The invention relates to an electric propelling engine gas distributor, relates to the problem that whether propellant gas distribution of an electric propelling engine is uniform or not and belongs to the field of electric propelling Due to non-uniform distribution of gas inlet pipelines, traditional gas distributors cause non-uniform circumferential distribution of propellant gas in electric discharging channels, and consequently, electric discharging of thrusters is affected In order to solve the problem, the gas distributor with circumferential and radial gas transmission grooves and non-uniform distributed axial gas transmission holes/grooves is designed The gas distributor mainly comprises a distributor-upper bottom, a distributor-lower bottom, gas inlet pipes and fastening screws By forming gas transmission grooves, circumferential and radial diffusion of the propellant gas are manually inhibited, and non-uniform axial gas transmission holes/grooves are formed according to the different propellant gas densities in the different positions, so that the propellant gas enters the electric discharging channels more uniformly and the uniform and stable neutral particle environment is provided for the thrusters

Electric propelling engine gas distributor

The invention provides a magnetic screen/discharge channel integrated structure of a Hall thruster. The structure includes an anti-sputtering ring, a ring cylindrical magnetic screen and an insulator,wherein an inner ring of the anti-sputtering ring is in matching connection with the second inner thread of an inner wall of the ring cylindrical magnetic screen through the first outer thread, an outer ring of the anti-sputtering ring is in matching connection with the second outer thread of an outer wall of the ring cylindrical magnetic screen through the first inner thread, the inner ring andthe inner wall are coaxial and equal in diameter, the outer ring and the outer wall are coaxial and equal in diameter, the ring cylindrical magnetic screen is fixed on a bottom plate of a thruster bracket, the insulator is disposed between the ring cylindrical magnetic screen and an anode, and circumferentially uniformly distributed protrusions at the bottom of the insulator recess are matched with through holes uniformly distributed in the circumferential direction of the bottom plate of the ring cylindrical magnetic screen. The structure is advantaged in that a problem of mounting and adjustment difficulty as magnetic screens and discharge channels are respectively designed and manufactured in the prior art is solved, the magnetic screen and ceramic discharge channel structure is improved into the metal magnetic screen/discharge channel integrated structure, and the structure and the size of the thruster are simplified.

Magnetic screen/discharge channel integrated structure of Hall thruster

The invention belongs to the field of electric thrust and particularly relates to a micro-cathode electric arc thruster applied to a micro-nano satellite. The micro-cathode electric arc thruster is mainly applied to power systems of small satellites such as the micro-nano satellite. According to the micro-cathode electric arc thruster, aiming at solving the problem that an existing micro-nano satellite is not provided with a propelling system, through the vacuum cathodic electric arc discharging principle, an integral electric thruster structure is designed. The thruster structure is mainly composed of a shell 1, a cathodic working medium 2, a spring 3, a ceramic cylinder 4, a base 5, fixing nuts 6, nut fastening bolts 7, an anode 8, a conductive coating film layer 9 and a magnetic coil 10. When a preset voltage is achieved between a cathode and the anode, cathode spots conduct discharging, spreading is gradually conducted, and the cathodic working medium is continuously subjected to ionization corrosion to form a stable plasma plume. The plasma plume is sprayed outwards under the effect of an applied magnetic field to form needed counteractive thrust. The micro-cathode electric arc thruster is small in overall structural size and low in weight.

Micro-cathode electric arc thruster

The invention relates to a magnetic circuit structure design method under the long service life design of a magnetic focusing Hall thruster and belongs to the Hall thruster design technical field. According to the method, the thickness of the wall surface of a ceramic discharge channel, the thickness of an inner magnetic screen and the thickness of an outer magnetic screen are increased, so that the service life of the thruster can be prolonged; the wall surface rear section of the ceramic discharge channel is adjusted to be a segmented structure or the ceramic discharge channel wall surface thickness of the rear section of the ceramic discharge channel is decreased; and therefore, low excitation efficiency loss can be realized. According to the inner magnetic screen and the outer magneticscreen, a soft magnetic ferrite material with a high magnetic permeability and a low thermal expansion coefficient is adopted to replace DT4C pure iron.

Magnetic circuit structure design method under long service life design of magnetic focusing Hall thruster

The invention discloses a Hall thruster with a novel buffer cavity, and belongs to the technical field of Hall thrusters. The Hall thruster with the novel buffer cavity solves the problems that in thecase of an existing low-power Hall thruster, due to the fact that the size is too small, gas density and homogenization degree are not high. An inner ceramic screen and an outer ceramic screen of theHall thruster with the novel buffer cavity are of an inside-and-outside nested cylindrical structure, a radial gap and an axial gap are formed between the inner ceramic screen and the outer ceramic screen, so that a buffer cavity structure between the inner ceramic screen and the outer ceramic screen is formed, an anode and the outer ceramic screen are fixedly mounted on a bottom plate through agas distributor and a nut, an inner permanent magnet is fixedly mounted in the inner ceramic screen through a permanent magnet support, and is fixedly mounted on the bottom plate through a fixing nut,and an outer permanent magnet is mounted on the outer side of the outer ceramic screen in a sleeving mode. A discharge channel of the Hall thruster with the novel buffer cavity is formed by insertingthe outer ceramic screen and the inner ceramic screen, the buffer cavity is formed at the area between the outer ceramic screen and the inner ceramic screen, a gas motion path is enlarged through thenovel buffer cavity structure, and gas is more sufficiently homogenized.

