Abstract: Thruster grid clear circuits and methods to clear thruster grids are disclosed. An example apparatus includes a low voltage grid clear circuit to apply first energy to a grid at a first voltage, and a high voltage grid clear circuit to detect a failure of the applied energy to clear a short circuit condition of the grid and to apply second energy to the grid at a second voltage higher than the first voltage.

Abstract: The present subject matter overcomes the deficiencies in the prior art by introducing or generating charged particles in an air stream and manipulating the air stream with magnetic fields operating on the charged particles. Embodiments of the present subject matter compress the air stream by accelerating charged particles with a moving magnetic field, where the magnetic field has a velocity perpendicular to its flux lines. The increased velocity of the charged particles increases the statistical mean particle velocity and thereby increases the pressure in the air stream. The compressed air stream is then heated and expanded through a second magnetic field. The expansion of the air stream substantially increases the velocity of the air stream and the charged particles therein. The interaction of the high velocity charged particles and the magnetic field imparts a force perpendicular to the flux lines, this force powers the movement of the magnetic field and can also be extracted in the form of mechanical work.

Abstract: Magnetically shielded miniature Hall thrusters are disclosed that use a unique magnetic field topology that prevents the magnetic field lines from intersecting the discharge channel walls in the acceleration region of the thruster. Instead, the lines of force originating from both the inner and outer pole pieces curve around the downstream edges of the discharge channel and follow the channel walls towards the anode. This unique field topology results in low electron temperature at the discharge channel walls while eliminating strong electric field components that would otherwise lead to high erosion rates and power deposition from ion acceleration into the channel walls.

Abstract: A chemical-electromagnetic hybrid propeller with variable specific impulse. Fuel gas ejected out from a spraying tube of the chemical propeller through chemical propulsion enters an ionization chamber through a first magnetic mirror tube for ionization. The fuel gas after ionization is heated up by radio-frequency ion cyclotron waves in an ion cyclotron wave heating chamber so as to improve the kinetic energy. Then a second magnetic mirror tube is used, so that ions in the fuel gas after the ionization are heated up many times in a reciprocating manner between the magnetic mirror tubes, and ejected to generate forward propulsion force. By means of the propeller, the propulsion force and the specific impulse are greatly increased.

Abstract: An electric thruster includes at least one electric engine, a feed system for the engine including a high-pressure tank of ionizable gas, a low-pressure buffer tank connected to the high-pressure tank by a valve, and a system of pipes for conveying the gas from the low-pressure buffer tank to an anode and to a cathode of the engine. The low-pressure buffer tank is in open connection with the engine. The thruster detects that a magnitude of the discharge current between the anode and the cathode is less than a threshold value and switches off the discharge voltage as a result of the detection. The thruster can be for use in a satellite.

Abstract: A magnetically enhanced micro-cathode thruster assembly provides long-lasting thrust. The micro-cathode thruster assembly includes a tubular housing, a tubular cathode, an insulator, an anode and a magnetic field. The tubular housing includes an open distal end. The tubular cathode is housed within the housing and includes a distal end positioned proximate the open distal end of the housing. The insulator is in contact with the cathode forming an external cathode-insulator interface. The anode is housed within the housing, proximate the open distal end of the housing. The magnetic field is positioned at or about the external cathode-insulator interface and has magnetic field lines with an incidence angle of about 20 to about 30 degrees and preferably about 30 degrees relative to the external cathode-insulator interface.

Abstract: Systems and methods are described for increasing the burn efficiency of fuel in a jet engine by charging the intake air molecules and inversely charging the fuel molecules, while reducing the fuel droplet size using a fuel-atomizing transducer in the air/fuel path. Generally speaking, an apparatus (and method) for increasing fuel burning efficiency in a jet engine is described, comprising: an intake air high voltage charger; a fuel injector downstream of the intake air charger; a fuel atomizer formed from an acutely angled transducer in a flow path of the fuel, wherein the atomized fuel is charged to an opposite voltage to that of the intake air; and an ignitor for igniting the atomized charged fuel and charged intake air for combustion.

