Abstract: A fiber laser powered, optical to thermal conversion thruster with improved practicality and operational and design flexibility.

Abstract: A nozzle arrangement for use in a gas thruster is presented. At least one heater micro structure (20) is arranged in a stagnation chamber (12) of the gas thruster. The heater microstructure (20) comprises a core of silicon or a silicon compound coated by a surface metal or metal compound coating. The heater microstructure (20) is manufactured in silicon or a silicon compound and covered by a surface metal coating. The heater microstructure (20) is mounted in the stagnation chamber (12) before or after the coverage of the surface metal or metal compound coating. The coverage is performed by heating the heater microstructure and flowing a gas comprising low quantities of a metal compound. The compound decomposes at the heated heater microstructure (20), forming the surface metal or metal compound coating. The same principles of coating can be used for repairing the heater microstructure (20) in situ.

Abstract: In a propulsion system, an electrohydrodynamic (EHD) body force is used to control the flow of a propellant through a micro channel, expansion slot, plenum chamber, or other flow region and thereby increase the specific impulse created by a propulsion system. In an embodiment, a plurality of electrodes are arranged and powered to create a plasma discharge, which can impart an EHD body force to a fluid. Various configurations of electrodes can be used to control the flow of the fluid into, out of, or through the flow region. In an embodiment, the use of EHD body forces can reduce, or substantially eliminate, shear forces on the surface of a plenum chamber, micro channel, or expansion slot of the propulsion system, resulting in a smooth flow of the propellant and increased thrust.

Abstract: At least one exemplary embodiment is directed to a propulsion device that ionizes a portion of a medium and ExB drifts the ionized portion providing thrust where the ionized portion is created using high pressure field emitters comprising: a substrate layer; a gate layer; a field emitter tip; and a cover layer, wherein the field emitter tip is configured to emit electrons in a region when there is a potential difference between the gate layer and the field emitter tip, where the cover layer separates an ambient environment at a pressure from the region, and where a substantial portion of the electrons pass through the cover layer.

Abstract: A gas turbine engine including an electrical assembly operable as at least one of an electric motor and a generator, with an electromagnetic rotor formed in part by a portion of one of a main shaft concentrically and drivingly connected to at least one turbine rotor and a tower shaft directly driven by the main shaft and extending generally radially therefrom.

Abstract: A plasma thruster includes a plasma chamber having first and second axial ends, the first of which is open, an anode located at the second axial end, and a cathode. The cathode and anode are arranged to produce an electric field having at least a component in the axial direction of the thruster. A magnet system including a plurality of magnets is spaced around the thruster axis, each magnet having its north and south poles spaced around the axis.

Abstract: A standard 4-pole electric motor stator with capacitive plates in-line with the magnetic poles, but electrically 90° out of phase, produces two Lorentz force geometries 90° out of phase with each other (i.e., vertical, horizontal). An alternating source electrically rotates this pair of Lorentz geometries producing a propagating electromagnetic wave at the source frequency within the vacant internal cavity. Any charged particle within the cavity and along its axis will be accelerated or decelerated from an initial velocity via the Lorentz force. The rotating geometry provides for the coupling of the Lorentz force through a current loop and diamagnetism, providing acceleration and deceleration of non-charged particles. The force coupling is dependent upon the material's electromagnetic properties, the frequencies generated by the capacitive stator, and the velocity of the particles within the capacitive stator's influence.

Abstract: This invention relates to absolute universal engine for aviation, from ground to orbit and space, by total integration of all modes of operation, turbo fan subsonic, turbo jets supersonic, turbo air ram rockets, and turbo space rockets, <<<One Engine From Ground to Orbit>>>

Abstract: A system and method are provided to control hydronic systems having a plurality of sources, including at least one of an on-demand source, a semi-on-demand source, and an intermittent source that are fluidly or thermally coupled to a plurality of load zones. The hydronic system device obtains performance measurements for system components to provide system metrics, including failure diagnostics, energy capture, and usage optimization. The hydronic system device may also calculate British Thermal Units produced and used by the plurality of sources and loads to calculate incentives, including renewable energy credits.

Abstract: An electrostatic colloid thruster for implementing a method of ionizing a liquid is disclosed herein. The electrostatic colloid thruster includes an electrically conductive extractor having a plurality of holes defined therethrough; an ultrasonic atomizer having an electrically conductive atomization surface at least partially facing the extractor and being arranged relative thereto so as to define a gap; a reservoir system in fluid communication with the atomization surface; and an electrical power source in electrical communication with both the extractor and the atomization surface. The apparatus and method are generally utile in various applications including, for example, spacecraft propulsion, paint spray techniques, semiconductor fabrication, biomedical processes, and the like.

