generators (36,38) have their exhausts (44,54) through the side of the nozzle. Each gas generator includes a fuel grain (46,56) and a source of oxidizer (16,40,50). The fuel grain is kept hot by either or both (a) direct radiation or conduction from the hot propulsion fluid, or (b) by a trickle of oxidizer. The fuel grain can thus react quickly to a substantial flow of oxidizer.
    Type: Grant
    Filed: January 3, 2002
    Date of Patent: October 29, 2002
    Assignee: Lockheed Martin Corporation
    Inventors: Herbert Stephens Jones, Joseph Paul Arves, Darren Andrew Kearney, Ryan Earl Roberts, Rory Nell McLeod
  • HYBRID INJECTION THRUST VECTOR CONTROL
    Publication number: 20020078680
    Abstract: A rocket engine (10) generates a flow of hot propulsion fluid through a nozzle (14N) for generating propulsive thrust along a thrust vector 8. One or more hybrid exhaust gas generators (36,38) have their exhausts (44,54) through the side of the nozzle. Each gas generator includes a fuel grain (46,56) and a source of oxidizer (16,40,50). The fuel grain produces exhaust gas only when oxidizer is provided. The fuel grain is kept hot by either or both (a) direct radiation or conduction from the hot propulsion fluid, or (b) by a trickle of oxidizer. The fuel grain can thus react quickly to a substantial flow of oxidizer. When the thrust vector is to be modified, the appropriate one of the hybrid gas generators receives a flow of oxidizer, and the resulting exhaust gas is injected through the side of the nozzle to disrupt the flow of propulsion fluid and modify the thrust vector.
    Type: Application
    Filed: January 3, 2002
    Publication date: June 27, 2002
    Applicant: Lockhead Martin Corporation
    Inventors: Herbert Stephen Jones, Joseph Paul Arves, Darren Andrew Kearney, Ryan Earl Roberts, Rory Neil McLeod
  • Hybrid injection thrust vector control
    Patent number: 6354074
    Abstract: A rocket engine (10) generates a flow of hot propulsion fluid through a nozzle (14N). Hybrid exhaust gas generators (36,38) have their exhausts (44,54) through the side of the nozzle. Each gas generator includes a fuel grain (46,56) and a source of oxidizer (16,40,50). The fuel grain is kept hot by either or both (a) direct radiation or conduction from the hot propulsion fluid, or (b) by a trickle of oxidizer. When the thrust vector is to be modified, the appropriate one of the hybrid gas generators receives a flow of oxidizer, and the resulting exhaust gas is injected through the side of the nozzle.
    Type: Grant
    Filed: May 24, 2000
    Date of Patent: March 12, 2002
    Assignee: Lockheed Martin Corp.
    Inventors: Herbert Stephen Jones, Joseph Paul Arves, Darren Andrew Kearney, Ryan Earl Roberts, Rory Nell McLeod