Patents by Inventor Vladimir Hruby
Vladimir Hruby 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: 9944412Abstract: A spacecraft system and method includes a platform with a dock and an umbilical payout device. A robot is connected to an umbilical paid out by the umbilical payout device and is repeatedly deployable from the dock. The robot includes one or more imagers, an inertial measurement unit, and a plurality of thrusters. A command module receives image data from the one or more robot imagers and orientation data from the inertial measurement unit. An object recognition module is configured to recognize one or more objects from the received image data. The command module determines the robot's orientation with respect to an object and issues thruster control commands to control movement of the robot based on the robot's orientation. The combination of the space platform and robot on umbilical line can be used for towing another object to different orbital location, inspection including self-inspection of the robot carrying platform and for robotic servicing.Type: GrantFiled: October 3, 2014Date of Patent: April 17, 2018Assignee: Busek Co., Inc.Inventors: James J. Szabo, Vladimir Hruby, Thomas R. Roy, Craig DeLuccia, Jay Andrews, W. Dan Williams, Matthew R. Berlin, Jesse V. Gray
-
Publication number: 20150097084Abstract: A spacecraft system and method includes a platform with a dock and an umbilical payout device. A robot is connected to an umbilical paid out by the umbilical payout device and is repeatedly deployable from the dock. The robot includes one or more imagers, an inertial measurement unit, and a plurality of thrusters. A command module receives image data from the one or more robot imagers and orientation data from the inertial measurement unit. An object recognition module is configured to recognize one or more objects from the received image data. The command module determines the robot's orientation with respect to an object and issues thruster control commands to control movement of the robot based on the robot's orientation. The combination of the space platform and robot on umbilical line can be used for towing another object to different orbital location, inspection including self-inspection of the robot carrying platform and for robotic servicing.Type: ApplicationFiled: October 3, 2014Publication date: April 9, 2015Inventors: James J. Szabo, Vladimir Hruby, Thomas R. Roy, Craig DeLuccia, Jay Andrews, W. Dan Williams, Matthew R. Berlin, Jesse V. Gray
-
Patent number: 8907578Abstract: An autonomous method for minimizing the magnitude of plasma discharge current oscillations in a Hall effect plasma device includes iteratively measuring plasma discharge current oscillations of the plasma device and iteratively adjusting the magnet current delivered to the plasma device in response to measured plasma discharge current oscillations to reduce the magnitude of the plasma discharge current oscillations.Type: GrantFiled: September 17, 2012Date of Patent: December 9, 2014Assignee: Busek Co., Inc.Inventors: Vladimir Hruby, Nathaniel Demmons, Eric Ehrbar, Bruce Pote, Nathan Rosenblad
-
Patent number: 8610356Abstract: An iodine fueled plasma generator system includes a plasma generator. At least one storage vessel is configured to store condensed phase iodine therein. A heating device proximate to the storage vessel is configured to create iodine vapor from the condensed phase iodine. A propellant management subsystem is configured to deliver the iodine vapor to the plasma generator. A feedback control subsystem is responsive to one or more of plasma generator discharge current, the pressure of the iodine vapor, and/or the temperature of the iodine vapor configured to regulate the flow rate of the iodine vapor to the plasma generator.Type: GrantFiled: July 27, 2012Date of Patent: December 17, 2013Assignee: Busek Co., Inc.Inventors: James J. Szabo, Jr., Bruce Pote, Surjeet Paintal, Michael Robin, Vladimir Hruby
-
Patent number: 8550405Abstract: A solar powered spacecraft power system including a solar photovoltaic array, an electric propulsion system connected directly to the solar photovoltaic array in parallel with the spacecraft power system; the electric propulsion system including a Hall effect thruster, a thruster power supply for driving the thruster; a sensor for sensing the power output of the solar array and a controller responsive to the power output of the solar array and configured to periodically adjust an operating parameter of the thruster to operate the thruster at the maximum available output power of the solar array including comparing a previous solar array output power level with a later solar array output power level, and incrementing the operating parameter with a positive value if the later is greater and with a negative value if the later is lesser; a solar powered spacecraft power system including a solar photovoltaic array, an electric propulsion system connected directly to the solar photovoltaic array, and a power manageType: GrantFiled: August 31, 2010Date of Patent: October 8, 2013Assignee: Busek Company, Inc.Inventors: Vladimir Hruby, Thomas Jaquish, Antonio Rizzo, Eric Ehrbar
-
Publication number: 20130093350Abstract: An autonomous method for minimizing the magnitude of plasma discharge current oscillations in a Hall effect plasma device includes iteratively measuring plasma discharge current oscillations of the plasma device and iteratively adjusting the magnet current delivered to the plasma device in response to measured plasma discharge current oscillations to reduce the magnitude of the plasma discharge current oscillations.Type: ApplicationFiled: September 17, 2012Publication date: April 18, 2013Inventors: Vladimir Hruby, Nathaniel Demmons, Eric Ehrbar, Bruce Pote, Nathan Rosenblad
-
Publication number: 20130026920Abstract: An iodine fueled plasma generator system includes a plasma generator. At least one storage vessel is configured to store condensed phase iodine therein. A heating device proximate to the storage vessel is configured to create iodine vapor from the condensed phase iodine. A propellant management subsystem is configured to deliver the iodine vapor to the plasma generator. A feedback control subsystem is responsive to one or more of plasma generator discharge current, the pressure of the iodine vapor, and/or the temperature of the iodine vapor configured to regulate the flow rate of the iodine vapor to the plasma generator.Type: ApplicationFiled: July 27, 2012Publication date: January 31, 2013Applicant: BUSEK COMPANY, INC.Inventors: James J. Szabo, JR., Bruce Pote, Surjeet Paintal, Michael Robin, Vladimir Hruby