Abstract: A gas turbine engine including a first shaft being one of a main shaft concentrically mounted to at least one turbine rotor and a tower shaft directly driven by the main shaft and extending generally radially therefrom, the first shaft having a reduced diameter portion located within the gas turbine engine, an electrical assembly having a rotor comprising permanent magnets retained on an outer surface of the reduced diameter portion and a stator comprising a magnetic field circuit disposed adjacent an outer periphery of the rotor, and an electrical connection between the magnetic field circuit and at least one of a power source and an electrically drivable accessory.

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, (b) extends into the cylindrical vessel, and (c) can be moved along the longitudinal axis, 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 creates a plasma that discharges through the hollow electrode nozzle.

Abstract: A system and method are provided to control hydronic systems having a plurality of sources, including at least one of an on-demand source, a semi-on-demand source, and an intermittent source that are fluidly or thermally coupled to a plurality of load zones. The hydronic system device obtains performance measurements for system components to provide system metrics, including failure diagnostics, energy capture, and usage optimization. The hydronic system device may also calculate British Thermal Units produced and used by the plurality of sources and loads to calculate incentives, including renewable energy credits.

Abstract: In order to make a drive device available on the basis of a gel-type propellant, in particular, for a flying object, comprising at least one tank for gel-type propellant, a combustion chamber and a device for supplying propellant to the combustion chamber, which is of a simple construction it is suggested that at least one radiation impinging device be provided for acting on gel-type propellant with electromagnetic radiation and/or at least one heating device for heating gel-type propellant in order to improve the flow behavior.

Abstract: A multi-functional power supply system for a Hall thruster including a thruster assembly for providing a plasma discharge and a cathode assembly for providing electrons. The cathode assembly includes an emitter, a keeper with a current limiting device, and a heater. A magnetic field source is operatively associated with the cathode assembly for generating a magnetic field to control the discharge. A plasma discharge circuit creates a plasma and accelerates the plasma to produce thrust. A power supply is connected to the keeper and the plasma discharge circuit and is connected to the heater through a switching device responsive to a predetermined condition for interrupting the power to the heater and simultaneously enabling the power supply to deliver power to the keeper and the plasma discharge circuit to initiate production of thrust.

Abstract: This invention relates to a nuclear fusion reaction process utilizing a B-11 isotope ion spherical plasma. Said spherical plasma will be formed on roof of a ferromagnetic chromium steel hulled aircraft, utilizing two larger magnesium based aircraft. Said spherical plasma is formed by raising a pyramid shaped device with a slotted glass ball electrode on top, on roofs of said air-craft. Only the smaller craft will utilize the fusion fuels, B-11 isotope ion and H-1 atom, in forming said spherical plasmas. The two larger craft will apply pressure toward smaller craft, and coalesce their plasmas into the smaller plasma. By forming this induced magnetic field, an electron current existing in larger applied magnetic field, is raised to middle of smaller aircraft spherical plasma. Ignition can be accomplished with land based neutral beam, FIG. 15. Produced energetic charged particles, electric energy, can be stored within craft plasma vortices and beamed to power stations.

Abstract: A system and method are provided to control hydronic systems having a plurality of on-demand sources, semi-on-demand sources, and intermittent sources that are fluidly or thermally coupled to a plurality of load zones. The hydronic system device obtains performance measurements for system components to provide system metrics, including failure diagnostics, energy capture, and usage optimization. The hydronic system device may also calculate British Thermal Units produced and used by the plurality of sources and loads to calculate incentives, including renewable energy credits.

Abstract: A coil system for a plasmoid thruster includes a bias coil, a drive coil and field coils. The bias and drive coils are interleaved with one another as they are helically wound about a conical region. A first field coil defines a first passage at one end of the conical region, and is connected in series with the bias coil. A second field coil defines a second passage at an opposing end of the conical region, and is connected in series with the bias coil.

Abstract: Systems and methods are disclosed related to utilization of energy including utilization of latent energy from electricity generating processes. According to one exemplary implementation, steam is produced from thermal energy, such as fossil fuel energy, nuclear energy and solar thermal energy; generating electricity from the steam using a turbine; and directing steam exhausted from the turbine to an absorption chiller or desalination apparatus as a condenser to drive an industrial process therein. In one exemplary implementation the absorption chiller may be an atmospheric control system to produce a gas of a desired temperature such as in an air-conditioning system. In another exemplary implementation the heat exchange apparatus is a desalination system employed to produce water of a desired purity.

