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.

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%.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.