15 results about "Plasma acceleration" patented technology

A hybrid ultra-high enthalpy arc heater comprises a rear electrode group, a contraction section, a compression channel, a throat, an expansion section, and a front electrode group. The arc cathode is attached to the electrode of the rear electrode group. The contraction section is mainly used to compress the arc column, completing the first plasma acceleration. The compression channel is used to compress and elongate the arc column, fully heating and ionizing the working gas. The airflow is concentrated to high pressure at the throat, completing the second plasma acceleration. The airflow completes the third plasma acceleration in the expansion section. The arc cathode is attached to the electrode terminal of the front electrode group, where the plasma is subjected to the Lorentz force, achieving the fourth acceleration and ultimately forming an ultra-high enthalpy flow field. This invention can be applied to the field of aerodynamic thermal ground simulation technology research, mainly providing medium and low pressure ultra-high enthalpy uniform flow fields.

The invention discloses a generating device of a surface electromagnetic wave radiation source, which can be applied to the technical field of electromagnetic waves. The plasma excitation unit is used for generating plasma, and the plasma acceleration unit comprises an electron acceleration power supply, a cathode end face, a slow wave circuit, a plurality of insulation spacers, a plurality of acceleration poles and an output end face. An electron beam channel is formed in the middle area of the upper surface of the slow wave circuit and the middle area of the lower surface of the cathode end face, the insulation spacers, the acceleration poles and the output end face, and meanwhile the insulation spacers and the acceleration poles are arranged between the cathode end face and the output end face at intervals. The speed of the plasma in the electron beam channel output by the plasma excitation unit is adjusted through the plasma acceleration unit, so that the electromagnetic wave radiation source under the target frequency, the target bandwidth or the target power can be output, and the electromagnetic wave radiation source with high frequency, wider bandwidth and high power can be obtained.

A plasma source device (100) for providing a gas volume (1) in a plasma accelerator apparatus (200) comprises a capillary channel device (10) for guiding a gas flow (2), with an irradiation port (10A) for receiving laser light (3) along an irradiation direction deviating from an axial flow direction of the gas flow (2) and with an output port (10B) aligned with the irradiation port (10A) and arranged for an output of a plasma accelerator output (4), including electron and / or X-ray beams, wherein the gas volume (1) is provided by gas of the gas flow (2) traversing an irradiation path (5) between the irradiation port (10A) and the output port (10B). The capillary channel device (10) comprises multiple capillary channels (11, 12), wherein each of the capillary channels (11, 12) has two radial pinholes (13), the capillary channels (11, 12) are arranged side by side with all pinholes (13) being aligned in series so that the irradiation path (5) through the capillary channel device (10) along the irradiation direction (z) is provided, wherein a first pinhole (13) of a first capillary channel (11) is the irradiation port (10A) and a last pinhole (13) of a last capillary channel (12) is the output port (10B), and the gas volume (1) comprises multiple gas sections (14, 15) arranged along the irradiation path (5), wherein each of the gas sections (14, 15) is provided with predetermined gas parameters by one of the capillary channels (11, 12) and wherein the gas sections (14, 15) provide the gas volume (1) as a continuous gas field along the irradiation path (5). Furthermore, a plasma accelerator apparatus (200) and a method of creating electron and / or X-ray beams are described.

The invention discloses a plasma acceleration grid surface high-carbon sputtering protection permeation layer and a preparation method thereof. The preparation method specifically comprises the following steps: carrying out nanocrystallization treatment on the surface of a molybdenum grid; carrying out cleaning and finishing pretreatment on the molybdenum gate material; coating and packaging the molybdenum gate material with a carburizing medium; and a specific temperature is selected for reaction diffusion carburization, so that a high-carbon sputtering protection permeation layer can be formed on the surface. According to the preparation method provided by the invention, surface nanocrystallization high-frequency micro-deformation processing is carried out on the finished product molybdenum grid in the state of the finished product molybdenum grid, so that surface metallization cleaning and diffusion strengthening treatment are realized; and a high-carbon compound protection permeation layer which has enough thickness and is metallurgically bonded with the molybdenum matrix is obtained by combining a high-temperature diffusion reaction process on the surface layer in the atmosphere protection solid carbon-rich medium, so that the ideal processing and maintenance characteristics of the molybdenum gate are inherited; and the requirement on the size precision of the gate hole structure can be met, and excellent electric conduction and heat conduction capabilities are maintained.

The embodiment of the invention discloses an electron gun with a controllable electron beam shape, which can be applied to the technical field of electronics. According to the embodiment of the invention, after the plasma generation module for generating the plasma and the plasma acceleration module comprising the electron beam channels of various shape structures are arranged in the electron gun, the plasma generated by the plasma generation module is accelerated through the plasma acceleration module; and the target electron beam is sent to the target vacuum tube, so that the electron beam with the target shape can be obtained without changing a focusing electrode through a Pearls electron gun, the electron beams with different interface shapes can be provided, and the engineering technical difficulty is effectively reduced.

