Abstract: A plasma thruster has a tunable electron source configured to provide electrons with controllable energy. An entry electrode and an exit electrode permit an air flow to pass from the entry electrode to the exit electrode. The entry electrode and exit electrode receive electrons from the tunable electron source. A controller selectively controls the entry and exit electrodes to accelerate positive and negative ions in the air.

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 thruster has a first stage and a second stage. The first stage is a plasma source that outputs a plasma. The second stage is an accelerator. In one embodiment, the second stage is a plasma accelerator that accelerates the plasma. In another embodiment, the second stage is an ion accelerator that accelerates the ions from the plasma.

Abstract: Solutions having a solvent and a cold atmospheric plasma dissolved in the solvent are described. Methods and systems of forming cold atmospheric plasma (CAP)-containing solutions are also described. A system for producing (CAP)-containing solutions includes a gas source; a plasma generating device having a hollow body fluidically coupled with the gas source, a closed proximal end and an open distal end, the hollow body receiving gas from the gas source, and at least one electrode in or about the hollow body and ionizing the gas to discharge a cold atmospheric plasma (CAP) from the open distal end; and a container for housing a fluid, the open distal end of the plasma generating device in fluid communication with an inner portion of the container. CAP-containing solutions can be used in treatment of cancer cells, infected tissue sterilization, microorganism inactivation, promotion of wound healing, skin regeneration, and blood coagulation, and teeth bleaching/whitening.

Abstract: A thruster has a first stage and a second stage. The first stage is a plasma source that outputs a plasma. The second stage is an accelerator. In one embodiment, the second stage is a plasma accelerator that accelerates the plasma. In another embodiment, the second stage is an ion accelerator that accelerates the ions from the plasma.

Abstract: A satellite propulsion system and methods of operating the same include a first ionization stage and a second acceleration stage. The first ionization stage has a plasma source configured to produce an arc discharge and emit a preliminary plasma. The plasma source includes an external magnetic field configured to magnetize the arc discharge. The second acceleration stage has an accelerator positioned in series with the plasma source. The accelerator is configured to accelerate the preliminary plasma out through the accelerator, thereby creating an accelerated plasma flow. The application of an activation threshold voltage to the accelerator results in a surge in system performance parameters.

Abstract: A micro-sized cold atmospheric plasma accessory. The micro-sized cold atmospheric plasma accessory comprises a tube, an active electrode within said tube, and a nozzle at a distal end of said tube, said nozzle having an inner diameter less than 1 mm and a length less than 30 mm. A distal end inner diameter of said tube is greater than said inner diameter of said nozzle. The nozzle preferable is 15-25 mm in length. The nozzle may comprise stainless steel. The tube may have an inner diameter greater than 1 mm. The nozzle preferably has a distal end inner diameter less than 280 ?m. The micro-sized cold atmospheric plasma accessory may further comprise a return electrode on an outside of said tube.

Abstract: A matrix thruster that may be used to reposition and/or stabilize a CubeSAT satellite. The matrix thruster includes a conductive plate with an opening, a plurality of wires within the opening, a power supply electrically connected to the conductive plate or each of the plurality of wires via an inductor, and an electrical switch. The electrical switch creates a current change that creates an electric potential spike across the inductor. The electric potential spike across the inductor initiates an arc discharge between one of the wires and the conductive plate, which forms plasma that ejects cathode particles from the matrix thruster. Using multiple wires (e.g., four titanium wires) extends the lifetime of the thruster, as each wire restores an inter-electrode film needed for the other wires to continue generating plasma.

Abstract: A method and system of adaptive cold atmospheric based treatment for diseased tissues, such as an area with cancerous cells, is disclosed. A plasma device generates a cold atmospheric plasma jet directed at the area having cancerous cells. A sensor is operable to sense the viability of the cancerous cells in the area. A controller is coupled to the plasma device and sensor. The controller is operative to control an initial plasma jet generated by the plasma device. The controller receives a sensor signal from the sensor to determine cell viability of the selected cells from the initial plasma jet. The controller adjusts the plasma jet based on the viability of the cancerous cells.

Abstract: A modular micro-cathode arc thruster for use in satellites. An exemplary satellite has a plurality of stacked modular arc thrusters, each having an external anode, an internal cathode, and an insulator therebetween. The arc thrusters are situated in a housing, wherein the housing has an opening to eject exhausted thrusters. Once an arc thruster is expended, the push rod ejects that arc thruster and the next arc thruster takes its place.

Abstract: A method and system of sensitization of cancerous cells in a volume is disclosed. A plasma tube including a pair of electrodes coupled to a power supply is provided. The plasma tube generates a plasma jet between the electrodes. A controller is coupled to a power supply to control a discharge voltage to the electrodes to generate the plasma jet and direct an electro-magnetic field at the volume having cancerous cells and normal cells for a sufficient time to sensitize the cancer cells. A treatment device applies a treatment such as TMZ to the sensitized cancer cells after the cancer cells are sensitized by the electro-magnetic field.

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: This disclosure relates to stabilized anti-cancer atmospheric plasma (CAP)-stimulated media, to methods for preparing such media, and to methods of treatment using such media.

Abstract: A thruster for a micro-satellite is disclosed. The thruster includes a cathode composed of a propellant material and an anode composed of ablative material. The thruster includes a housing having a proximate end and an opposite distal end having a thrust channel. The housing holds the anode and the cathode. A pulsed voltage source is coupled between the cathode and the anode causing current sufficient to create ablation of the anode and a plasma jet including ablated particles from the anode to be emitted from the thrust channel.

Abstract: A method and system of adaptive cold atmospheric based treatment for diseased tissues, such as an area with cancerous cells, is disclosed. A gas such as helium is ionized via supplying power between and anode and a cathode to create an initial cold atmospheric plasma jet. The initial plasma jet is directed toward the area for a sufficient time, such as 10 seconds, to sensitize the cells via a reactive species. A reactive treatment, such as H2O2 or TMZ, is directed to the sensitized cells. The effectiveness of the reactive treatment is increased by the process of sensitizing the cells.

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 matrix thruster that may be used to reposition and/or stabilize a CubeSAT satellite. The matrix thruster includes a conductive plate with an opening, a plurality of wires within the opening, a power supply electrically connected to the conductive plate or each of the plurality of wires via an inductor, and an electrical switch. The electrical switch creates a current change that creates an electric potential spike across the inductor. The electric potential spike across the inductor initiates an arc discharge between one of the wires and the conductive plate, which forms plasma that ejects cathode particles from the matrix thruster. Using multiple wires (e.g., four titanium wires) extends the lifetime of the thruster, as each wire restores an inter-electrode film needed for the other wires to continue generating plasma.

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 modular micro-cathode arc thruster for use in satellites. An exemplary satellite has a plurality of stacked modular arc thrusters, each having an external anode, an internal cathode, and an insulator therebetween. The arc thrusters are situated in a housing, wherein the housing has an opening to eject exhausted thrusters. Once an arc thruster is expended, the push rod ejects that arc thruster and the next arc thruster takes its place.

Abstract: A thruster has a first stage and a second stage. The first stage is a plasma source that outputs a plasma. The second stage is an accelerator. In one embodiment, the second stage is a plasma accelerator that accelerates the plasma. In another embodiment, the second stage is an ion accelerator that accelerates the ions from the plasma.