A vehicle comprising a structure, a plurality of heating sources, and a transport mechanism. The structure is comprised of multiple materials, a composite such that some of the material constituents can be extracted leaving behind others via application of energy (such as de-alloying). The extracted material or materials are configured to be re-purposed into a propellant. The plurality of heating elements surrounds or is embedded within the structure configured to convert the material into the propellant. The transport mechanism is configured to transport the propellant from the structure to a reservoir or to the propulsion system.

An ion jet engine system includes a jet turbine engine having at least one high voltage turbine blade, a microwave emitter in communication with the jet turbine engine, a water tank having stainless steel plates for providing and being in communication with the jet turbine engine, a plasma torch in communication with the water tank, and a plasma chamber in communication with the plasma torch and having diameter spheres that trap and internally reflect microwaves. Advantageously, the jet turbine engine uses plasma from ionizing air, and liquid hydrogen and/or oxygen from electrolyzing water to create thrust.

High propellant throughput Hall-effect thrusters (HETs) and components thereof are disclosed. A compact and high propellant throughput HET has an improved magnetic circuit that mostly shields the discharge chamber walls from high-energy ionized propellant, low-profile sacrificial pole covers to delay magnetic pole erosion, a unique discharge chamber subassembly, a mechanically crimped cathode emitter retainer to increase efficiency, a center-mounted hollow cathode, or a combination thereof. Such feature(s) may balance propellant throughput and thruster performance, minimize the volume of the thruster envelope, and/or simplify the thruster assembly.

A narrow channel Hall thruster comprising a thruster body with a magnetic circuit, an annular thruster channel having a channel width of less than 3 mm formed within the magnetic circuit, an annular anode, a cathode positioned externally to the thruster, and configured for electron emission, a power supply applying a positive potential to the anode, such that a plasma discharge can be generated in the annular thruster channel, and another power supply applying a negative potential to the cathode, relative to the thruster body and the anode. The second power supply reduces its negative voltage output to the cathode when the current supplied by the anode power supply exceeds a predetermined level, indicating that the discharge has reached a stable initiated condition. The reduction of the voltage output of the second power supply can be achieved either by self-regulation, or by use of a current limit circuit.

A multi-mode thruster system for use in a spacecraft includes a microwave source; a cavity coupled to the microwave source and including a first inlet to receive a first fluid and a second inlet to receive a second fluid; and a nozzle provided at one end of the cavity. The thruster operates in a microwave electrothermal thruster (MET) mode to (i) generate a standing wave in the cavity using the microwave source and (ii) raise a temperature of the first fluid to generate a first hot gas that exits the cavity via the nozzle to generate thrust. The thruster operates in a chemical propulsion mode to (i) produce a reduction-oxidation reaction between the first fluid and the second fluid and (ii) generate a second hot gas that exits the cavity via the nozzle to generate thrust.

Fluid flow control valve comprising a tubular body extending in a longitudinal direction with a fluid inlet and a fluid outlet situated respectively at the two longitudinal ends of the body, the valve comprising a nozzle and a piston connected to the body, the piston being housed in the body, the nozzle being made up of a part provided with a fluid passage having a calibrated dimension, the passage emerging at one end of the nozzle and forming a seat, said seat being situated against a terminal end of the piston forming a shutter preventing the flow of fluid in the closed position of the valve, the piston comprising a body defining a passage for the fluid in the body for the flow of the fluid between the inlet and the outlet, the body of the valve consisting of a material having a different expansion coefficient from the piston or the nozzle, the valve comprising a heating member which, depending on the heating power delivered, makes it possible to separate the end of the nozzle and the piston by differential expansion, to allow the flow of fluid between the inlet and the outlet in an open position of the valve, characterized in that the terminal end of the piston comprises a ball that is crimped into the body of the piston.

Fluid flow control valve comprising a tubular body extending in a longitudinal direction with a fluid inlet and a fluid outlet situated respectively at the two longitudinal ends of the body, the valve comprising a nozzle and a piston connected to the body, the piston being housed in the body, the nozzle being made up of a part provided with a fluid passage having a calibrated dimension, the passage emerging at one end of the nozzle and forming a seat, said seat being situated against a terminal end of the piston forming a shutter preventing the flow of fluid in the closed position of the valve, the piston comprising a body defining a passage for the fluid in the body for the flow of the fluid between the inlet and the outlet, the body of the valve consisting of a material having a different expansion coefficient from the piston or the nozzle, the valve comprising a heating member which, depending on the heating power delivered, makes it possible to separate the end of the nozzle and the piston by differential expansion, to allow the flow of fluid between the inlet and the outlet in an open position of the valve, characterized in that the terminal end of the piston comprises a ball that is crimped into the body of the piston.

A system and method for generating a force from a voltage difference applied across at least one electrically conductive surface. The applied voltage difference creates an electric field resulting in an electrostatic pressure force acting on at least one surface of an object. Asymmetries in the resulting electrostatic pressure force vectors result in a net resulting electrostatic pressure force acting on the object. The magnitude of the net resulting electrostatic pressure force is a function of the geometry of the electrically conductive surfaces, the applied voltage, and the dielectric constant of any material present in the gap between electrodes. The invention may be produced on a nanoscale using nanostructures such as carbon nanotubes. The invention may be utilized to provide a motivating force to an object. A non-limiting use case example is the use of electrostatic pressure force apparatus as a thruster to propel a spacecraft through a vacuum.

A vacuum arc thruster device having a cathode rod disposed within a concentric insulator tube, and an anode electrode located at the distal edge of the insulator tube, separated from the cathode rod by the insulator tube. A controlled feeding mechanism moves the cathode towards the distal exit plane in a helical motion, the cathode rotating as it moves forward. The cathode rod is fixed in the center of a headless screw segment, which is rotated within a screw thread on the internal surface of a cylindrical wall of the device. As the erosion rate is concentrated at the exit plane, the screw action path enables uniform erosion around the cathode circumference, and cathode linear motion that can be matched to the radial erosion rate. The feeding rate and hence the thrust are proportional to the input power, which can be regulated by the pulse frequency.

This device, the (‘Demon’ Quantum Mechanical, (H/C)/(Propulsion) system), replaces entirely, the (antiquated system of using Cryogens for cooling, in satellite applications). This device, is the ONLY application, which uses (Quantum Mechanics) for Propulsion/Thrusting. This device is the ONLY design to use (Quantum Mechanics) to (simultaneously Heat and Cool) in any application. This device is the ONLY design to use (Quantum Mechanics) to (simultaneously Heat and Cool) and for (Propulsion) in any application, —and due to the system (operating methods) and (weightless environment), —with EXPONENTIALLY greater (fuel) efficiency. This device (extends the (working service life) of Satellites requiring cooling) from MONTHS, to 50+ YEARS/more.