43 results about "Ion thruster" patented technology

A gas distributor for improving ionization efficiency of a radio frequency ion thruster, comprising a gas supply pipeline, a cavity, a flow guide ball, radial rotational flow holes, axial diffusion holes and a flow guide ball limiter, the gas supply pipeline and the cavity are integrally formed, the radial rotational flow holes and the axial diffusion holes are dispersedly arranged in the cavity, the flow guide ball is filled into the cavity through the gas supply pipeline, the flow guide ball limiter is arranged in the cavity to prevent relative movement of the flow guide ball in the cavity, and the gas distributor composed of the gas supply pipeline, the cavity, the flow guide ball, the radial rotational flow holes, the axial diffusion holes and the flow guide ball limiter is arranged at the bottom of a discharge chamber of the thruster.

The application relates to the technical field of electric propulsion, in particular to a laser array hole forming method for a spherical carbon-carbon grid of an ion thruster, which comprises the following steps: step 1: fixing the spherical carbon-carbon grid on a laser processing workbench through a combined tool; step 2: scanning and fitting the spherical profile parameters of the carbon-carbon grid; step 3: carrying out fan-shaped partitioning on the spherical carbon-carbon grid, selecting one fan-shaped partitioning, and carrying out laser hole forming through a laser processing device; and step 4: rotating and arraying and splicing all information in the selected fan-shaped partitioning along an axial direction, and sequentially completing laser hole forming processing in the remaining fan-shaped partitionings. The application innovatively adopts the laser hole forming mode of fan-shaped partitioning and rotating arraying in combination with the special thin-walled curved multi-hole structure characteristics of the grid of the ion thruster and the carbon-carbon material characteristics, greatly simplifies the planning of the laser processing track, simultaneously, can eliminate the stepping error, and effectively guarantees the position precision of the grid holes.

The invention relates to a cusped magnetic field configuration-based direct-current ion thruster device, and relates to the field of ion thrusters, the cusped magnetic field configuration-based direct-current ion thruster device comprises a shell, a tungsten filament cathode, an inner magnetic ring, an outer magnetic ring, an upstream anode and a radial anode, and the outer magnetic ring and the inner magnetic ring are fixed on the side surface of a discharge chamber to establish cusped magnetic field configuration to restrain plasma; the axial gas distributor serves as an upstream anode, the radial gas distributor serves as a radial gas supply anode, electrons can move from a tungsten filament cathode to the upstream anode or the radial gas supply anode under the action of an electric field, and in the process, the electrons are captured by a cusped magnetic field and then generate ionization collision with gaseous working medium atoms to generate ions; according to the structure of the thruster, electrons in the discharge chamber are distributed more uniformly, uniform ionization of working medium gas atoms in the discharge chamber is achieved, and the thruster has the technical advantages of being high in ionization efficiency and large in thrust adjusting range.

The invention specifically discloses an ion thruster acceleration grid probability life evaluation method based on coupling competitive failure, and relates to the technical field of aerospace propulsion system life evaluation. The method comprises the following steps: firstly, obtaining deterministic parameters and random parameters of a thruster acceleration grid assembly; then based on an ion sputtering corrosion theory, considering material loss caused by charge exchange ion bombardment of the acceleration gate, and establishing a coupling corrosion model of the thickness and aperture of the acceleration gate; thirdly, constructing a competitive failure model, and realizing numerical solution of competitive failure life by dynamically iterating a corrosion state and a failure criterion; and finally, independently repeated random sampling is carried out based on probability distribution of random parameters, the random sampling is substituted into the competitive failure model to obtain an acceleration grid simulation life sample set, and statistical analysis is carried out on the life sample set to obtain a probability life evaluation result. The method solves the problem of errors caused by independent modeling of structural failure and electronic reflux failure in the prior art, and is helpful for reducing the system operation risk and improving the reliability of a spacecraft.