Abstract: The invention relates to a surface section that is exposed to an ion flow, in particular for a drive arrangement in a spacecraft, comprising an electrostatic ion accelerator arrangement. According to the invention, in order to reduce erosion, an intermediate potential energy surface is provided, the surface being advantageous in that it allows a magnetic field that is essentially parallel to the surface section to be formed.

Abstract: The invention, which relates to a miniaturisable plasma thruster, consists of: —igniting the plasma by microhollow cathode discharge close to the outlet and inside the means for injecting the propellant gas, said injection means being magnetic and comprising a tip at the downstream end thereof; —bringing the electrons of the magnetised plasma into gyromagnetic rotation, at the outlet end of said injection means; —sustaining the plasma by means of Electron Cyclotron Resonance (ECR), said injection means being metal and being used as an antenna for electromagnetic (EM) emission, the volume of ECR plasma at the outlet of said injection means being used as a resonant cavity of the EM wave; —accelerating the plasma in a magnetic nozzle by diamagnetic force, the ejected plasma being electrically neutral.

Abstract: At least one electrode assembly is configured to enable like charged ions to convert potential energy of the like charged ions into kinetic energy based on the Coulomb forces therebetween via linear alignment thereof, or enable a first portion of like charged ions to convert potential energy of the first portion of like charged ions to kinetic energy based on interaction with the Coulomb forces of a second portion of like charged ions, or enable a first portion of like charged ions to convert potential energy of a second portion of like charged ions to kinetic energy based on similar interaction. Various electrode assemblies are described and corresponding methods of converting potential energy of like charged ions to kinetic energy. The like charged ions are configured to form a passive electric field voltage source that may have one or more electric field monopoles to enable motion of a mobile assembly.

Abstract: A Hall effect thruster including a downstream end of its annular channel presenting a cross-section that is variable to vary a thrust and a specific impulse of the thruster.

Abstract: The present invention provides an inductively coupled plasma device with a cylindrical vessel having a first end and a second end, wherein at least a portion of the cylindrical vessel is transparent or semi-transparent to a wave energy. A tangential inlet is connected to or proximate to the first end. A tangential outlet is connected to or proximate to the second end. An electrode housing is connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, and (b) extends into the cylindrical vessel. A hollow electrode nozzle is connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel. An electromagnetic radiation source that produces a wave energy and is disposed around or within the cylindrical vessel.

Abstract: An electronic propulsion engine that creates a propulsive force or thrust using electromagnetic forces or electrostatic forces, with an effect that is similar to the thrust of a jet or rocket engine. Forces are generated using electromagnets or capacitor plates that are separated by dielectric spacer cores and are operated with two modulated currents. The two modulated currents are synchronized, but with a relative phase such that the forces on the two magnets or capacitor plates are not balanced. Included are techniques to reduce circuit impedance and control electric-magnetic field dispersion, such as tuned LCR circuits, dielectric core materials between the magnets or capacitor plates, and RF superconductors result in high propulsion efficiencies. The system operates at RF frequencies and can also be used as a communication device.

Abstract: A magnetically enhanced micro-cathode thruster assembly for providing long-lasting thrust is provided. The micro-cathode thruster assembly includes a tubular housing, a tubular cathode, an insulator, an anode and a magnetic field. The tubular housing includes an open distal end. The tubular cathode is housed within the housing and includes a distal end positioned proximate the open distal end of the housing. The insulator is in contact with the cathode forming an external cathode-insulator interface. The anode is housed within the housing, proximate the open distal end of the housing. The magnetic field is positioned at or about the external cathode-insulator interface and has magnetic field lines with an incidence angle of about 0 to about 90 degrees and preferably about 4 to about 30 degrees relative to the external cathode-insulator interface.

Abstract: A propulsion system for spacecraft is based on an electric engine that expels propellant to achieve thrust. The propellant is first ionized to generate a plasma. Plasma particles are selectively accelerated via a pulsed laser that accelerates predominantly the electrons in the plasma. The electrons are expelled first, forming a space charge that acts as a virtual cathode to accelerate the positive ions. Interactions between the laser beam and plasma electrons are predominantly through the ponderomotive force.