Hall thruster with novel buffer cavity

The invention discloses a double-layer pore plate type gas distributor easy to assemble The double-layer pore plate type gas distributor easy to assemble comprises a gas guiding column, a distributor base, a first-layer pore plate, a second-layer pore plate, an outer baffle, an inner baffle and a fixing column The gas guiding column, the distributor base, the outer baffle and the inner baffle are all hollow cylinders, the first-layer pore plate and the second-layer pore plate are both hollow circular plates, and the fixing column is a cylinder One end of the distributor base is provided with holes for installation of the gas guiding column and the fixing column, the other end of the distributor base is provided with grooves for installation of the first-layer pore plate and the second-layer pore plate, and the first-layer pore plate and the second-layer pore plate are both provided with small holes for homogenizing gas The outer baffle is fixedly connected with the outer side of the second-layer pore plate, the inner baffle is fixedly connected with the inner side of the second-layer pore plate, and the outer baffle and the inner baffle are further fixedly connected with the other end of the distributor base Through the cooperation of the distributor base, the outer baffle and the inner baffle, the number of weld joints of the gas distributor is reduced, and the problem that a traditional gas distributor has multiple weld joints is solved

Double-layer pore plate type gas distributor easy to assemble

The invention discloses an anode magnetic screen integrated structure for a Hall thruster. The structure is composed of an outer ceramic cylinder, an inner ceramic cylinder, an anode, a magnetic conductive part, insulation ceramics, an insulation cap, a conductive column and a magnetic source; holes are evenly formed in the outer circle, with the largest maximum, of the anode, the anode has the gas homogenization effect, through the anode, the magnetically soft alloy material is adopted to achieve the magnetic conductive function, the magnet exciting coil manner is adopted in the magnetic source, the permanent magnet manner is adopted, the outer ceramic cylinder and the inner ceramic cylinder are arranged in an anode cavity, and therefore building of an insulation acceleration channel of the Hall thruster is achieved; during work, the anode with the high potential is isolated from other parts with different potentials through the insulation ceramics and the insulation cap; the anode is connected with other components through the conductive column, the anode is connected with the conductive column through the electron beam welding manner, the Hall thruster with the small size can achieve the focusing magnetic field type, and the type is the magnetic field type structure generally obtained by the high-performance Hall thruster.

Anode magnetic screen integrated structure for Hall thruster

The invention discloses a coaxial micro-arc cathode discharge plasma propulsion device. The coaxial micro-arc cathode discharge plasma propulsion device comprises a shell, an insulated support, insolated ceramics, a metal cathode, a metal anode and a spring, wherein the metal anode is sleeved in the insulated ceramics; the inner wall of the insulated ceramics is connected with the metal anode; the other end of the insulated ceramics is connected with a round boss of the metal anode, and the other end of the insulated ceramics is sleeved in the inner cavity of the insulated support; the insulated ceramics is sleeved in the metal cathode; the spring is arranged between the metal cathode and the insulated support; the metal cathode, the insulated ceramics and the metal anode are arranged in the shell; one end of the metal cathode clings to an annular bulge on the inner wall surface of the shell, and the other end of the metal cathode presses tightly against the spring; the other end of the insulated support is fixedly connected with the other end of the shell; when an external power control unit is controlled to discharge, the metal cathode is ablated to generate high-density plasmoids; and the high-density plasmoids fly out at high speed through the end surface of the shell 1, and then is ejected out in an accelerated manner through a magnetic field generated by a permanent magnet to generate propulsion force.

Coaxial micro-arc cathode discharge plasma propulsion device

The invention discloses a macro-arc cathode discharge micro electric boosting module which comprises a power supply, an inductance coil, a control switch, a diverter, a cathode, an anode and an electromagnetic coil, wherein the power supply is used for providing direct current which is measured by using the diverter; the inductance coil is charged with power when the control switch is closed; an instantaneous high voltage is generated to the outside when the control switch is opened; if an external circuit is communicated, current is provided to the outside till the electric energy stored in the inductance coil is completely released; the cathode and the anode can discharge power and are broken and communicated when being subjected to the instantaneous high voltage, the surface of the cathode can be burnt and plasma is generated; and under the action of magnetic lines of the electromagnetic coil, the plasma is focused and ejected out at a high speed, and thus boosting force can be generated A solid metal is adopted as a propellant, so that the problem that a micro boosting module is relatively large in size can be solved; due to cooperation of the electromagnetic coil and the control switch, and residual current discharge of an electric arc, the problem that the power of the inductance coil is consumed can be solved; and as the plasma on the surface of the cathode of a booster is focused by the electromagnetic coil, the specific impulse of the booster can be improved

Macro-arc cathode discharge micro electric boosting module

A propellant self-driven device of an MEMS electrospray thruster comprises a storage box (1), a connecting device (2), a porous emitter electrode (3), an insulating alignment frame (4), a mounting silicon frame (5) and an extraction electrode (6), wherein propellant liquid is stored in the hollow part inside the storage box (1); the insulating alignment frame (4) is mounted at the upper part of the storage box (1); the extraction electrode (6) is mounted on the insulating alignment frame (4) through the mounting silicon frame (5) mounted at the edge of the extraction electrode (6); the porousemitter electrode (3) and the connecting device (2) are mounted between the extraction electrode (6) and the storage box (1); the porous emitter electrode (3) is connected to the upper part of the storage box (1) through the connecting device (2); and there is a potential difference between the porous emitter electrode (3) and the extraction electrode (6). The propellant self-driven device of theMEMS electrospray thruster solves the problem that an original electrospray propulsion system needs to be equipped with special propellant supply management devices such as a micro pump and a micro valve, and that the thrust precision is largely limited by the propellant supply precision of the micro valve and other mechanisms.

Propellant self-driven device of MEMS electrospray thruster

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