Abstract: Dual mode engine for propelling spacecraft, including combustion chamber having flange end, open nozzle end, and enclosed chamber portion extending therebetween, propellant tank in fluidic communication with combustion chamber, electronic controller, power source operationally connected to electronic controller, and fluid flow motivator operationally connected to electronic controller and connected in fluidic communication with propellant tank.

Abstract: A dual mode engine for propelling a spacecraft, including a combustion chamber having a flange end, an open nozzle end, and an enclosed chamber portion extending therebetween, a propellant tank in fluidic communication with the combustion chamber, an electronic controller, a power source operationally connected to the electronic controller, and a fluid flow motivator operationally connected to the electronic controller and connected in fluidic communication with the propellant tank. The engine further includes a chemical propulsion portion further including a propellant inlet port operationally connected to the combustion chamber and disposed adjacent the flange end, an ignition trigger electrode positioned in the combustion chamber adjacent the propellant inlet port and operationally connected to the electronic controller and operationally connected to the power source, wherein the propellant inlet port is fluidically connected to the propellant tank.

Abstract: A system is provided for generating plasma within narrow diameter tubes, e.g., tubes with an inner diameter of less than 1 millimeter. The system may comprise the tube, a nozzle connected to at least one end of the tube configured to supply a gas into the interior of the tube at atmospheric pressure, at least one ring-shaped anode electrode and configured to surround an outer surface of the tube, at least one ring-shaped cathode electrode spaced apart from the anode electrode along the longitudinal axis and configured to surround the outer surface of the tube, and a voltage source connected to the at least one anode electrode. When activated, the system is configured to generate an electric field between the electrodes which ignites a plasma within the gas in the interior of the tube.

Abstract: A dual mode engine for propelling a spacecraft, including a combustion chamber having a flange end, an open nozzle end, and an enclosed chamber portion extending therebetween, a propellant tank in fluidic communication with the combustion chamber, an electronic controller, a power source operationally connected to the electronic controller, and a fluid flow motivator operationally connected to the electronic controller and connected in fluidic communication with the propellant tank. The engine further includes a chemical propulsion portion further including a propellant inlet port operationally connected to the combustion chamber and disposed adjacent the flange end, an ignition trigger electrode positioned in the combustion chamber adjacent the propellant inlet port and operationally connected to the electronic controller and operationally connected to the power source, wherein the propellant inlet port is fluidically connected to the propellant tank.

Abstract: An integrated gas-enhanced electrosurgical generator. The generator comprises a high frequency power module, a low frequency power module and a gas module. The high frequency power module adapted to generate an electrical energy having a band of frequencies centered around a first frequency, wherein the electrical energy has a first power as the first frequency and a second power lower than the first power at a second frequency lower than the first frequency. The low frequency power module having an input connected to an output of the high frequency module. The low frequency module comprises a resonant transformer comprising a ferrite core, a primary coil and a secondary coil, the secondary coil having a larger number of turns than the primary coil, wherein the resonant transformer has a resonant frequency equal to the second frequency. The gas module is adapted to control a flow of an inert gas.

Abstract: Methods and systems capable of measuring gas temperatures utilizing plasma discharges. Such a method performs a measurement of a temperature of a gas by generating a probing nanosecond plasma pulse in the gas, and then using an optical emission spectroscopy technique to measure the temperature of the gas by processing a light emission signal excited by the probing nanosecond plasma pulse.

Abstract: A system for propelling a nanosatellite, including a pair of separated electrodes defining an ignition space therebetween a power source operationally connected to the pair of separated electrodes. Also included is a liquid propellant reservoir a pump reconnected in fluidic communication with reservoir and the ignition space and an electronic controller operationally corrected to the power source and to the pump.

Abstract: A system and method of treating an area having cancerous cells. The system includes a plasma device to generate a plasma jet directed at the area having cancerous cells. A magnetic field generator generates a magnetic field directed at the area having cancerous cells. A controller is coupled to the plasma device and the magnetic field generator to control the plasma jet generated by the plasma device and control the magnetic field generated by the magnetic field generator.

Abstract: A method of determining stress within a composite structure is provided which includes coupling a sensor to a composite structure under load having embedded therein a plurality of particles, wherein the particles at room temperature are paraelectric or ferroelectric, transmitting an electromagnetic radiation to the sensor, thereby generating an electromagnetic field into the composite structure, sweeping frequency from a first frequency to a second frequency in a pulsed manner, receiving reflected power from the composite structure, determining the resonance frequency of the sensor, and translating the resonance frequency of the sensor to stress within the composite structure.

Abstract: Methods and systems capable of measuring gas temperatures utilizing plasma discharges. Such a method performs a measurement of a temperature of a gas by generating a probing nanosecond plasma pulse in the gas, and then using an optical emission spectroscopy technique to measure the temperature of the gas by processing a light emission signal excited by the probing nanosecond plasma pulse.