Abstract: An electrospray thruster and methods of manufacturing such thrusters are provided. The micro-electrospray thruster increases the thrust density of conventional electrospray thrusters by miniaturizing the individual components of the thruster thereby allowing for the increase in the number and density of the charged particle emitters.

Abstract: Pulsed plasma engine and method in which a noncombustible gas is introduced into an explosion chamber, the gas is ionized to form a plasma within the chamber, an electrical pulse is applied to the plasma to heat the plasma, the pulse is turned off to produce an explosive pressure pulse in the plasma, and the plasma is confined in the chamber by a magnetic field that directs the pressure pulse toward an output member which is driven by the pressure pulse.

Abstract: A steerable-thrust Hall effect thruster in which a final stage of a magnetic circuit includes an inner pole and a facing outer pole, the inner pole being offset axially downstream relative to the outer pole, so that a magnetic field is inclined relative to a transverse plane of the thruster.

Abstract: The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, and (b) extends into the cylindrical vessel, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle create a plasma that discharges through the hollow electrode nozzle.

Abstract: The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, and (b) extends into the cylindrical vessel, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle create a plasma that discharges through the hollow electrode nozzle.

Abstract: An electron acceleration device using thermionic fission cells and an electromagnetic scoop coil for power. A power control junction and electron injector control that feeds free electrons in packets into the acceleration components that consist of a series of induction linac module units, having quadrupole magnet units in series between the induction module units. Has on-board xenon gas for a deep space electron source. At the high speed electrons exit from the device, deflector plates control the exit path of the electrons to direct the course of a craft.

Abstract: An electric propulsion system includes a first stationary plasma thruster including a single first cathode, a first anode, and a first gas manifold, and a second stationary plasma thruster including a single second cathode, a second anode, and a second gas manifold. The system further includes an electrical connection device common to the first and second cathodes, first and second gas flow rate control devices with a common fluid flow device for feeding gas, and a selective control device for activating at any given instant only one of the first and second cathodes in co-operation with one or the other of the first and second anodes.

Abstract: A plasma micro-thruster, including: an elongate and substantially non-conductive tube having a first end to receive a supply of propellant gas, and an open second end to act as an exhaust; first, second, and third electrodes extending circumferentially around the tube and being mutually spaced along a longitudinal axis of the tube, the third electrode being longitudinally interposed between the first and second electrodes; wherein the tube and the first, second and third electrodes are configured to generate a plasma from propellant gas flowing though the tube from the first end of the tube when the third electrode receives radio frequency power and the first and second electrodes are electrically grounded relative to the third electrode, such that the expansion of the plasma from the open end of the tube generates a corresponding thrust.

Abstract: A plasma generator having a housing surrounding an ionization chamber, at least one working-fluid supply line leading into the ionization chamber, the ionization chamber having at least one outlet opening, at least one electric coil arrangement which surrounds at least one area of the ionization chamber, the coil arrangement being electrically connected with a high-frequency alternating-current source (AC) which is constructed such that it applies a high-frequency electric alternating current to at least one coil of the coil arrangement, is wherein a further current source (DC) is provided which is constructed such that it applies a direct voltage or an alternating voltage of a frequency lower than that of the voltage supplied by the high-frequency alternating current source (AC) to at least one coil of the coil arrangement.

Abstract: The invention relates to an electric thruster for a spacecraft. According to the invention, the thruster (II) comprises a jet generating portion (G1) and a jet accelerating portion (A2), pivotably connected (H1) such that the jet accelerating portion (A2) can rotate in relation to the jet generating portion (G1).

Abstract: A gridded ion propulsion system comprising two power controllers, four ion thrusters, and two switch assemblies. One switch assembly is connected to the two power controllers and to two of the four ion thrusters. The other switch assembly is connected to the two power controllers and to the other two ion thrusters. Each switch assembly has first and second switching states which can be selected to enable either power controller to supply power to any one of the four ion thrusters. Each switch assembly comprises a respective movable body and a respective multiplicity of switches which change state in unison when the movable body changes position. For example, the movable body may be a rotatable hollow shaft driven by a stepper motor.

