25 results about "Micro propulsion" patented technology

The invention provides an air pressure regulation and control device, a cold air micro-propulsion system and a satellite, and relates to the technical field of cold air micro-propulsion. The air pressure regulation and control device comprises a high-pressure valve, a two-stage pressure reducing valve, a precise pressure regulating valve, a buffer gas cylinder and a pressure sensor; one end of the high-pressure valve is connected with the high-pressure gas cylinder, and the other end of the high-pressure valve is connected with the two-stage pressure reducing valve through a first pipeline; the precise pressure regulating valve is provided with a first connector, a second connector, a third connector and a fourth connector, the first connector is connected with the two-stage pressure reducing valve through a second pipeline, the second connector is connected with the pressure sensor through a third pipeline, the third connector is connected with the buffer gas cylinder through a fourth pipeline, and the fourth connector is connected with the thruster. Compared with the prior art, the air pressure regulation and control device has the advantages that the mode of combining two-stage pressure reduction, air capacity buffering and air pressure closed-loop precise regulation and control is adopted, stable and low-noise air can be supplied to the thruster, and therefore high-stability and low-noise thrust output is achieved.

The invention discloses an oil cylinder fixing device for thermal forming of a mold, and relates to the technical field of fluid driving tools of the mold, the oil cylinder fixing device comprises an oil cylinder oil way control structure, the oil cylinder oil way control structure is mounted in a slotted flexible metal lamination frame, and an oil way pipe at the top of the oil cylinder oil way control structure is communicated with an oil way in the mold; under the cooperation of the self-adaptive fixing assembly and the soft pressure contact fixing assembly, a linkage synergistic effect is formed, stress synergistic adjustment among all parts of the whole fixing device is achieved, and after the position of the oil cylinder oil way control structure is greatly adjusted through the self-adaptive fixing assembly, the edge side pushes the abutting frame through the micro driving structure of the abutting frame, so that the position of the oil cylinder oil way control structure is adjusted. The micro propelling guide rod is promoted to carry out corresponding secondary adjustment, it is ensured that the all-directional and high-precision contact state and the fixing effect are always kept between the soft pressing contact fixing assembly and the oil cylinder oil way control structure, dynamic balance is achieved, and the service life of the oil cylinder oil way control structure is guaranteed.

The invention discloses a propulsion storage tank lightweight design method based on variable thickness topological optimization, which is characterized in that topological optimization is carried out on a storage tank wall plate structure, the weight is reduced while the design requirement is met, and the lightweight of a micro propulsion storage tank is realized. According to the topological optimization process of the inner wall face of the storage box, the wall thickness, stress, inherent materials and the like serve as boundary conditions, the stress distribution state is optimized by optimizing structural characteristics, and meanwhile the process of structural weight reduction is achieved. Compared with the prior art, optimization of the stress distribution state of the storage tank and lightweight design of the structure of the storage tank are achieved at the same time; the universality is high, and the method can be used in the design of regular containers or special-shaped pressure-bearing containers; the coincidence with the 3D printing technology is high, and the design redundancy in the structural design under the limitation of the traditional 3D printing technology is effectively reduced; the operation is simple, and the practicability is high.

The present invention relates to a micro-thruster based on an annular bombardment cathode, which belongs to the field of space electric propulsion, and includes a thruster housing, insulating ceramics, a thruster anode, a plurality of annular permanent magnets, a thruster pole shoe, a cathode fixing ceramic and a cathode emitter; the thruster housing is a hollow cylinder, an insulating ceramic is arranged inside one end of the thruster housing, a thruster anode is arranged inside the insulating ceramic, the insulating ceramic and the thruster anode are arranged coaxially, the other end of the thruster housing is an open end, a cathode fixing ceramic is sleeved outside the open end, the cathode fixing ceramic is used to fix the cathode emitter, and the cathode emitter is arranged coaxially with the thruster housing; a plurality of annular permanent magnets are coaxially fixed to the inner side of the thruster housing, and fixed between the cathode fixing ceramic and the insulating ceramic, and a thruster pole shoe is arranged between each annular permanent magnet; the cathode emitter is located within the angle of the plume bombardment generated when the micro-thruster is working. The present invention improves the overall efficiency and specific impulse of the micro-thruster.