The invention relates to the technical field of spaceflight space electric propulsion, in particular to a magnetic reconnection electric thruster electromagnetic topology integrated simulation system which comprises a high-density spiral wave ion source simulation area, an RMF rotating magnetic field simulation area and a discharge chamber model. Wherein the high-density spiral wave ion source simulation area comprises a spiral wave ion source antenna area and a spiral wave ion source steady-state magnetic field area; the RMF rotating magnetic field simulation area comprises a plasma acceleration section steady-state magnetic field area and a rotating field antenna area; the discharge chamber model comprises a discharge model, a magnetofluid model, a particle collision model and a plasma transport model. The whole working process of the magnetic reconnection electric thruster can be simulated, the performance of the magnetic reconnection electric thruster under different electromagnetic parameter combinations can be rapidly predicted, and the problems that an existing spiral wave ion source and an RMF acceleration device electromagnetic field are difficult to match, and interference exists among multiple electromagnetic fields are solved.

1. The name of the design product: superconducting magnet (magnetic plasma propulsion). 2. The use of the design product: used in the field of spaceflight, using magnetic field to control plasma to accelerate the spacecraft. 3. The design points of the design product: in shape. 4. The picture or photo that best shows the design points: perspective view 1.

The invention relates to the technical field of spaceflight space electric propulsion, in particular to a magnetic reconnection electric thruster electromagnetic topology integrated simulation system which comprises a high-density spiral wave ion source simulation area, an RMF rotating magnetic field simulation area and a discharge chamber model. Wherein the high-density spiral wave ion source simulation area comprises a spiral wave ion source antenna area and a spiral wave ion source steady-state magnetic field area; the RMF rotating magnetic field simulation area comprises a plasma acceleration section steady-state magnetic field area and a rotating field antenna area; the discharge chamber model comprises a discharge model, a magnetofluid model, a particle collision model and a plasma transport model. The whole working process of the magnetic reconnection electric thruster can be simulated, the performance of the magnetic reconnection electric thruster under different electromagnetic parameter combinations can be rapidly predicted, and the problems that an existing spiral wave ion source and an RMF acceleration device electromagnetic field are difficult to match, and interference exists among multiple electromagnetic fields are solved.

The application relates to the technical field of aerospace propulsion, and particularly discloses a vacuum arc pulse plasma thruster. The vacuum arc pulse plasma thruster comprises a vacuum arc ignition system and a pulse plasma acceleration system. The vacuum arc ignition system forms an arc to generate plasma based on high-voltage pulse discharge ablation of metal, and injects the plasma into the pulse plasma acceleration system; the pulse plasma acceleration system axially accelerates the plasma based on the Lorentz force generated by the internal formed orthogonal electromagnetic field, and the high-speed ejection of the plasma from the discharge channel forms a recoil force. The introduction of the pulse plasma propulsion acceleration mechanism promotes the efficient conversion of the capacitor energy storage into axial directional kinetic energy, and improves the thrust, specific impulse and energy conversion efficiency of the thruster.

This utility model relates to an air outlet structure for a miniature circuit breaker. By setting a first air outlet and a second air outlet on the housing, a multi-channel arc-extinguishing path is formed. During the operation of the circuit breaker, the electric arc and heat generated inside can be quickly dissipated through these two air outlets, preventing the airflow from interfering with each other within the arc-extinguishing assembly. This effectively reduces the residence time of the electric arc inside the circuit breaker. The first air guide wall between the arc-extinguishing assembly and the first air outlet, and the second air guide wall between the arc-extinguishing assembly and the second air outlet, play a role in precisely guiding the airflow. When an electric arc is generated, the air guide wall can guide the airflow in an orderly and uniform manner to the arc-extinguishing assembly, forming a stable and suitable airflow field around the arc-extinguishing grid. This airflow field helps to quickly remove the heat and plasma generated by the electric arc, accelerate the arc extinguishing process, improve the arc extinguishing efficiency, reduce the erosion of the internal components of the circuit breaker by the electric arc, and enhance the breaking capacity and reliability of the circuit breaker.

The application aims to provide a kind of plasma electromagnetic thruster, including upper clamping plate, lower clamping plate, electrode fixed box body;Box body is made of insulating material, upper clamping plate and lower clamping plate are respectively installed on the top surface and bottom surface of box body;The middle part in box body is equipped with plasma acceleration channel along its longitudinal direction, and the two ports are respectively arranged on the left and right end surfaces of box body;Box body is respectively spaced apart and arranged with more than one group of electrode sheets on the front and back sides of plasma acceleration channel;Each group of electrode sheets is respectively connected with vertical electrode rod;The upper end of electrode rod passes through the top surface of box body and penetrates through the upper clamping plate, which is located above the top surface of upper clamping plate;The lower end of electrode rod passes through the bottom surface of box body and penetrates through the lower clamping plate, which is located above the bottom surface of lower clamping plate;The bottom surface of upper clamping plate and the top surface of lower clamping plate are respectively installed with magnet.The application is scientific in design, and the plasma moves directionally in the electric field on both sides, and under the action of magnetic field, it moves quickly under the combined thrust of Ampere force and Lorentz force, thereby generating propulsive force.