Abstract: A turbine engine includes an air inlet fluidly coupleable with an air compressor subassembly. The air compressor subassembly is fluidly coupleable with a combustion subassembly. The combustion subassembly generates and combusts ionic hydrogen, and is fluidly coupleable with a mid-turbine subassembly. The mid-turbine subassembly is fluidly coupleable with a rear turbine subassembly. The rear turbine subassembly is fluidly coupleable with an exhaust outlet for exhausting combustion products from said mid-turbine subassembly. The combustion subassembly includes an electrostatic subassembly fluidly coupleable with a combustion chamber subassembly. The combustion chamber subassembly is fluidly coupleable with the mid-turbine subassembly. The air compressor subassembly can compress and humidify air.

Abstract: Thruster grid clear circuits and methods to clear thruster grids are disclosed. An example apparatus includes a low voltage grid clear circuit to apply first energy to a grid at a first voltage, and a high voltage grid clear circuit to detect a failure of the applied energy to clear a short circuit condition of the grid and to apply second energy to the grid at a second voltage higher than the first voltage.

Abstract: The invention relates to the field of Hall effect thrusters. The invention provides a Hall effect thruster having a discharge channel of annular shape extending along an axis, the discharge channel being defined by an outer wall of annular shape and an inner wall of annular shape situated inside the space defined by the outer wall, a cathode situated outside the discharge channel, and an injector system situated at the upstream end of the discharge channel and also forming an anode, the downstream end of the discharge channel being open, wherein the thruster includes a heat sink device comprising a heat sink in contact with the inner wall and of thermal conductivity that is greater than the thermal conductivity of the inner wall, the heat sink being a sleeve and the heat sink device being suitable for discharging heat from the inner wall to the outside of the thruster so as to reduce the temperature difference between the inner wall and the outer wall.

Abstract: A Hall effect plasma thruster including an annular discharge channel around a main axis presenting an open downstream end and defined between an inner wall and an outer wall, at least one cathode, a magnetic circuit for creating a magnetic field in the channel, a pipe for feeding ionizable gas to the channel, an anode, and a manifold placed in the upstream end of the channel. The manifold is connected to the pipe and enables the ionizable gas to flow into the ionization zone of the channel in concentric manner around the main axis. The anode acts as a manifold, and the manifold includes a directional mechanism that gives rise at an outlet from the manifold to swirling motion of the gas around the main axis.

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 Hall effect thruster includes at least one tank of gas under high pressure, a pressure regulator module, a gas flow rate control device, an ionization channel, a cathode placed in a vicinity of an outlet from the ionization channel, an anode associated with the ionization channel, an electrical power supply unit, an electric filter, coils for creating a magnetic field around the ionization channel, and an additional electrical power supply unit for applying a pulsating voltage between the anode and the cathode.

Abstract: A system and a method of generating energy in a power plant using a turbine are provided. The system includes an air separation unit providing an oxygen output; a plasma generator that is capable of generating plasma; and a combustor configured to receive oxygen and to combust a fuel stream in the presence of the plasma, so as to maintain a stable flame, generating an exhaust gas. The system can further include a water condensation system, fluidly-coupled to the combustor, that is capable of producing a high-content carbon dioxide stream that is substantially free of oxygen. The method of generating energy in a power plant includes the steps of operating an air separation unit to separate oxygen from air, combusting a fuel stream in a combustor in the presence of oxygen, and generating an exhaust gas from the combustion. The exhaust gas can be used in a turbine to generate electricity. A plasma is generated inside the combustor, and a stable flame is maintained in the combustor.

Abstract: A Hall thruster apparatus having walls constructed from a conductive material, such as graphite, and having magnetic shielding of the walls from the ionized plasma has been demonstrated to operate with nearly the same efficiency as a conventional non-magnetically shielded design using insulators as wall components. The new design is believed to provide the potential of higher power and uniform operation over the operating life of a thruster device.

