Patents by Inventor Rodney L. Burton

Rodney L. Burton 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).

  • Publication number: 20200233575
    Abstract: Presenting a plurality of windows on a display of a mobile device can comprise displaying a first window on the display. The first window can be a dual-display window displayed on both a first and second display portion of the display. In response to a touch gesture, a second window can be presented on at least one of the first and second display portions. When the second window is a dual-display window, the second window can be displayed in the first and second display portions. When the second window is not a dual-display window, the second window can be displayed on one of the first and second display portions and a third window can be displayed on another one of the first and second display portions. When the third window is a dual-display window, it can be displayed on the other one of the first and second display portions.
    Type: Application
    Filed: January 21, 2020
    Publication date: July 23, 2020
    Inventors: Sanjiv Sirpal, Brett B. Faulk, Paul E. Reeves, Alexander de Paz, Rodney W. Schrock, John S. Visosky, Eric Freedman, Jared L. Ficklin, Denise L. Burton, Misty Cripps, Gregg Wygonik
  • Patent number: 10540087
    Abstract: An intuitive technique for inputting user gestures into a handheld computing device is disclosed allowing a user to better manipulate different types of screen display presentations, such as desktops and application windows, when performing tasks thereon, wherein a window stack for application windows and/or desktops can be navigated and sequentially displayed according to the window stack ordering without disturbing or changing this ordering.
    Type: Grant
    Filed: December 14, 2015
    Date of Patent: January 21, 2020
    Assignee: Z124
    Inventors: Sanjiv Sirpal, Brett B. Faulk, Paul E. Reeves, Alexander de Paz, Rodney W. Schrock, John S. Visosky, Eric Freedman, Jared L. Ficklin, Denise L. Burton, Misty Cripps, Gregg Wygonik
  • Patent number: 9909574
    Abstract: A method for operating self-pressurizing propellants in space thruster chambers and nozzles heated by resistive, radiative or nuclear methods at temperatures hundreds of degrees above the decomposition temperature. The method is defined by reducing the chamber volume Vc and increasing the nozzle throat area A* such that a propellant vapor with sonic velocity a* experiences a high temperature residence time that is less than 10 milliseconds. In other aspects of the invention propellant vapor is formed from a self-pressurizing propellant and the residence time is such that the propellant vapor does not decompose nor does the propellant vapor polymerize to a solid.
    Type: Grant
    Filed: May 2, 2016
    Date of Patent: March 6, 2018
    Assignee: CU Aerospace, LLC
    Inventors: Neil J. Heimanowski, Curtis A. Woodruff, Rodney L. Burton, David L. Carroll
  • Patent number: 9242747
    Abstract: It is disclosed herein an innovative concept for in-space propulsion for future Air Force, NASA and commercial systems having mass and power scalability over a wide range and using easily-handled advanced propellants. The invention combines the fields of microdischarge physics and nonequilibrium plasmadynamics to reduce dramatically the size of electric thrusters by 1-2 orders of magnitude, which when coupled with micronozzles that are electrically conducting or electrically insulating result in high thrust and high thruster efficiency, and will enable scalable, low-cost, long-life distributable propulsion for control of femtosats, picosats, nanosats, microsats, and space structures. The concept is scalable from power levels of 1 W to several kilowatts with thrust efficiency approaching 60%.
    Type: Grant
    Filed: November 19, 2012
    Date of Patent: January 26, 2016
    Assignee: CU Aerospace, LLC
    Inventors: Rodney L. Burton, Gabriel F. Benavides, David L. Carroll
  • Patent number: 8689537
    Abstract: It is disclosed herein a breakthrough concept for in-space propulsion for future Air Force, NASA and commercial systems. The invention combines the fields of micro-electrical-mechanical (MEMs) devices, optical physics, and nonequilibrium plasmadynamics to reduce dramatically the size of electric thrusters by 1-2 orders of magnitude, which when coupled with electrodeless operation and high thruster efficiency, will enable scalable, low-cost, long-life distributable propulsion for control of microsats, nanosats, and space structures. The concept is scalable from power levels of 1 W to tens of kilowatts with thrust efficiency exceeding 60%. Ultimate specific impulse would be 500 seconds with helium, with lower values for heavier gases.
    Type: Grant
    Filed: October 19, 2009
    Date of Patent: April 8, 2014
    Assignee: CU Aerospace, LLC
    Inventors: Rodney L. Burton, James Gary Eden, Sung-Jin Park, David L. Carroll
  • Patent number: 7935176
    Abstract: A facility and process capable of extracting oxygen in extraterrestrial environments from materials available in extraterrestrial environments, for example, on planets, planetoids, etc. The facility extracts oxygen from a mineral-containing solid material and is configured to form a free-falling molten stream of the solid material, evaporate at least a portion of the molten stream and produce a vapor containing gaseous oxygen, create a supersonic stream of the vapor, condense constituents of the supersonic stream to form particulates within the supersonic stream, separate the gaseous oxygen from the particulates, and then collect the gaseous oxygen.
    Type: Grant
    Filed: October 23, 2008
    Date of Patent: May 3, 2011
    Assignee: Packer Engineering, Inc.