Abstract: The invention concerns an electrothermal thruster (1) comprising a heating section (20) through which a propellant fluid (4) is intended to pass so that it is heated before it is exhausted, the heating section (20) being supplied by an electric power source (22). According to the invention, the electric power source (22) comprises photovoltaic cells (24) mounted on the heat exchanger (10) through which the propellant fluid (4) is intended to pass before it reaches the heating section (20). Application to the area of spacecraft propulsion.

Abstract: Spacecraft thrusters capable of dual-mode operation, and a method of applying propulsion to a spacecraft using a dual-mode thruster are provided. In one embodiment, the thrusters of the current invention can operate as a chemical motor to provide high thrust and low propellant exhaust velocity to achieve fast maneuverability, or as an electric propulsion thruster to provide low thrust and high exhaust velocity to perform maneuvers with a minimal amount of propellant.

Abstract: A modular propulsion system includes an array of micromachined field effect electrostatic propulsion devices, each of which is an assembled micromachined device including an array of field effect electrostatic propulsion thrusters, a fuel container of propellant using passive plumbing, electronic power and command controls, with the array of devices disposed about and on a surface of a spacecraft for providing diverse propulsion needs.

Abstract: Coaxial micronozzle designs are presented. Initial coaxial micronozzle designs utilizing center-body geometries to better exploit pressure thrust show a potential threefold increase in specific impulse under vacuum and near vacuum conditions.

Abstract: A thruster for exo-atmospheric vehicles with electro-thermal thrust augmentation and having internally embedded heating elements for direct contact heating of gaseous products released by a propellant, particularly hydrazine, so as to increase the Specific Impulse (Isp) of the thruster. The electrical heating elements are resistant to hydrazine products. The thruster is configured as a closed sealed chamber divided into a decomposition section upstream and a heating section downstream. At least one heating element is disposed in the heating section, directly in a mixture catalyst forming a porous bed, or within a concentric ceramic tube operative as a heat exchanger, to heat the gaseous products by direct contact. The heater indirectly heats the catalyst in the decomposition section and directly heats the heating section. The thruster is operable both in space and at sea-level gravity and barometric pressure.

Abstract: A pulsed plasma thruster and method of operation are provided. The pulsed plasma thruster comprises solid propellant material. A main discharge source provides a pulsed discharge across the propellant material for ablating the propellant material to produce propellant plasma and accelerating the ablated propellant plasma, and an auxiliary discharge source accelerates late ablated propellant plasma without substantially further ablating the propellant material.

Abstract: A method, device, and projectile having a device for guiding or piloting projectiles or missiles (self-propelled or non-self-propelled), to deflect, in a direction Y, a hypervelocity projectile operating in a gas, such as a shell, a bullet, or a missile, having a nose, generally in the shape of a cone, with a more or less pointed tip, by generating a first high-voltage discharge able to produce a plasma over a first limited sector of the projectile surface and in direction Y, maintaining the plasma, and generating another low-voltage discharge able to supply the plasma with energy over a second limited sector of the projectile surface and in direction Y, the first and the second sectors being different and may overlap.

Abstract: In order to make a drive device available on the basis of a gel-type propellant, in particular, for a flying object, comprising at least one tank for gel-type propellant, a combustion chamber and a device for supplying propellant to the combustion chamber, which is of a simple construction it is suggested that at least one radiation impinging device be provided for acting on gel-type propellant with electromagnetic radiation and/or at least one heating device for heating gel-type propellant in order to improve the flow behavior

Abstract: A plasma thruster having a magnetic circuit of a downstream bottom plate from which arms protrude. At least one of the arms includes a permanent magnet. The mass, overall dimensions, electricity consumption, and cost of the thruster are thereby reduced.

Abstract: The proposed technology is a rocket engine cycle utilizing as the propulsive fluid a low molecular weight, cryogenic fluid, typically liquid hydrogen, pressure driven, heated, and expelled through a nozzle to generate high velocity and high specific impulse discharge gas. The proposed technology feeds the propellant through the engine cycle without the use of a separate pressurization fluid and without the use of turbomachinery. Advantages of the proposed technology are found in those elements of state-of-the-art systems that it avoids. It does not require a separate pressurization fluid or a thick-walled primary propellant tank as is typically required for a classical pressure-fed system. Further, it does not require the acceptance of intrinsic reliability risks associated with the use of turbomachinery.