-
Patent number: 7932492Abstract: An electrospray device includes an electrospray emitter adapted to receive electrospray fluid; an extractor plate spaced from the electrospray emitter and having at least one aperature; and a power supply for applying a first voltage between the extractor plate and emitter for generating at least one Taylor cone emission through the aperature to create an electrospray plume from the electrospray fluid, the extractor plate as well as accelerator and shaping plates may include a porous, conductive medium for transporting and storing excess, accumulated electrospray fluid away from the aperature.Type: GrantFiled: July 14, 2009Date of Patent: April 26, 2011Assignee: Busek Co. Inc.Inventors: Nathaniel Demmons, Roy Martin, Vladimir Hruby, Thomas Roy, Douglas Spence, Eric Ehrbar, Jurg Zwahlen
-
Publication number: 20110073714Abstract: a solar powered spacecraft power system including a solar photovoltaic array, an electric propulsion system connected directly to the solar photovoltaic array in parallel with the spacecraft power system; the electric propulsion system including a Hall effect thruster, a thruster power supply for driving the thruster; a sensor for sensing the power output of the solar array and a controller responsive to the power output of the solar array and configured to periodically adjust an operating parameter of the thruster to operate the thruster at the maximum available output power of the solar array including comparing a previous solar array output power level with a later solar array output power level, and incrementing the operating parameter with a positive value if the later is greater and with a negative value if the later is lesser; a solar powered spacecraft power system including a solar photovoltaic array, an electric propulsion system connected directly to the solar photovoltaic array, and a power manageType: ApplicationFiled: August 31, 2010Publication date: March 31, 2011Inventors: Vladimir Hruby, Thomas Jaquish, Antonio Rizzo, Eric Ehrbar
-
Publication number: 20100025575Abstract: An electrospray device includes an electrospray emitter adapted to receive electrospray fluid; an extractor plate spaced from the electrospray emitter and having at least one aperature; and a power supply for applying a first voltage between the extractor plate and emitter for generating at least one Taylor cone emission through the aperature to create an electrospray plume from the electrospray fluid, the extractor plate as well as accelerator and shaping plates may include a porous, conductive medium for transporting and storing excess, accumulated electrospray fluid away from the aperature.Type: ApplicationFiled: July 14, 2009Publication date: February 4, 2010Inventors: Nathaniel Demmons, Roy Martin, Vladimir Hruby, Thomas Roy, Douglas Spence, Eric Ehrbar, Jurg Zwahlen
-
Patent number: 7420182Abstract: This invention features a combined radio frequency (RF) and Hall Effect ion source and plasma accelerator system including a plasma accelerator having an anode and a discharge zone, the plasma accelerator for providing plasma discharge. A gas distributor introduces a gas into the plasma accelerator. A cathode emits electrons attracted to the anode for ionizing the gas and neutralizing ion flux emitted from the plasma accelerator. An electrical circuit coupled between the anode and the cathode having a DC power source provides DC voltage. A magnetic circuit structure including a magnetic field source establishes a transverse magnetic field in the plasma accelerator that creates an impedance to the flow of the electrons toward the anode to enhance ionization of the gas to create plasma and which in combination with the electric circuit establishes an axial electric field in the plasma accelerator.Type: GrantFiled: April 27, 2006Date of Patent: September 2, 2008Assignee: Busek CompanyInventors: Vladimir Hruby, Kurt Hohman, Thomas Brogan
-
Publication number: 20080083335Abstract: A liquid degasser for a space device including a gas permeable material configured for contact with a flow of liquid to be de-gassed on one side and a vacuum on the other side, and wherein the gas permeable material allows gas in the liquid to diffuse to the vacuum to remove the gas from the liquid.Type: ApplicationFiled: July 25, 2007Publication date: April 10, 2008Inventors: Vladimir Hruby, Nate Demmons, Tom Roy, Doug Spence, Eric Ehrbar, Jurg Zwahlen, Charles Gasdaska
-
Publication number: 20060284562Abstract: This invention features a combined radio frequency (RF) and Hall Effect ion source and plasma accelerator system including a plasma accelerator having an anode and a discharge zone, the plasma accelerator for providing plasma discharge. A gas distributor introduces a gas into the plasma accelerator. A cathode emits electrons attracted to the anode for ionizing the gas and neutralizing ion flux emitted from the plasma accelerator. An electrical circuit coupled between the anode and the cathode having a DC power source provides DC voltage. A magnetic circuit structure including a magnetic field source establishes a transverse magnetic field in the plasma accelerator that creates an impedance to the flow of the electrons toward the anode to enhance ionization of the gas to create plasma and which in combination with the electric circuit establishes an axial electric field in the plasma accelerator.Type: ApplicationFiled: April 27, 2006Publication date: December 21, 2006Inventors: Vladimir Hruby, Kurt Hohman, Thomas Brogan
-
Publication number: 20060186837Abstract: A Hall thruster with a shared magnetic structure including a plurality of plasma accelerators each including an anode and a discharge zone for providing plasma discharge. An electrical circuit having one or more cathodes connected to the plurality of plasma accelerators emits electrons that are attracted to the anode in each of the plasma accelerators. A shared magnetic circuit structure establishes a transverse magnetic field in each of the plurality of plasma accelerators that creates an impedance to the flow of electrons toward the anode in each of the plurality of plasma accelerators and enables ionization of a gas moving through one or more of the plurality of plasma accelerators. The impedance localizes an axial electric field in the plurality of plasma accelerators for accelerating ionized gas through the one or more of the plurality of plasma accelerators to create thrust.Type: ApplicationFiled: December 13, 2005Publication date: August 24, 2006Inventors: Vladimir Hruby, Bruce Pote, Rachel Tedrake, Lawrence Byrne, James Szabo, Juraj Kolencik