    Inventors: Rodney L. Burton, Peter J. Schubert, Filip Rysanek, Paul Fenoglio, Mike Hutches
  • Patent number: 7926258
    Abstract: A pulsed plasma thruster provides for an advanced lightweight design with solid propellant and predominately electromagnetic thrust in a coaxial geometry. Electromagnetic forces are generated in a plasma by current flowing from a small central electrode to an electrically conducting diverging nozzle electrode. The thruster employs a series of electric current pulses of limited duration and varying frequency between the pair of electrodes creating a series of electric arcs. The electric arcs pass over a propellant surface located between the electrodes, forming a plasma, which is then exhausted from the device to produce thrust. The thruster maintains a low plasma resistance and cavity pressure, which in turn yields strong electromagnetic body forces, resulting in a high efficiency and consistent pulse-to-pulse performance.
    Type: Grant
    Filed: July 22, 2008
    Date of Patent: April 19, 2011
    Assignee: CU Aerospace, LLC
    Inventors: Rodney L. Burton, Gabriel F. Benavides, Julia K. Laystrom
  • Patent number: 7926257
    Abstract: A pulsed plasma thruster provides for an advanced lightweight design with solid propellant and predominately electromagnetic thrust in a coaxial geometry. Electromagnetic forces are generated in a plasma by current flowing from a small central electrode to an electrically conducting diverging nozzle electrode. The thruster employs a series of electric current pulses of limited duration and varying frequency between the pair of electrodes creating a series of electric arcs. The electric arcs pass over a propellant surface located between the electrodes, forming a plasma, which is then exhausted from the device to produce thrust. The thruster maintains a low plasma resistance and cavity pressure, which in turn yields strong electromagnetic body forces, resulting in a high efficiency and consistent pulse-to-pulse performance.
    Type: Grant
    Filed: July 22, 2008
    Date of Patent: April 19, 2011
    Assignee: CU Aerospace, LLC
    Inventors: Rodney L. Burton, Gabriel F. Benavides, Julia K. Laystrom
  • Publication number: 20090269273
    Abstract: A facility and process capable of extracting oxygen in extraterrestrial environments from materials available in extraterrestrial environments, for example, on planets, planetoids, etc. The facility extracts oxygen from a mineral-containing solid material and is configured to form a free-falling molten stream of the solid material, evaporate at least a portion of the molten stream and produce a vapor containing gaseous oxygen, create a supersonic stream of the vapor, condense constituents of the supersonic stream to form particulates within the supersonic stream, separate the gaseous oxygen from the particulates, and then collect the gaseous oxygen.
    Type: Application
    Filed: October 23, 2008
    Publication date: October 29, 2009
    Applicant: PACKER ENGINEERING, INC.
    Inventors: Rodney L. Burton, Peter J. Schubert, Filip Rysanek, Paul Fenoglio, Mike Hutches
  • Patent number: 6808145
    Abstract: The present invention includes a method for a dual-mode propulsion system. During the first mode of operation, intake air is liquefied through a cooling heat exchanger and condenser using a combination of stored liquid hydrogen (LH2) and stored liquid nitrogen (LN2) as coolants. The liquefied air is then separated into separated liquid oxygen (SLO2) and separated liquid nitrogen (SLN2), which may contain molecules of each other or other elements commonly found in air. The stored liquid nitrogen is replaced with SLO2, while the SLN2 is pumped back through the system with the stored nitrogen in a regeneration process. The SLN2, LN2, and LH2 become gaseous as they pass through the condenser and heat exchanger and are burned in the dual mode rocket thrust chamber to produce thrust. In the second mode, the same thrust chamber is operated as a liquid hydrogen-oxygen rocket, where the liquid oxygen is the SLO2 collected during the first mode.
    Type: Grant
    Filed: February 7, 2003
    Date of Patent: October 26, 2004
    Assignee: CU Aerospace
    Inventor: Rodney L. Burton
  • Publication number: 20040026572
    Abstract: The present invention includes a method for a dual-mode propulsion system. During the first mode of operation, intake air is liquefied through a cooling heat exchanger and condenser using a combination of stored liquid hydrogen (LH2) and stored liquid nitrogen (LN2) as coolants. The liquefied air is then separated into separated liquid oxygen (SLO2) and separated liquid nitrogen (SLN2), which may contain molecules of each other or other elements commonly found in air. The stored liquid nitrogen is replaced with SLO2, while the SLN2 is pumped back through the system with the stored nitrogen in a regeneration process. The SLN2, LN2, and LH2 become gaseous as they pass through the condenser and heat exchanger and are burned in the dual mode rocket thrust chamber to produce thrust. In the second mode, the same thrust chamber is operated as a liquid hydrogen-oxygen rocket, where the liquid oxygen is the SLO2 collected during the first mode.
