| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060203100 | Electric, nuclear, or radiated energy fluid heating means | 20 |
| 20080202093 | Pulsed plasma thruster using vapor and method of making - 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. | 08-28-2008 |
| 20090056304 | Solar energy augmented jet aircraft - 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. | 03-05-2009 |
| 20090120056 | Microthruster, in particular for use as a position adjustment thruster, thruster and method for producing a microthruster - 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. | 05-14-2009 |
| 20090165437 | Drive device on the basis of a gel-type propellant and method for conveying propellant - 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 | 07-02-2009 |
| 20100024385 | PULSED PLASMA THRUSTER AND METHOD OF OPERATION THEREOF - 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. | 02-04-2010 |
| 20100058734 | METHOD OF ENHANCING MICROTHRUSTER PERFORMANCE - 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. | 03-11-2010 |
| 20110000185 | Fusion energy process - 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. | 01-06-2011 |
| 20120110978 | Absolute universal engine, one from ground to orbit - 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, <<>> | 05-10-2012 |
| 20120167548 | PLASMA THRUSTERS - 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. | 07-05-2012 |
| 20120304618 | METHOD AND APPARATUS FOR SMALL SATELLITE PROPULSION - 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. | 12-06-2012 |
| 20130014486 | Fiber laser powered thrusterAANM Campbell; Robert NeilAACI CorralesAAST NMAACO USAAGP Campbell; Robert Neil Corrales NM US - A fiber laser powered, optical to thermal conversion thruster with improved practicality and operational and design flexibility. | 01-17-2013 |
| 20140013724 | ELECTROMAGNETIC THRUSTER - Systems and methods for electromagnetic thrusting are disclosed. An electromagnetic thrusting system includes an axially-asymmetric resonant cavity including a conductive inner surface, the resonant cavity adapted to support a standing electromagnetic (EM) wave therein, the standing EM wave having an oscillating electric field vector defining a z-axis of the resonant cavity. The resonating cavity lacks 2nd-axis axial symmetry. The standing EM wave induces a net unidirectional force on the resonant cavity. | 01-16-2014 |
| 20140075917 | FAULT TOLERANT CONTROL SYSTEM FOR DISTRIBUTED MICRO-THRUSTERS - A control system for controlling the operation of a plurality of micro thrusters arranged in a plurality of parallel horizontal rows and a plurality of parallel vertical columns, the control system requires a power source, a first plurality of power lines connected to the power source and coupled to at least one micro thruster of the plurality of micro thrusters in a horizontal row of the plurality of parallel horizontal rows, a second plurality of power lines connected to the power source and coupled to at least one micro thruster of the plurality of micro thrusters in a vertical column of the plurality of parallel vertical columns, and a control unit coupled to the power source to control activation of the first plurality of power lines and activation of the second plurality of power lines. | 03-20-2014 |
| 20150040536 | EXTERNALLY POWERED HYBRID PROPULSION SYSTEM - A hybrid propulsion system for a vehicle comprises a propellant tank for providing a supply of propellant, a propellant heater, and an exhaust nozzle. The propellant tank is in fluid communication with the propellant heater and is configured for providing a flow of propellant to the propellant heater. The propellant heater is in fluid communication with the propellant tank and the nozzle and initially comprises a supply of oxidizer that is configured for reacting chemically with the propellant to produce heat. The propellant heater is further configured for receiving a beam of microwave energy and facilitating transmission of the beam of microwave energy to the propellant. The nozzle is in fluid communication with the propellant heater and is configured for receiving a flow of propellant from the propellant heater, for accelerating the propellant, and for expelling the propellant so as to produce thrust. | 02-12-2015 |
| 20150373826 | ION ACCELERATORS - An ion accelerator includes: an inner magnet having a channel extending through it in an axial direction; an outer magnet extending around the inner magnet, the magnets having like polarities so as to produce a magnetic field having two locations of zero magnetic field strength. The locations are spaced apart in the axial direction; and an anode and a cathode are arranged to generate an electrical potential difference between the locations. | 12-24-2015 |
| 20160032906 | PLASMA DRIVE - A plasma drive includes a plurality of plasma thrusters arrayed in each of at least one array of plasma thrusters. Plasma thrust may be generated sequentially or in a pulse from each array. Circuitry is adapted to selectively fire each thruster in each array according to a digitally controlled progression. The controlled firing progression collectively provides a cumulative thrust vector for each array. In a turbine drive embodiment the controlled progression causes sequential firing of the thrusters in each array, and the arrays in sequence. The controlled progression allows for directional control of the combined cumulative thrust vectors. | 02-04-2016 |
| 20160047364 | METHOD AND SYSTEM FOR A PROGRAMMABLE AND FAULT TOLERANT PULSED PLASMA THRUSTER - A system and method provides a fault-tolerant multi-channel pulsed plasma thruster system utilizing a control unit and an embedded real time application manipulating low-level timing events with programming, with clear examples of completely flexible control techniques of a scalable micropropulsion system having many pulsed plasma thruster channels, taking into account system aging behavior and specific mission utilization requirements that may change in the mission lifetime. The system and method also covers an architecture lending itself suitable for design of a dedicated FGPA or ASIC that would tightly integrate many channels of thruster components to build a robust, resilient and versatile micropropulsion subsystem for space applications, and indirectly for advanced multi-channel spacecraft instrumentation. | 02-18-2016 |
| 20160076450 | Solar Jet Turbofan Aircraft Engine - The Solar Jet Turbofan Aircraft Engine is a system and method for utilizing electrical heating elements to heat compressed air within a jet engine's “Heating Chamber” in order to increase or decrease thrust. | 03-17-2016 |
| 20160086680 | Positron Systems for Energy Storage, Production and Generation - A positron based system is disclosed which extracts electric power from matter-antimatter annihilation reactions between electrons and positrons. In one embodiment, for storage and distribution of electric power, a solar array provides power to a cyclotron that produces the positron emitter | 03-24-2016 |
| 20160146197 | BATTERY POWERED VEHICLE PROPULSION SYSTEM - A vehicle propulsion system includes an air heating chamber that receives inlet air from an air intake chamber and provides thrust through an exhaust chamber. A battery powered pulse generator generates a pulsed electrical output signal. An amplifier amplifies the pulsed electrical output signal to provide an amplified pulsed power output signal to the air heating chamber. The amplified pulsed power output signal directly heats the inlet air to generate thrust through the exhaust chamber. | 05-26-2016 |
