1504results about "Using plasma" patented technology

The invention, in various embodiments, is directed to a solid-state flow generator and related systems, methods and applications.

A dc accelerator system able to accelerate high currents of proton beams at high energies is provided. The accelerator system includes a dc high-voltage, high-current power supply, an evacuated ion accelerating tube, a proton ion source, a dipole analyzing magnet and a vacuum pump located in the high-voltage terminal. The high-current, high-energy dc proton beam can be directed to a number of targets depending on the applications such as boron neutron capture therapy BNCT applications, NRA applications, and silicon cleaving.

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.

An ion radiation therapy machine provides a steerable beam for treating a tumor within the patient where the exposure spot of the beam is controlled in width and / or length to effect a flexible trade-off between treatment speed, accuracy, and uniformity.

A particle beam therapeutic apparatus can ensure the uniformity of dose distribution by overlapping the desired loci of the irradiation of a particle beam a reduced number of times. A flow of a particle beam transported so as to be irradiated to a diseased part is caused to deflect in two mutually orthogonal directions perpendicular to the direction of travel of the particle beam. The irradiation position of the particle beam is scanned, upon each period, in a manner to return to a position of irradiation located at the start of the period, whereby a plurality of loci drawn within one period are overlapped with one another thereby to irradiate a desired planned dose to the diseased part. The particle beam can be interrupted only at the end of the period.

A method and apparatus for deploying a group of panels. An apparatus comprises a group of panels in a folded configuration against a side of a spacecraft, a group of flexible members connected to the group of panels, and an interface system associated with the group of panels and the group of flexible members. The interface system is configured to move the group of panels from the folded configuration to a deployed configuration when the group of flexible members is extended from the spacecraft.

An apparatus and / or method for controlling an ion beam may be provided, and / or a method for preparing an extraction electrode for the same may be provided. In the apparatus, a plurality of extraction electrodes may be disposed in a path of an ion beam. At least one extraction electrode may include a plurality of sub-grids.

The invention is intended to increase the number of patients treatable using one wheel having a thickness varied in the rotating direction to change energy of an ion beam passing the wheel. Ion beam delivery equipment for irradiating an ion beam to a patient for treatment comprises a beam generator for producing and accelerating the ion beam, an beam delivery nozzle including a range modulation wheel which has a predetermined thickness distribution in the rotating direction and is rotated on a travel passage of the ion beam generated from the beam generator to control a range of the ion beam, and an irradiation controller for controlling the beam producing and accelerating operation of the beam generator in accordance with the phase of rotation of the range modulation wheel.

A closed drift ion source which includes a channel having an open end, a closed end, and an input port for an ionizable gas. A first magnetic pole is disposed on the open end of the channel and extends therefrom in a first direction. A second magnetic pole disposed on the open end of the channel and extends therefrom in a second direction, where the first direction is opposite to the second direction. The distal ends of the first magnetic pole and the second magnetic pole define a gap comprising the opening in the first end. An anode is disposed within the channel. A primary magnetic field line is disposed between the first magnetic pole and the second magnetic pole, where that primary magnetic field line has a mirror field greater than 2.

This invention features a combined radio frequency (RF) and Hall Effect ion source and plasma accelerator system including a plasma accelerator having an anode and a discharge zone, the plasma accelerator for providing plasma discharge. A gas distributor introduces a gas into the plasma accelerator. A cathode emits electrons attracted to the anode for ionizing the gas and neutralizing ion flux emitted from the plasma accelerator. An electrical circuit coupled between the anode and the cathode having a DC power source provides DC voltage. A magnetic circuit structure including a magnetic field source establishes a transverse magnetic field in the plasma accelerator that creates an impedance to the flow of the electrons toward the anode to enhance ionization of the gas to create plasma and which in combination with the electric circuit establishes an axial electric field in the plasma accelerator. An RF power source provides RF power to at least one electrode disposed about and / or inside the plasma accelerator that induces current for ionizing the gas to create the plasma such that the axial electric field accelerates ions through the plasma accelerator to provide ion flux.