This application provides an atomic deposition apparatus suitable for ion sputtering experiments, including a sputtering product deposition module, a support and position adjustment module, a tilt adjustment module, and a target fixing and beam signal acquisition module. This application addresses the problem that existing atomic deposition apparatuses primarily measure the atomic deposition rate inside ion thruster discharge chambers or sputtering coating chambers, making it difficult to accurately control ion incident conditions and measure the spatial distribution of sputtering products. The target fixing and beam signal acquisition module is mounted on the tilt adjustment module and located within the sputtering product deposition module. It also utilizes the support and position adjustment module as a base placed at the bottom of the vacuum chamber, supporting and driving the other modules to move horizontally and / or vertically.

The application discloses an enhanced ion propulsion ship platform, which comprises a ship body, a rudder, an enhanced ion thruster and a high-pressure generating module. A plurality of enhanced ion thrusters are coaxially connected in series through connecting rods in a propulsion direction and are installed on a tail deck of the ship body. The enhanced ion thruster comprises an acceleration duct, two groups of supports are installed in the acceleration duct, each group of supports comprises two electrode supports, first electrodes in the form of sheets are uniformly arranged on the electrode supports close to the connecting rods, and second electrodes in the form of sharp shapes are uniformly arranged on the electrode supports on the other side. The number of the enhanced ion thrusters to be connected and the electrode voltage required are controlled to meet the required thrust of the ship at different speeds. The particle swarm algorithm is used to determine the minimum ship resistance, and the best longitudinal inflow angle and outflow angle are obtained to realize the efficient operation of the low-speed ship platform. The application has the advantages of simple structure, economy, lightness, easy popularization and suitability for various water surface low-speed operation systems.

The application relates to the field of aerospace measurement technology, in particular to an ion thruster current density three-dimensional cloud map dynamic reconstruction system and method.The system comprises a vacuum cabin, a data acquisition and display module, a control module, an ion thruster, a support frame, a Faraday probe array, a moving mechanism, a multi-signal acquisition module, a measurement and control module and a data processing module, wherein the ion thruster is fixed at one end of the support frame through a support; the Faraday probe array is fixed at the other end of the support frame through the moving mechanism; the control module is connected with the data acquisition and display module and the ion thruster; the measurement and control module is connected with the data processing module and the multi-signal acquisition module, and the multi-signal acquisition module is connected with a switching cable box. The application adopts double linear interpolation to capture the changes in the cross section, combines linear interpolation to describe the gradual change between cross sections, the mathematical model is rigorous, the reconstructed field is smooth and continuous, the fidelity is significantly higher than that of a traditional method, and the inversion accuracy is high.

Disclosed is an electric propulsion system (110, 210) utilizing particles collected from atmosphere, the electric propulsion system having a first end (112) facing, when in use, incoming flow of particles (102, 202) and an exit aperture (252) at a second end (114) to eject accelerated particles to generate thrust, the electric propulsion system comprising an active intake module (220, 320A, 320B, 320N) having an opening (222, 322A, 322B, 322N), an active compression mechanism (224) and a first output (226); a guiding channel (230, 330) comprising a splitter (332, 432); the ion thruster; and the cathode.

The invention discloses an ion thruster acceleration gate downstream pit-groove corrosion morphology prediction method, which comprises the following steps: establishing a computational domain, and determining boundary conditions of the computational domain; ions are injected from the left boundary of the computational domain, charges carried by all the ions are mapped to grid nodes of the computational domain through a weight distribution method, and space charge density distribution is obtained; solving three-dimensional potential distribution and three-dimensional electric field distribution in a computational domain based on space charge density distribution and set boundary conditions; pushing the ions to move based on the three-dimensional electric field distribution, and updating the positions and speeds of all the ions; simulating a charge exchange collision process of ions and neutral atoms based on the updated ion position and speed, and updating the state of the collided ions; counting information of charge exchange ions impacting the downstream surface of the acceleration gate within a set time; and calculating the three-dimensional corrosion morphology of the downstream surface of the acceleration gate based on charge exchange ion information in combination with a sputtering yield model and gate material attributes.