Abstract: Microthruster includes a combustion chamber comprising a substrate material, a fuel inlet, and a gas outlet. A first resistance heater is arranged in the combustion chamber. A catalyst is structured and arranged to decompose fuel entering the combustion chamber. First substrate material sections are heated by the first resistance heater to at least one of a predetermined temperature and a predetermined temperature range. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.

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 (PPT) and a method of making the PPT are disclosed. The PPT includes no moving parts and can be made in a small size. The PPT can achieve long operating duration by using vapor as a fuel. Liquid used to form the vapor can be easily stored and can provide an ample supply of vapor. The PPT is also designed to facilitate easy and rapid manufacture. The process for making the PPT uses known techniques for making printed circuit board devices.

Abstract: An electric propulsion device is disclosed having an anode and a cathode. The propulsion device includes a discharge annulus having the anode adjacent an end region thereof. At least one inlet aperture is adjacent the anode, the aperture(s) having propellant gas flow therethrough into the discharge annulus. The propellant gas has an ionization potential. Opposed, dielectric walls define the annulus, with at least one of the opposed dielectric walls having pores therein, the pores having cooling gas flow therethrough into the discharge annulus and substantially adjacent the opposed dielectric wall(s). The cooling gas has an ionization potential higher than the ionization energy of the propellant gas. The cooling gas is adapted to substantially prevent at least one of secondary electron emission and sputtering of the dielectric walls.

Abstract: A solar energy augmented jet aircraft uses solar energy as the energy source for dielectric heating of a jet engine exhaust gas stream thereby increasing thrust.

Abstract: A pulsed plasma thruster (PPT) and a method of making the PPT are disclosed. The PPT includes no moving parts and can be made in a small size. The PPT can achieve long operating duration by using vapor as a fuel. Liquid used to form the vapor can be easily stored and can provide an ample supply of vapor. The PPT is also designed to facilitate easy and rapid manufacture. The process for making the PPT uses known techniques for making printed circuit board devices.

Abstract: A pulsed plasma thruster (PPT) and a method of making the pulsed plasma thruster are disclosed. The PPT includes no moving parts and is able to achieve a small size. The PPT is also designed to facilitate easy and rapid manufacture. The process for making the PPT uses known techniques for making printed circuit board devices. Another PPT also has no moving parts and uses a liquid fuel that is progressively advanced by capillary action.

Abstract: A heat transfer thruster by which performance can be enhanced by realizing optimal temperature distribution for heating propellant without complicating the structure. In the heat transfer thruster, propellant flows through two pipes (102, 104) into the thruster body (106) thence flows through a channel (110) formed in the thruster body (106) to the nozzle side while being heated from the thruster body (106) which is heated by a heat source, and reaches a plenum chamber (114) in front of a nozzle before being injected from a propellant outlet along the outer wall (126) of a plug nozzle (112). Heat from the heat source is transmitted directly to the nozzle through the inner wall (128) of the plug nozzle (112). In other words, the hollow section (118) of the plug nozzle (112) functions as a heating section for the nozzle.

Abstract: A modular propulsion system includes an array of micromachined field effect electrostatic propulsion devices, each of which is an assembled micromachined device including an array of field effect electrostatic propulsion thrusters, a fuel container of propellant using passive plumbing, electronic power and command controls, with the array of devices disposed about and on a surface of a spacecraft for providing diverse propulsion needs.

Abstract: A pulsed plasma thruster (PPT) and a method of making the pulsed plasma thruster are disclosed. The PPT includes no moving parts and is able to achieve a small size. The PPT is also designed to facilitate easy and rapid manufacture. The process for making the PPT uses known techniques for making printed circuit board devices. Another PPT also has no moving parts and uses a liquid fuel that is progressively advanced by capillary action.

Abstract: Systems, methods and computer program products provide secure access to real-time emissions data from one or more power generating plants via a web-based interface. The user provides log-in information to gain a predefined level of access based on the inputted log-in information, and may access emissions data of one or more power generating plants located remotely with respect to the user. The user can utilize any suitable computing device with a suitable browser application to access the emissions data. Accordingly, the system is highly scalable, in both users and power generating plants being monitored.