Abstract: An integrated gas-enhanced electrosurgical generator. The generator comprises a high frequency power module, a low frequency power module and a gas module. The high frequency power module adapted to generate an electrical energy having a band of frequencies centered around a first frequency, wherein the electrical energy has a first power as the first frequency and a second power lower than the first power at a second frequency lower than the first frequency. The low frequency power module having an input connected to an output of the high frequency module. The low frequency module comprises a resonant transformer comprising a ferrite core, a primary coil and a secondary coil, the secondary coil having a larger number of turns than the primary coil, wherein the resonant transformer has a resonant frequency equal to the second frequency. The gas module is adapted to control a flow of an inert gas.

Abstract: An apparatus or device for performing cold atmospheric plasma procedures. The device or apparatus has a housing, a chamber within the housing, an entry port to the chamber, a plurality of exit ports from the chamber, and a plurality of electrodes mounted in the housing, each of the plurality of electrodes having a distal end adjacent one of the plurality of exit ports. The entry port, chamber, exit ports and plurality of electrodes are configured to provide for an inert gas flowing in the entry port and through the chamber to the exit port to become plasmatized by electrical energy applied to the plurality of electrodes to form a cold plasma flowing from the exit ports.

Abstract: An integrated gas-enhanced electrosurgical generator. The generator comprises a high frequency power module, a low frequency power module and a gas module. The high frequency power module adapted to generate an electrical energy having a band of frequencies centered around a first frequency, wherein the electrical energy has a first power as the first frequency and a second power lower than the first power at a second frequency lower than the first frequency. The low frequency power module having an input connected to an output of the high frequency module. The low frequency module comprises a resonant transformer comprising a ferrite core, a primary coil and a secondary coil, the secondary coil having a larger number of turns than the primary coil, wherein the resonant transformer has a resonant frequency equal to the second frequency. The gas module is adapted to control a flow of an inert gas.

Abstract: A system for propelling a nanosatellite, including a pair of separated electrodes defining an ignition space therebetween a power source operationally connected to the pair of separated electrodes. Also included is a liquid propellant reservoir a pump reconnected in fluidic communication with reservoir and the ignition space and an electronic controller operationally corrected to the power source and to the pump.

Abstract: An apparatus or device for performing cold atmospheric plasma procedures. The device or apparatus has a housing, a chamber within the housing, an entry port to the chamber, a plurality of exit ports from the chamber, and a plurality of electrodes mounted in the housing, each of the plurality of electrodes having a distal end adjacent one of the plurality of exit ports.

Abstract: A system and method for producing graphene includes a heating block, substrate, motor and collection device. The substrate is arranged about the heating block and is configured to receive heat from the heating block. A motor is connected to the substrate to rotate the substrate about the heating block. A cathode and anode are configured to direct a flux stream for deposit onto the rotating substrate. A collection device removes the deposited material from the rotating substrate. A heating element is embedded in the heating block and imparts heat to the heating block. The heating block is made of cement or other material that uniformly disperses the heat from the heating element throughout the heating block. The flux stream can be a carbon vapor, with the deposited flux being graphene.

Abstract: A method of determining stress within a composite structure is provided which includes coupling a sensor to a composite structure under load having embedded therein a plurality of particles, wherein the particles at room temperature are paraelectric or ferroelectric, transmitting an electromagnetic radiation to the sensor, thereby generating an electromagnetic field into the composite structure, sweeping frequency from a first frequency to a second frequency in a pulsed manner, receiving reflected power from the composite structure, determining the resonance frequency of the sensor, and translating the resonance frequency of the sensor to stress within the composite structure.

Abstract: An ignitor subsystem for use in an electric propulsion system is disclosed. The igniter subsystem includes an igniter, which includes a first electrically conducting electrode, a second electrically conducting electrode, and an electrically insulating layer sandwiched between the first and the second electrically conducting electrodes, and a voltage pulse generator electrically coupled to the first and the second electrically conducting electrodes and is adapted to generate a plurality of pulses each with sufficient voltage to cause a breakdown of the electrically insulating layer, thus causing an avalanche of electrons from one of the first and the second electrically conducting electrodes to the other, the voltage pulse generator is further adapted to limit energy transferred to the igniter in each of the plurality of pulses so as to minimize damage to the igniter.

Abstract: A device uses cold plasma to treat cancerous tumors. The device has a gas supply tube with a delivery end. The gas supply tube is configured to carry a gas to the delivery end. A syringe is provided having an opening. The syringe is connected to the supply tube and configured to carry the gas to the opening. A first electrode is positioned inside said syringe, and a second electrode is positioned adjacent to the opening. The first and second electrodes excite the gas to enter a cold plasma state prior to being discharged from the opening of the syringe. An endoscopic tube can be used instead of the syringe. An exhaust tube can be provided to remove gas introduced into the body cavity by the cold plasma jet.

Abstract: An electrosurgical cable that produces no electromagnetic (EM) field around its vicinity (zero-EM pollution). The cable is comprised of inner insulator with embedded conductor placed inside the outer insulator tube with embedded second conductor. Sizes and materials of conductors and insulators are chosen so that voltage applied to inner conductor is higher than the breakdown voltage while voltage applied to gas gap inside the electrosurgical cable is below than the breakdown voltage. Therefore, the cable is producing discharge at the surgical handpiece, but breakdown inside the cable is prohibited.