An In Orbit Transportation & Recovery System (IOSTAR™) (10) One preferred embodiment of the present invention comprises a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.

The invention relates to apparatus for generating ions in a gaseous medium, the apparatus comprising one or more needles (40) each presenting a shank (40.1) and an emitter end (40.2), a sheath (42) of composite material comprising glass fiber reinforced unsaturated polyester surrounding the shank (40.1) of each needle, and means (44, 46, 80) for applying a voltage between two portions of the shank of each needle.

A system for, and method of recovering a solar-powered spacecraft from an anomaly that renders the attitude of the spacecraft unknown includes maintaining a power-safe attitude by switching between two orthogonal axes using solar panel current sensors. The system and method may also include simultaneously determining spacecraft attitude using a star sensor. The system is applicable to spacecraft operating in a solar wing-stowed configuration.

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.

A method for controlling an actuator of a vehicle comprises providing a dynamic condition sensor generating a vehicle movement signal and a position sensor for generating a reported position. A processor is coupled to the inertial sensor and the position sensor and comprises an estimator, a position measurement predictor having a filter, a comparator and a control shaping block, said estimator generating a vehicle position based upon the dynamic condition sensor, said position measurement predictor generating an estimated position measurement in response to the reported vehicle position and a matched frequency response to the movement signal, said control shaping block generating an actuator control signal in response to a comparison of the estimated position measurement and the reported vehicle position.

An ionic liquid ion source can include a microfabricated body including a base and a tip. The microfabricated body can be formed of a porous metal compatible (e.g., does not react or result in electrochemical decaying or corrosion) with an ionic liquid or a room-temperature molten salt. The microfabricated body can have a pore size gradient that decreases from the base of the body to the tip of the body, so that the ionic liquid can be transported through capillarity from the base to the tip.

A Hall field plasma accelerator with closed electron drift includes a composite anode including a housing with inner and outer walls which form an outer anode and an inner anode forming inner and outer distribution zones; the housing is electrically conductive and has an upstream end and an exit port electrically insulated from the housing; the composite anode includes an input distribution system for introducing plasma gas into the distribution zones; poles establish a magnetic field across the exit port and a cathode establishes an electron flow through the magnetic field toward the composite anode and creates an electric field through the exit port; the electrons ionize the plasma gas that is accelerated by the electric field through the exit port.

An apparatus for producing a vacuum arc plasma source device using a low mass, compact inductive energy storage circuit powered by a low voltage DC supply acts as a vacuum arc plasma thruster. An inductor is charged through a switch, subsequently the switch is opened and a voltage spike of Ldi / dt is produced initiating plasma across a resistive path separating anode and cathode. The plasma is subsequently maintained by energy stored in the inductor. Plasma is produced from cathode material, which allows for any electrically conductive material to be used. A planar structure, a tubular structure, and a coaxial structure allow for consumption of cathode material feed and thereby long lifetime of the thruster for long durations of time.

The invention provides a novel, low-cost, spin-stabilized lander architecture capable (with appropriate system scaling tailored to the attributes of the target) of performing a soft-landing on a solar-system body such as Earth's Moon, Mars, Venus, the moons of Mars, Jupiter, Saturn, Uranus and Neptune, selected near-Earth and main-belt asteroids, comets and Kuiper belt objects and even large human-made objects, and also moving about on the surface of the target solar-system body after the initial landing in movement akin to hopping.

Methods and apparatus are presented for spacecraft operation in which a control problem is formulated using a control law or steering law as a path constraint or as a dynamic constraint, and the control problem is solved to provide a guidance command trajectory for use in operating spacecraft control momentum gyroscopes to guide the spacecraft from an initial state to a desired final state.