Abstract: A vehicle propulsion system comprises a propellant source, a microwave energy source; an ionizer, a heater, and a propellant accelerator. The ionizer is configured for receiving propellant and for also receiving microwave energy from the microwave energy source so as to produce ionized propellant. The heater comprises a heater shell that defines a plasma heating cavity and is configured for receiving the ionized propellant from the ionizer. The heater shell is configured to transmit microwave energy received from the microwave energy source to the ionized propellant in the plasma heating cavity and to thereby facilitate absorption of microwave energy by the ionized propellant to produce heated ionized propellant. The propellant accelerator is configured for receiving the heated ionized propellant from the heater, accelerating the heated ionized propellant to produce accelerated propellant, and expelling the accelerated propellant in a desired direction to impose a reaction force (i.e.

Abstract: An electron cyclotron resonance (ECR) thruster is disclosed having a plasma chamber which is electrically biased with a positive voltage. The chamber bias serves to efficiently accelerate and expel the positive ions from the chamber. Electrons follow the exiting ions, serving to provide an electrically neutral exhaust plume. In a further embodiment, a downstream shaping magnetic field serves to further accelerate and/or shape the exhaust plume.

Abstract: Some embodiments provide a dual use hydrazine propulsion thruster system. The dual use hydrazine propulsion thruster system may include a storage vessel configured to store hydrazine and a chemical thruster configured to provide thrust using the hydrazine. The dual use hydrazine propulsion thruster system may also include a convertor configured to catalytically convert hydrazine to a product comprising ammonia, and an electric thruster configured to provide thrust by ionizing ammonia and accelerating the ionized ammonia out of the electric thruster.

Abstract: To explore deeper expanses of space, rocket ships need rockets that can last twice as long as conventional rockets. Modern rockets use the electric field to attract and accelerate charged particles out and away from the combustion chamber. Space qualified components to increase the electric field are difficult to obtain. Various embodiments of the present subject matter use multiple phases of an input signal into the power supply to cause the output DC voltage signal to be substantially smooth. These smoother signals reduce the voltage requirements of the output diodes and capacitors thereby making them easier to obtain.

Abstract: An electric thruster includes at least one electric engine, a feed system for the engine including a high-pressure tank of ionizable gas, a low-pressure buffer tank connected to the high-pressure tank by a valve, and a system of pipes for conveying the gas from the low-pressure buffer tank to an anode and to a cathode of the engine. The low-pressure buffer tank is in open connection with the engine. The thruster detects that a magnitude of the discharge current between the anode and the cathode is less than a threshold value and switches off the discharge voltage as a result of the detection.

Abstract: A plasma propulsion nozzle incorporates a cylinder having an inlet and an outlet. A plurality of substantially cylindrical planarly disbanded electrodes with sandwiched dielectric spacers is cascaded in an array to be concentrically expanding from the inlet through an interior chamber to the outlet for a nozzle. A voltage source applies a periodic signal with rapidly reversing polarity to the electrodes with differential phase applied to adjacent electrodes in the array creating and expelling plasma clusters at each dielectric spacer inducing flow from the nozzle outlet to produce thrust.

Abstract: An electric propulsion machine includes an ion thruster having an annular discharge chamber housing an anode having a large surface area. The ion thruster includes flat annular ion optics with a small span to gap ratio. Optionally, a second electric propulsion thruster may be disposed in a cylindrical space disposed within an interior of the annulus.

Abstract: An electronic propulsion engine that creates a propulsive force or thrust using electromagnetic forces or electrostatic forces, with an effect that is similar to the thrust of a jet or rocket engine. Forces are generated using electromagnets or capacitor plates that are separated by dielectric spacer cores and are operated with two modulated currents. The two modulated currents are synchronized, but with a relative phase such that the forces on the two magnets or capacitor plates are not balanced. Included are techniques to reduce circuit impedance and control electric-magnetic field dispersion, such as tuned LCR circuits, dielectric core materials between the magnets or capacitor plates, and RF superconductors result in high propulsion efficiencies. The system operates at RF frequencies and can also be used as a communication device.