The present application relates to a kind of barrel inner surface modification device, including two explosion guns and two plasma accelerators;Two plasma accelerators are in with reaction chamber, and the open end section is formed with one end of reaction chamber;Two reaction chambers are connected at open end section;Two explosion guns are respectively assembled in two ends of two reaction chambers;Wherein, explosion gun is connected to nozzle by auxiliary pipe and movable pipeline, and insulator, rod electrode and current lead are installed on the axis of reaction chamber;Insulator is assembled in the end of two reaction chambers;Axial electrode is built into reaction chamber, and two ends pass through insulator and are connected with current lead;The present application is simple in structure, ingenious in design, mainly used for the modification of the inner surface of cylindrical workpiece, and the focusing of plasma in pipe is used to increase energy density to ensure modification effect.

The invention relates to a dual-mode plasma thruster in the technical field of thrusters. The dual-mode plasma thruster comprises a spiral wave plasma source (ionization chamber) with an external magnetic field, a magnetic confinement plasma thruster (acceleration chamber I) with an external positive voltage, and a multi-coil plasma thruster (acceleration chamber II), the ionization chamber is in Y-shaped through connection with the two acceleration chambers, the head end of the ionization chamber is provided with a working medium gas inlet, and the tail ends of the two acceleration chambers are provided with plasma outlets; a spiral antenna is arranged outside the ionization chamber, and two annular permanent magnets with opposite polarities are coaxially sleeved outside the antenna and are used for ionizing and generating plasma with higher density and more uniformity; an electromagnetic coil I is arranged on the outer side of the head of the accelerating chamber I and used for generating a constant magnetic field, and a bias electrode is arranged at the tail of the accelerating chamber I and used for externally applying positive voltage; and two groups of stator coils are arranged at the two ends and the tail of the acceleration chamber. The thruster has a double-component propelling mode and a single-component propelling mode, different working modes can be switched, and working diversification of the thruster is achieved.

The present invention relates to a plasma acceleration propulsion device, and in particular to a plasma generation device and method based on a multi-stage magnetic field and a multi-stage nozzle. The present invention solves the technical problem that a plasma generation device with a single-stage nozzle is not conducive to optimizing the magnetic field configuration, making it difficult to control the trajectory of the plasma jet, resulting in unsatisfactory specific impulse and thrust. The device of the present invention includes a working fluid supply distribution unit and a plasma generation acceleration unit. The working fluid supply distribution unit includes a working fluid distributor, a second insulator, a transition electrode and a third insulator coaxially arranged from the inside to the outside; the plasma generation acceleration unit includes an n-stage nozzle, an n-1-stage first insulator, an accelerator electric field power supply corresponding to the nozzle, an electromagnetic coil corresponding to the nozzle, and an electromagnetic field power supply corresponding to the electromagnetic coil; the n-stage nozzle and the n-1-stage first insulator form a nozzle assembly. The present invention also provides a plasma generation method based on a multi-stage magnetic field and a multi-stage nozzle.

A plasma source device (100) for providing a gas volume (1) in a plasma accelerator device (200) comprises a capillary channel device (10) for conducting a gas flow (2), the capillary channel device having an irradiation port (10A) for receiving a laser light (3) in an irradiation direction deviating from an axial flow direction of the gas flow (2), and an output port (10B) aligned with the irradiation port (10A) and arranged for outputting a plasma accelerator output (4) comprising an electron beam and / or an X-ray beam, where the gas volume (1) is provided by a gas flowing through a gas flow (2) of an irradiation path (5) between the irradiation port (10A) and the output port (10B). The capillary channel arrangement (10) comprises a plurality of capillary channels (11, 12), where each capillary channel (11, 12) has two radial apertures (13), the capillary channels (11, 12) are arranged side by side, all apertures (13) are aligned in series to provide an irradiation path (5) through the capillary channel arrangement (10) in an irradiation direction (z), where a first aperture (13) of a first capillary channel (11) is an irradiation port (10A) and a second aperture (12) of a second capillary channel (12) is an irradiation port (10B). The last aperture (13) of the last capillary channel (12) is an output port (10B), and the gas volume (1) comprises a plurality of gas sections (14, 15) arranged along the irradiation path (5) wherein each gas section (14, 15) is provided by one of the capillary channels (11, 12) with a predetermined gas parameter, and the gas sections (14, 15) provide a continuous gas field as a gas volume (1) along the irradiation path (5). Furthermore, a plasma accelerator device (200) and a method of generating an electron beam and / or an X-ray beam are described.