The invention relates to an efficient miniature ion thruster based on microwave ionization enhancement, and relates to the field of ion thrusters, a permanent magnet group comprises a plurality of annular permanent magnets which are distributed at intervals along the axis direction of a shell, and cusped magnetic fields are formed between adjacent permanent magnets to reduce the loss of plasmas on the wall surface; the tungsten filament cathode is fixedly connected to the middle of one side of the shell and the axis coincides with the axis of the shell; the annular anode is fixedly connected in the shell on the periphery of the tungsten filament cathode, the axis of the anode coincides with the axis of the tungsten filament cathode, and the gas supply assembly is fixedly connected to the shell on one side of the anode so as to supply a gaseous propellant into the shell; the device has the advantages that microwave energy coupling, efficient magnetic confinement of a cusped magnetic field, ionization area expansion and high specific impulse acceleration of a grid system are combined, and therefore efficient ionization and high specific impulse acceleration of low-density working medium gas can be achieved under the low-power condition; the device has the advantages of compact structure, high efficiency and high specific impulse.

The invention relates to a compact air purification device based on ion thruster technology During operation, the ion thruster generates ozone (O₃) as a byproduct of oxygen ionization. This ozone is directed into a reaction chamber where it oxidizes volatile organic compounds (VOCs) and other airborne pollutants. The system eliminates the need for external fans or filters by using the natural airflow created by the thruster itself. Key components include an ionization chamber, a grounded copper ring, a high-voltage accelerator grid, and a downstream reaction zone. The device operates effectively in low-humidity environments, where ozone remains stable and highly reactive. This integration of aerospace propulsion and environmental chemistry offers a novel, energy-efficient solution for air treatment in enclosed or emergency settings. The invention is suitable for use in homes, laboratories, industrial spaces, and mobile purification units.

This invention relates to the fields of aerospace propulsion and laser communication technology, specifically to an interplanetary laser communication silicon-tritium sphere nuclear fusion laser emission thruster, comprising a silicon-tritium sphere nuclear fusion laser emitter and a laser communication device. By employing nuclear fusion technology, silicon and tritium elements are fused under high temperature and high pressure to generate energy, which is then converted into laser light and emitted, providing powerful propulsion for rockets. This solves the technical problem that existing aerospace propulsion technologies mostly use chemical rockets or ion thrusters, which have low propulsion force and long acceleration times, failing to meet the needs of future deep space exploration. By modulating and demodulating the generated laser signal, rapid data transmission can be achieved, thus solving the technical problem that existing laser communication technologies mostly use semiconductor lasers as the emission source, where the transmission distance and data rate are limited.

This invention discloses a gas supply system for a miniature radio frequency ion thruster, belonging to the field of electric propulsion technology, and relating to rarefied gas flow in plasma propulsion. By placing a gas distribution structure at the working fluid inlet in the ionization chamber and arranging the disc of the gas distribution structure coaxially with the ionization chamber, the propellant entering the ionization chamber is uniformly distributed after passing through the gas distribution structure, increasing the average density of the propellant in the ionization chamber. This results in higher absorption efficiency of radio frequency energy by the miniature radio frequency ion thruster, more uniform plasma distribution, and higher ion density in the plume, significantly improving the performance and operational stability of the miniature radio frequency ion thruster. Furthermore, the gas distribution structure is simple, with both the disc and cylinder being cylindrical, reducing manufacturing difficulty and increasing economic efficiency compared to existing technologies. The gas supply system for the miniature radio frequency ion thruster of this invention solves the problems of complex structure and low propellant density in existing gas supply structures.

The invention discloses a radio frequency ion thruster based on a composite coil, and belongs to the field of space electric propulsion. The thruster comprises a radio frequency coil, a direct current magnetic field coil, an insulating layer, an ionization chamber, a screen grid, an acceleration grid and a neutralizer, and the radio frequency coil and the direct current magnetic field coil are wound around the ionization chamber to form a composite constraint environment of an alternating electromagnetic field and a steady magnetic field; the radio frequency coil and the DC magnetic field coil are wrapped by the insulating layers. And the screen grid, the acceleration grid and the neutralizer are sequentially arranged at the outlet end of the ionization chamber. The problem that an existing radio frequency ion thruster is difficult to ignite and start can be solved, meanwhile, the in-orbit operation stability of the thruster is improved, and the service life of the thruster is prolonged.