    Type: Application
    Filed: February 7, 2003
    Publication date: February 12, 2004
    Applicant: CU Aerospace, LLC
    Inventor: Rodney L. Burton
  • Patent number: 6295804
    Abstract: A thruster system includes a power supply and a pulse forming circuit coupled to the power supply. The pulse forming circuit includes a capacitor and first and second diodes. The positively-charged plate of the capacitor is coupled to the anode of the first diode, the negatively-charged of the capacitor is coupled to the anode of the second diode, and the cathode of the first diode is coupled to the cathode of the second diode. A low-impedance thruster is coupled in parallel to the second diode.
    Type: Grant
    Filed: October 21, 1998
    Date of Patent: October 2, 2001
    Assignee: The Board of Trustees of the University of Illinois
    Inventors: Rodney L. Burton, Gary Willmes
  • Patent number: 5924278
    Abstract: A thruster includes a body having a cavity with a discharge end, an apparatus for generating an electric arc having a current path through the cavity between first and second locations, and a non-gaseous, non-liquid propellant material (26) that forms an ionized gas as an incident of being heated. The propellant material (26) is heated by the electric arc to produce an ionized gas in the cavity. The cavity is configured to cause the ionized gas to be expelled from the cavity through the discharge end of the cavity in a flow path that is substantially parallel to the electric arc and current path within the cavity.
    Type: Grant
    Filed: April 3, 1997
    Date of Patent: July 20, 1999
    Assignee: The Board of Trustees of the University of Illinois
    Inventors: Rodney L. Burton, Susan G. Delmedico, Michael Wilson
  • Patent number: 5425231
    Abstract: The present invention relates to a thruster for propelling a mass using a propellant gas which is repetitively converted to a pressurized plasma by pulses of electrical energy.
    Type: Grant
    Filed: August 12, 1994
    Date of Patent: June 20, 1995
    Inventor: Rodney L. Burton
  • Patent number: 4974487
    Abstract: A projectile is accelerated in a barrel bore by applying a plasma jet to a projectile propelling fluid. The plasma jet is derived from a structure forming a capillary passage having a wall formed by a low molecular weight, dielectric powdery filler or water in many rigid containers, shaped as spheres or straw-like tubes having axes parallel to the passage longitudinal axis. The fluid and jet interact so the fluid is heated by the jet, whereby low atomic weight constituents of the fluid are sufficiently heated to become mixed with the plasma to form a high pressure mixture that is injected into the bore to accelerate the projectile. The fluid is dragged into the plasma during mixing to cool the plasma and form a boundary layer between the plasma and the barrel walls so that the mixture does not cause substantial damage to the walls of the bore. The plasma is energized by applying voltage from an electric pulse source to electrodes at opposite ends of the passage.
    Type: Grant
    Filed: October 3, 1988
    Date of Patent: December 4, 1990
    Assignee: GT-Devices
    Inventors: Yeshayahu S. A. Goldstein, Derek A. Tidman, Rodney L. Burton, Dennis W. Massey, Niels K. Winsor
  • Patent number: 4821508
    Abstract: A plasma electrothermal thruster includes a capillary passage in which a plasma discharge is formed and directed out of an open end of the passage into a supersonic nozzle. Liquid supplied to the capillary passage becomes partially atomized to cool a confining surface of the passage. The plasma discharge is formed as the atomized liquid flows out of the open end into a supersonic equilibrium nozzle. The discharge can have a duration greater than the two way travel time of acoustic energy in the capillary to cause the plasma to flow continuously through the nozzle during the time of the discharge pulse.
    Type: Grant
    Filed: June 10, 1985
    Date of Patent: April 18, 1989
    Assignee: GT-Devices
    Inventors: Rodney L. Burton, Yeshayahu S. A. Goldstein, Derek A. Tidman, Niels K. Winsor
  • Patent number: 4821509
    Abstract: A plasma electrothermal thruster includes a capillary passage in which a plasma discharge is formed and directed out of an open end of the passage into a supersonic nozzle. Liquid supplied to the capillary passage becomes partially atomized to cool a confining surface of the passage. The plasma discharge is formed as the atomized liquid flows out of the open end into a supersonic equilibrium nozzle. The discharge can have a duration greater than the two way travel time of acoustic energy in the capillary to cause the plasma to flow continuously through the nozzle during the time of the discharge pulse.
    Type: Grant
    Filed: December 7, 1987
    Date of Patent: April 18, 1989
    Assignee: GT-Devices
    Inventors: Rodney L. Burton, Yeshayahu S. A. Goldstein, Derek A. Tidman, Niels K. Winsor
  • Patent number: 4715261
    Abstract: A projectile is accelerated through a gun barrel bore by a cartridge containing a high temperature, high pressure plasma jet source. The cartridge has a geometry enabling it to be loaded into a breech bore of the gun. The plasma jet is supplied to the rear of the projectile and is derived by a tube having an interior wall forming a capillary passage. A discharge voltage applied between spaced regions along the capillary passage ionizes a dielectric to form a plasma. First and second ends of the passage are respectively open and blocked to enable and prevent the flow of plasma through them. The blocked end closes the breech bore.
    Type: Grant
    Filed: October 5, 1984
    Date of Patent: December 29, 1987
    Assignee: GT-Devices
    Inventors: Yeshayahu S. A. Goldstein, Derek A. Tidman, Rodney L. Burton, Dennis W. Massey, Niels K. Winsor