The application discloses a capillary type ion liquid electric spray thruster with electrically controlled thrust, and belongs to the technical field of micro-nano satellite micro propulsion. The application comprises a propellant tank, an upper shell, a constant force spring, a limiting plate, a capillary and an extraction electrode. The inner and outer walls of the capillary are covered with a dielectric layer with a micron level thickness, and the inner wall is covered with a hydrophobic layer with a nanometer level thickness. The extraction electrode is fixed through an insulating screw; and the upper shell is fixed with the propellant tank. The application is based on the principle of electric wetting, uses an electric field to control the active supply of ion liquid and simultaneously adjusts the thrust size of the thruster. The application can not only save complicated fluid control components such as high-precision pumps, valves and pipelines, but also can couple the supply process and the emission process of the ion liquid, simplify the operation process of the thruster system and facilitate the miniaturization of the thruster system. The application is suitable for resistance compensation, position keeping and attitude control of low-power micro-nano satellites.

The application discloses a gel micro-propeller for space propulsion, which comprises an electrode plate, a sealing ring, a combustion chamber, a nozzle, a threaded connecting port, a feeding port, an anti-backfire channel and a thermal protection layer. The gel micro-propeller has a small volume; the required gel propellant is continuously supplied by an injection pump; the gel propellant is ignited after the electrode plate is electrified; the combustion rate of the gel propellant is regulated by changing the feeding flow of the gel propellant; and the propeller keeps stable work when the flow of the gel propellant is constant. In addition, there is no problem of current wiring in the gel micro-propeller, and the related circuit content is concentrated in a commercialized circuit board. Therefore, the gel micro-propeller is light in weight, convenient to carry, simple in structure and high in maneuverability, and the influence of the problems of a large volume of a previous propeller and complex lines during installation on space micro-nano satellites is eliminated, and the gel micro-propeller is mainly used for precise control of the propulsive force required for attitude adjustment and orbit deviation of space micro-nano satellites.

The application provides a gas pressure regulating device, a cold gas micro-propulsion system and a satellite, and relates to the technical field of cold gas micro-propulsion. The gas pressure regulating device comprises a high-pressure valve, a two-stage pressure reducing valve, a precision pressure regulating valve, a buffer gas cylinder and a pressure sensor. One end of the high-pressure valve is connected with a high-pressure gas cylinder, and the other end of the high-pressure valve is connected with the two-stage pressure reducing valve through a first pipeline. The precision pressure regulating valve is provided with a first interface, a second interface, a third interface and a fourth interface. The first interface is connected with the two-stage pressure reducing valve through a second pipeline, the second interface is connected with the pressure sensor through a third pipeline, the third interface is connected with the buffer gas cylinder through a fourth pipeline, and the fourth interface is connected with a thruster. Compared with the prior art, the gas pressure regulating device adopts a combination of two-stage pressure reduction, gas capacity buffering and gas pressure closed-loop precision regulation, can supply stable and low-noise gas to the thruster, and thus realizes high-stability and low-noise thrust output.

The invention discloses a laser micro-propulsion system based on a micro-size zoom optical module. The laser micro-propulsion system comprises a laser light source, a working medium supply device, a target belt, a pre-collimating lens, a first beam expanding lens, a second beam expanding lens, a focusing lens and a diaphragm, wherein the target belt is wound on the working medium supply device, and the target belt is positioned at the rear part of the light of the diaphragm; the laser light source emits single-mode pulse laser, the single-mode pulse laser is pre-collimated by the pre-collimating lens to form a pre-collimated light beam, the pre-collimated light beam is expanded and collimated by the first beam expander and the second beam expander in sequence to obtain an expanded and collimated light beam, the expanded and collimated light beam is focused by the focusing lens to obtain a focused light beam, and the focused light beam is focused by the focusing lens to obtain a focused light beam. And the focused light beam is emitted from the diaphragm and acts on the target belt to form a jet plume. The dynamic adjustment of the specific impulse and the thrust of the micro-propulsion system is realized.

The invention relates to a process for bonding and gluing between a micro-thruster array charging chamber and an ignition chip layer. Comprising the following steps: preparing an epoxy resin powder chamber, an ignition chip, a gluing positioning mold, an ignition chip positioning mold and a mask; placing an epoxy resin powder chamber in a gluing positioning mold, and covering the epoxy resin powder chamber with a mask; the bottom of the gluing positioning mold is placed on a vacuum adsorption platform; dispersing and dispensing bonding glue on the mask, blade-coating the bonding glue, sucking the bonding glue into the window under the action of a vacuum pump, and separating the epoxy resin powder chamber distributed with the bonding glue from the mold; and the vacuum pump is closed, the mask is uncovered, the ignition chip is covered with the ignition chip positioning mold, the ignition chip is positioned, and the ignition chip provided with the positioning mold is covered with the powder chamber. The mask is used for controlling the gluing area and the gluing amount, and the mold is used for controlling the relative distribution positions of the powder chamber and the chip ignition bridge.