The aerospace-grade electric thruster is a 100% electric thruster that can be easily installed on a satellite or spacecraft to provide thrust or steering. Installation simply requires attaching the thruster securely to the structure to be propelled and connecting it to a power source. This thruster has a thrust that can be precisely controlled electronically. This design offers significant advantages over ion thrusters and chemical-type reaction thrusters because it uses no fuel or propellants; it requires only electrical power for operation.

The invention provides a dynamic progressive micro-discharge polishing method for a grid assembly of an ion thruster, and relates to the technical field of space electric propulsion. According to the method, under the normal beam extraction working condition of the ion thruster, voltage between grids and extraction beam density are gradually increased in a staged mode, the controllable micro-discharge phenomenon on the surfaces of the grids is induced, and local high-temperature plasma generated by micro-discharge is used for conducting in-situ removal on burrs on the edges and the surfaces of grid holes. By optimizing the voltage-beam collaborative loading path, uniform etching and ablation of burrs are realized, and the surface quality of the grid electrode is remarkably improved. The method can be directly implemented after the ion thruster is assembled, disassembly or chemical treatment is not needed, and the method has the advantages of being high in process compatibility, high in efficiency and free of pollution.

The invention relates to the technical field of spaceflight electric propulsion, and particularly discloses an ion thruster anode assembly integrated structure design optimization method based on additive manufacturing, which comprises the following steps: determining the external size of a gas distribution ring of a discharge chamber by combining the input parameters of the discharge chamber of the ion thruster; calculating the circumferential pressure distribution of the gas distribution ring; combining pressure distribution and gas distribution ring aperture matching to complete aperture number and gradient aperture size design; a bidirectional spiral pressurization flow channel is designed; performing gas uniformity simulation analysis in combination with CFD (Computational Fluid Dynamics); and finally, integrally modeling, designing and forming the anode and the gas distribution ring of the pressure gradient compensation type ion thruster based on additive manufacturing. Aiming at the core requirement of the circumferential gas supply uniformity of the discharge chamber of the ion thruster, balanced gas distribution is realized through flow channel pressure compensation and gradient aperture reverse adjustment, the problem of non-uniform circumferential gas supply caused by flow channel pressure gradient of a traditional gas distribution ring is solved, and uniform gas supply in the discharge chamber of the ion thruster is realized.

The application discloses an atomic oxygen conversion method and an air-breathing electric propulsion filtering system. The atomic oxygen is ionized and then recombined to generate oxygen, so that high-speed and controllable oxygen conversion is realized, and the reaction efficiency is high. The air-breathing electric propulsion filtering system comprises an air inlet section, a contraction section and a straight section. The air-breathing electric propulsion filtering system is provided with a central electrode and a side wall electrode, so that the atomic oxygen in the super-low orbit atmosphere is pre-ionized, and is pushed to a side wall thickening area under the action of an electric field. The atomic oxygen ion obtains electrons from the metal material of the side wall thickening area, and then re-generates atomic oxygen. A high-concentration atomic oxygen aggregation area is generated, so that the recombination rate of the atomic oxygen is greatly improved. The generated oxygen molecules are rectified by a rectifying mechanism, and then replace the original strong corrosive atomic oxygen to enter an ion thruster, so that the corrosion of the atomic oxygen in the super-low orbit atmosphere to key components of the ion thruster is effectively avoided.

The application provides a front ring gas supply device for an ion thruster discharge chamber, comprising a gas supply ring groove and a gas supply ring cover, the gas supply ring groove and the gas supply ring cover cooperate to form a cavity, the cavity comprises a first cavity and a second cavity, a plurality of through holes are arranged on the gas supply ring cover, the first cavity and the second cavity are communicated through the through holes, the first cavity is communicated with a gas supply pipeline, and the second cavity is communicated with a discharge chamber cavity. By adopting the two-stage cavity buffer gas supply mode, the distribution of the working gas in the ion thruster discharge chamber is more uniform, the spatial uniformity of the plasma density in the ion thruster is improved, and then the flatness of the extracted ion beam is improved, which is beneficial to prolonging the service life of the ion thruster; by adopting the oblique gas injection mode, the axial velocity of the gas is reduced, the residence time of the working gas in the ion thruster discharge chamber is prolonged, and the working gas utilization rate of the ion thruster is improved.