Abstract: A system and method for supplying thrust to a structure, such as a satellite or spacecraft, for the purposes of station keeping and attitude control of the structure in low-gravity (orbital) and zero-gravity environments. The system includes devices for emitting energy beams and targets impacted by the energy beams to cause ablation of the targets. The beam-emitting devices and targets are adapted to cooperate and cause the structure to selectively undergo translational and/or rotational motion in reaction to the motion of material ablated from the targets. The position, alignment, and/or attitude of the structure can thereby be controlled in a zero or low-gravity environment by selectively emitting the energy beams at the targets.

Abstract: A plasma impulse device/method has been developed to provide impulses that can be used for thrust. A field device produces electric and magnetic fields, which E×B drifts a charged portion in the ambient environment, resulting in thrust of the field device.

Abstract: The invention is a turbojet propulsion system which includes a compressor section, a turbine section coupled by a shaft to the compressor section, a combustion section mounted between the compressor section and the turbine section, and an exhaust duct coupled to the aft end of said turbine section. A fuel delivery system is incorporated for supplying fuel to the combustion section. A laser assembly provides electromagnetic radiation to the combustion section. An electrical generator coupled to the turbine driven shaft powers the laser assembly.

Abstract: An apparatus for generating electricity that uses at least one jet-type engine fueled with fissile material. The nuclear fueled jet engine is affixed to a connecting member that projects from a central, rotatable shaft, which is in engageable communication with an apparatus for converting the rotation of the central shaft to electricity, such as a stator and rotor combination. The engine is positioned so that the thrust produced by the jet engine causes the engine and connecting member to travel in a radial direction around the longitudinal axis of the central shaft, rotating the central shaft. As the central shaft rotates, the rotational motion of the central shaft is transmitted to conversion apparatus. An operating gas is used to cool the nuclear fueled jet engines and as the propellant for the jet engines.

Abstract: A thruster for use with an external power supply. The thruster includes a propellant that exists in a non-gaseous state at standard temperature and pressure and has a melting point Tm, a boiling point Tb, and an evaporation rate. The thruster further includes a reservoir adapted to house the propellant and selectively heated to a temperature greater than Tm and less than Tb, and a power control mechanism positioned to control the amount of power from the external power supply being deposited into the reservoir to control the evaporation rate of the propellant.

Abstract: A thruster device and associated methods are provided. The thruster device comprises a frustoconical inner layer and a frustoconical outer layer that surrounds the inner layer such that the inner and outer layers cooperate to define a spiral flow passage therebetween. An outlet, such as a nozzle, is attached to an exit end of the thruster device such that the outlet is in fluid communication with the spiral flow passage. In one embodiment, the thruster device includes an end flow cap that is also attached to the exit end and establishes the fluid communication between the spiral flow passage and the outlet. The end flow cap includes at least one channel for directing the propellant from the spiral flow passage to the outlet. The design of the thruster device allows the frustoconical inner and outer layers to be assembled without galling or damaging the spiral flow passage.

Abstract: A device and method for guiding or steering projectiles (self-propelled or non-self-propelled), or missiles, and for steering a supersonic projectile, or a missile, having a nose, generally in the shape of a cone, having a more or less pointed end, and capable of creating a plasma discharge near the end of the projectile over a limited sector of the outer surface of nose.

Abstract: A propulsion system is disclosed that uses microwaves originating from a ground-based or on-board source to provide energy for propulsion. The energy produces thrust by coupling into a propellant via a microwave absorbent heat exchanger, and by subsequent conversion of the propellant thermal energy to kinetic energy through a thrust converter or nozzle.

Abstract: The invention relates to a propulsion device comprising a gas ejection nozzle and an injection chamber for injecting at least one propellant fluid. According to the invention, the device has an induction loop which surrounds a zone of the nozzle and also an electricity generator to feed said induction loop, in particular under drive from a heat engine whose heat source is a nuclear core and whose heat sink is a cryogenic liquid which is subsequently used for propulsion.

Abstract: A method of producing and accelerating an ion beam comprising the steps of: providing a magnetic field with a cusp that opens in an outward direction along a centerline that passes through a vertex of the cusp: providing an ionizing gas that sprays outward through at least one capillary-like orifice in a plenum that is positioned such that the orifice is on the centerline in the cusp, outward of the vortex of the cusp; providing a cathode electron source, and positioning it outward of the orifice and off of the centerline; and positively charging the plenum relative to the cathode electron source such that the plenum functions as an anode. A hot filament may be used as the cathode electron source, and permanent magnets may be used to provide the magnetic field.