Propellant liquid is supplied to a Colloidal Thruster for Micro-Satellite vehicles in Space by capillarity induced flow through a wick element comprising a permeable porous aggregate of fibers or particles of material that is wetted by the propellant liquid. An intense electric field at the tip of the wick element dispersed the arriving liquid into a fine spray of charged droplets. Electrodes having appropriate design, location and potentials accelerate the charge droplets to high velocity, thereby providing reactive thrust to the vehicle. In this method of propellant liquid introduction the flow rate and exhaust velocity, and therefore the thrust level, are determined by the applied potential difference, thereby eliminating the need for pumps or pressurized gas and flow controllers to provide the desired flow-rate for the propellant liquid.

A closed-loop LRF pointing technology to measure the range of a target satellite from a chaser satellite for rendezvous is provided that includes: LOS angle measurements of the target, a relative navigation Kalman filter, attitude determination of the visible sensor with gyros, star trackers and a Kalman filter, pointing and rate commands for tracking the target, and an attitude controller. An analytical, steady-state, three-axis, six-state Kalman filter is provided for attitude determination. The system provides improved functionality and precision for relative navigation, attitude determination, pointing, and tracking for rendezvous. Kalman filters are designed for the closed-loop system to allow for pointing the laser rangefinder to a target even if a visible sensor, a laser rangefinder, gyros and a star tracker are misaligned and the LOS angle measurements from the visible sensor are interrupted.

Ion mobility spectrometer apparatus may include an ion interface that is operable to hold positive and negative ions and to simultaneously release positive and negative ions through respective positive and negative ion ports. A first drift chamber is operatively associated with the positive ion port of the ion interface and encloses an electric field therein. A first ion detector operatively associated with the first drift chamber detects positive ions from the first drift chamber. A second drift chamber is operatively associated with the negative ion port of the ion interface and encloses an electric field therein. A second ion detector operatively associated with the second drift chamber detects negative ions from said second drift chamber.

System for converting high frequency quantum electrodynamic radiation energy and at least one atom through cavity vacuum fluctuations and converting same into a superconductive electrical implosion propulsion energy from zero point energy at a frequency that is amenable to conversion to electrical and implosive propulsion and superconductive energy extracted within an environment having a desired voltage and a reversed waveform such that the emitted energy returns into the system to be recycled. In an externally winged craft comprising a selectively shaped vacuum cohesive fuselage and means for providing lift and propulsion for an aircraft generating an enormous electrostatic vortex lifting force when energized in conjunction with the quantum electrodynamic vortex implosion propulsion system and power plant maximizing fuel efficiencies including the extraction of usable energy from the vacuum of space. Actually riding on or in the shock waves verses the brute force disruption of the environment's equilibrium, as is the case with conventional modes of transportation or aircraft design.

The invention set forth herein describes propulsive guidance methods and apparatus for controlling and shaping an atmospheric skip reentry trajectory for a space vehicle. Embodiments of the invention may utilize a powered explicit guidance algorithm to provide a closed-loop control method for controlling a space vehicle during a skip reentry maneuver.

A system for providing attitude and antenna steering for a spacecraft is disclosed. The spacecraft has a number of reaction wheels and a number of antennas. The system includes control logic configured to: determine a beta angle, the beta angle being the angle between a sun vector and an orbit plane of the spacecraft, and alternately engage either a first mode or a second mode to provide attitude and antenna steering based on the beta angle.

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.

A propulsion system for the orbit control of a satellite in Earth orbit driven at a rate of displacement along an axis V tangential to the orbit comprises two propulsion modules, fixed to the satellite, and facing one another relative to the plane of the orbit, each of the propulsion modules comprising, in succession: a motorized rotation link about an axis parallel to the axis V; an offset arm; and a plate supporting two thrusters, suitable for delivering a thrust on an axis, arranged on the plate on either side of a plane P at right angles to the axis V passing through a centre of mass of the satellite; each of the two thrusters being oriented in such a way that the thrust axes of the two thrusters are parallel to one another and at right angles to the axis V.