The invention relates to the technical field of spacecraft propulsion, in particular to a method for improving the plasma discharge stability of a discharge chamber, and provides a progressive and differentiated cathode ignition starting method, and on the basis, the plasma discharge stability of the discharge chamber is improved through plasma discharge baking of the discharge chamber and small-beam baking of a grid assembly. Rapid matching and balance of two physical processes of gas discharge and ion beam extraction in the ion thruster are realized, so that the discharge stability of plasmas in the discharge chamber is effectively improved under the condition of ensuring that the ignition starting time of the ion thruster does not exceed the standard, the sputtering etching rate of the plasmas in the discharge chamber can be reduced, and the service life of the plasmas in the discharge chamber is prolonged. And the working reliability and safety of the ion thruster can be effectively improved.

The invention relates to a compact air purification device based on ion thruster technology During operation, the ion thruster generates ozone (O₃) as a byproduct of oxygen ionization. This ozone is directed into a reaction chamber where it oxidizes volatile organic compounds (VOCs) and other airborne pollutants. The system eliminates the need for external fans or filters by using the natural airflow created by the thruster itself. Key components include an ionization chamber, a grounded copper ring, a high-voltage accelerator grid, and a downstream reaction zone. The device operates effectively in low-humidity environments, where ozone remains stable and highly reactive. This integration of aerospace propulsion and environmental chemistry offers a novel, energy-efficient solution for air treatment in enclosed or emergency settings. The invention is suitable for use in homes, laboratories, industrial spaces, and mobile purification units.

The application relates to the technical field of space electric propulsion, in particular to an ion thruster grid state monitoring method based on an extended Kalman filter, which comprises the following steps: step 1, establishing an extended Kalman filter model for ion thruster grid state monitoring; step 2, calculating a state transition matrix; step 3, calculating a predicted value of a next node state; step 4, obtaining measurement data through an online measurement sensor; step 5, setting an offset limit; step 6, updating the state of the Kalman filter model; step 7, judging whether the online measurement sensor misreads or the ion thruster works abnormally according to a comparison result; step 8, calculating the remaining life of the grid according to the state update value; and step 9, repeating steps 3-8 until the task is completed. The application has the functions of dynamically monitoring the aperture of the grid, the etching depth of the grid hole, the abnormal working state and the remaining life of the grid, and the method is simple, the calculation amount is small, and the abnormal diagnosis speed is fast.

The application discloses a three-dimensional sputtering deposition collection device under multiple azimuth angles, comprising a vacuum chamber, a supporting bottom plate and a radio frequency ion thruster are arranged in the vacuum chamber, a sputtering deposition three-dimensional collection mechanism is detachably installed on the top of the supporting bottom plate, a target material is arranged at the top end of the supporting bottom plate, the target material is arranged on the inner side of the sputtering deposition three-dimensional collection mechanism, the radio frequency ion thruster is arranged above the sputtering deposition three-dimensional collection mechanism, the radio frequency ion thruster is used for generating an ion beam, and the ion beam is used for bombarding the target material. The application collects the sputtering deposition quality of the target material under multiple azimuth angles through experiments, based on the demand of monitoring the three-dimensional spherical sputtering area generated by the sputtering particles after the target material is bombarded by ions, the three-dimensional sputtering area monitoring of different ion bombardment incident angles is realized by arranging the target material and the three-dimensional sputtering deposition collection device at different angles. The application is composed of a mechanical structure, is easy to assemble, simple to process, convenient to use and stable in data acquisition.

The application relates to the technical field of measurement, in particular to a kind of ion thruster working state grid tiny deformation measurement method, comprising the following steps: step 1: constructing measurement system;Step 2: debugging camera;Step 3: open ion thruster to start working, make three cameras synchronous shooting by control software, complete image shooting collection every 30 seconds, and process image data collected synchronously;Step 4: continuously collect images, and process image data synchronously until ion thruster is powered off and cooled to room temperature;Step 5: according to the data processing result of continuous image collection, the result of ion thruster working state grid tiny deformation measurement is calculated.The application realizes the multidimensional repeated measurement of a group of data at the same time, improves the test accuracy, ensures the long-time continuous work of camera in vacuum, plasma environment, can collect ion thruster full working process data, and improves the reliability of test.