Abstract: There is disclosed a field emission electric propulsion (FEEP) system including a FEEP thruster having at least one emitter and an extractor electrode, and a power supply. The power supply may provide an extractor voltage applied between the emitter and the extractor electrode. The power supply may be operable in a constant current mode in which the extractor voltage is controlled to set an ion current flowing from the emitter at a target current level.

Abstract: A nano-particle field extraction system comprising a grid having a plurality of electrodes each defining an electrical field, wherein the grid has a plurality of vias extending therethrough. The system further comprises a reservoir having a generally dry mixture disposed therein, a plurality of particles suspended in the generally dry mixture, a biasing member applying a biasing force to the generally dry mixture in the reservoir, and a sieve electrode system in electrical communication with the grid. The sieve electrode system has a plurality of through-holes extending from the reservoir to the grid, such that the sieve electrode system cooperates with the biasing member to extract at least one particle from the generally dry mixture and into the grid whereby the electrical fields charge and accelerate the particle in the vias.

Abstract: An electrospray source useful for a variety of applications and including an emitter with a porous media flow distributor having a surface forming multiple Taylor cones. A casing about the porous media flow distributor controls the direction of a working fluid through the porous media. An extractor is at a potential different than the emitter for forming the Taylor cones. A guard electrode is disposed between the emitter and the extractor and is at or above the potential of the emitter for shaping the electric field formed between the emitter and the extractor.

Abstract: A Hall effect thruster including: a discharge channel with an open downstream end; a cathode situated outside the discharge channel; an injector system configured to inject atoms of gas into the discharge channel, the injector system situated at an upstream end of the discharge channel and also forming a cathode; a heater device configured to heat the cathode; a measurement mechanism measuring temperature of the heater device, and a regulator circuit regulating the temperature such that the heater device heats so long as its temperature is less than a threshold temperature from which the thruster is capable of starting, and ceases to heat shortly after the threshold temperature has been reached.

Abstract: The invention is a Hall thruster that incorporates a discharge chamber having a variable area channel including an ionization zone, a transition region, and an acceleration zone. The variable area channel is wider through the acceleration zone than through the ionization zone. An anode is located in a vicinity of the ionization zone and a cathode is located in a vicinity of the acceleration zone. The Hall thruster includes a magnetic circuit which is capable of forming a local magnetic field having a curvature within the transition region of the variable area channel whereby the transition region conforms to the curvature of the local magnetic field. The Hall thruster optimizes the ionization and acceleration efficiencies by the combined effects of the variable area channel and magnetic conformity.

Abstract: A thruster (1) has a main chamber (6) defined within a tube (2). The tube has a longitudinal axis which defines an axis (4) of thrust; an injector (8) injects ionizable gas within the tube, at one end of the main chamber. An ionizer (124) is adapted to ionize the injected gas within the main chamber (6). A first magnetic field generator (12, 14) and an electromagnetic field generator (18) are adapted to generate a magnetized ponderomotive accelerating field downstream of said ionizer (124) along the direction of thrust on said axis (4). The thruster (1) ionizes the gas, and subsequently accelerates both electrons and ions by the magnetized ponderomotive force.

Abstract: A spacecraft propulsion system has at least one chemical thruster, at least one electric thruster, a propellant supply arrangement that stores a propellant and a propellant conditioning arrangement configured to convert propellant into chemical species in a thermodynamic phase that can be readily ionized. The propellant is commonly supplied from the propellant storage device to each of the chemical thruster and the electric thruster. The chemical thruster has a gas generator and a high thrust accelerator; the electric thruster has a plasma generator and a high specific impulse accelerator. The propellant supply arrangement is configured to control flow of the propellant from the propellant supply arrangement to the gas generator and the propellant conditioning arrangement, and a first flow path connects propellant supply arrangement with the gas generator, and a second flow path connects propellant supply arrangement with the plasma generator.

Abstract: An emitter for an ion thruster. The emitter is a field-effect emitter for a field emission electric propulsion or colloid thruster. The field-effect emitter has a first and second portions defining an internal reservoir for supplying a liquid metal or a conducting ionic liquid and has a slit connecting the internal reservoir to an exit orifice.