The invention discloses a capacitive coupling high self-bias self-neutralization radio frequency ion thruster of a microcavity structure, and belongs to the field of space electric propulsion. The method is characterized in that the thruster comprises a radio frequency matcher, a radio frequency power supply and an axisymmetric cylindrical discharge cavity, the first bottom surface and the side surface of the discharge cavity are provided with power connection electrodes, and the second bottom surface of the discharge cavity is provided with an acceleration bias electrode and an insulator; the acceleration bias electrode is a circular flat plate and is provided with a plurality of lead-out holes with the same inner diameter; the insulator is arranged on the circumference of the acceleration bias electrode and is connected with the power connection electrode on the side surface of the cavity; the inner surface of the first bottom surface is provided with uniformly distributed microcavities, and the microcavities are cylindrical grooves distributed in an array mode; and the radio frequency power supply is electrically connected with the first bottom surface through the radio frequency matcher. The radio frequency ion thruster does not need an external neutralizer any more, and the application reliability of the thruster is improved.

Ion thrusters in the prior art apply a high electric potential between an emitter and a collector. Electrons are liberated to form ions around the emitter which are attracted toward the collector. The ions collide with molecules in an atmosphere creating an ionic wind. The electric field both liberates the electrons and attracts the ions to the collector. The disclosed ion thruster decouples the liberation of electrons from the attraction of the ions toward the collector. Instead of liberating the electrons by a coronal discharge, electrons are liberated by the photoelectric effect by shining a light on to the emitter comprised of a low work function solid that is susceptible to allowing electrons to be released. In some embodiments in which the material is easily oxidized, a coating is applied to the surface that allows subatomic particles to pass through the coating while blocking atoms and molecules.

This application relates to the field of space electric propulsion technology, specifically to a method for establishing a variable boundary simulation model of an ion thruster gate assembly. The method includes: Step 1: dividing the gate into regions; Step 2: selecting the object to be studied within each region; Step 3: calculating the upstream ion density of each object; Step 4: calculating the corresponding Debye length and determining the maximum values ​​of the calculation region in the lateral and radial directions; Step 5: handling collisions between atoms; Step 6: establishing a simulation calculation model; Step 7: calculating the gate morphology; Step 8: correcting the gate simulation calculation model; and Step 9: completing the establishment of the variable boundary simulation model of the ion thruster gate assembly. This application utilizes the sputtering etching morphology obtained from simulation calculations to update and improve the simulation calculation model in real time, enabling more accurate prediction of the thruster's operational lifespan, significantly shortening the product development cycle and reducing development costs.

The application discloses a gas-restraint type carbon nanotube field ionization thruster, which comprises a first pole plate, a second pole plate, a gas restraint plate, a sealing ring, a first shell and a second shell. The second pole plate is provided with carbon nanotube clusters with gaps generated by chemical vapor deposition and chemical point covering method, and the carbon nanotube clusters have larger tip electric field and higher ionization efficiency than common emitters, but the distribution of the carbon nanotube clusters is relatively sparse. The gas restraint device cooperates with the carbon nanotube clusters of the emitters to ensure that the carbon nanotube clusters have independent ionization spaces, avoids the working medium gas from escaping into the gaps of the carbon nanotube clusters, and thus improves the ionization efficiency. Meanwhile, the gas restraint device can further shield the electric field influence between the carbon nanotube clusters, avoids the mutual interference between different carbon nanotube clusters during propulsion, improves the controllability of the thruster, and further improves the ionization efficiency. The device can reduce the waste of the working medium gas and improve the service life of the thruster.

The invention discloses a high-thrust ion thruster integrating an emitting electrode and a receiving electrode. The high-thrust ion thruster comprises an integrated electrode integrating the emitting electrode and the receiving electrode, an insulating bracket and a high-voltage power supply module, the integrated electrode is arranged on the insulating bracket; according to the ion thruster, the problem that the thrust of the ion thruster is small can be solved.