The present invention relates to an integrated global micro-propulsion system and a micro-satellite, which are used to provide three-axis attitude control for the micro-satellite. The system includes: a thruster module and a propellant supply module; the thruster module is arranged on the surface of the satellite, and is integrated with three thrusters of cold air, electric heating type and microwave ion; the propellant supply module includes a common gas source and a decompression system, and the common gas source stores the gas propellant working medium required for the thruster to work, and is connected to each thruster module through a gas supply pipeline; the decompression system is arranged on the gas supply pipeline, and is used to regulate the gas pressure and flow rate of the working medium supply. Compared with the prior art, the present invention can achieve a large thrust range and high precision, overcome the requirements that a large thrust range and high precision are difficult to meet at the same time, improve the anti-disturbance capability of the satellite, meet the requirements of satellite three-axis attitude control and degree of freedom, and can realize the drag-free control of the satellite system, and is applied to major tasks such as gravitational wave detection and sky telescope.

The application relates to the technical field of precision measurement, and discloses a sub-micro-newton thrust vector testing method and device, wherein the device comprises a frame support arranged on a base and a double-shaft suspension beam mechanism; a first cross beam is arranged at the top of the frame support; the double-shaft suspension beam mechanism is connected to the center of the first cross beam and forms a double-shaft suspension structure; a micro-propeller mounting frame is used for mounting and fixing a sub-micro-newton micro-propeller and adjusting the position of the micro-propeller during measurement; a double-shaft electromagnetic actuator and a double-shaft displacement sensor are used for measuring the displacement change of the micro-propeller mounting frame and the thrust vector of the sub-micro-newton micro-propeller in two directions perpendicular to each other in a horizontal plane; and a data processing module is used for reading the working current of the double-shaft electromagnetic actuator during measurement, calculating the thrust vector of the sub-micro-newton micro-propeller, and outputting the measurement result of the thrust vector of the sub-micro-newton micro-propeller.

The invention relates to an ultra-large mode field spoke core fiber laser suitable for laser micro propulsion, which adopts a main oscillation power amplification structure and comprises a seed source, a first amplification stage, a second amplification stage and a main amplification stage, the seed source is a directly modulated semiconductor laser, outputs pulse laser with tunable pulse width and repetition frequency, and the laser of the seed source enters the main amplification light path in a free space coupling mode after being subjected to primary and secondary pre-amplification. The main amplification stage amplifies the average power of laser to hectowatt magnitude by adopting an ultra-large mode field spoke core optical fiber with a bilateral pumping design, and dynamic adjustment of specific impulse and thrust of the micro-thruster is realized by changing the power, pulse width and frequency of the laser. The laser micro-thruster is clear in design principle, the achievable effect of the laser micro-thruster breaks through the limitation of the specific impulse and thrust dynamic range of a common laser micro-thruster, and the multi-task scene application capacity of the laser micro-thruster is remarkably improved.

The utility model belongs to the field of propellers, and particularly relates to a water-cooling type electronic control solid micro propeller which comprises a propeller shell, a spray pipe and a propelling unit. The propeller shell comprises an annular side wall and an end plate; the propulsion unit comprises a cathode annular wall plate, an insulation sealing cover and an anode column, the cathode annular wall plate is arranged in the containing cavity, the two ends of the cathode annular wall plate abut against the two end plates respectively, through holes penetrating through the inner space of the cathode annular wall plate are formed in the two end plates, and the insulation sealing cover is arranged on the through hole in one side in a sealed mode; a liquid cooling cavity is formed by the outer side of the cathode annular wall plate and the inner wall of the containing cavity, and a liquid inlet and a liquid outlet which are communicated with the liquid cooling cavity are formed in the propeller shell. Due to the reasonable position distribution of the propeller shell and the annular cathode wall plate, efficient temperature control can be carried out on the propelling unit and the propeller shell by a cooling medium at the same time, the temperature of the outer side of the electronic control solid propellant and the temperature of the outer side of the propeller are guaranteed, and the controllability and safety of the propeller are improved.

The invention discloses a cold air micro-propulsion system and propulsion method applied to a micro-nano satellite, at least two pressure reducing valves are connected in series on a pipeline, and each pressure reducing valve comprises a valve body, a pressure regulating piston, an elastic piece and a regulating piece; the valve body is provided with an air inlet channel and an air outlet channel, and the pressure adjusting piston is movably arranged in the valve body and used for adjusting the communication state of the air inlet channel and the air outlet channel. The adjusting part acts on the elastic part to adjust the pre-tightening force of the elastic part, and the elastic part is arranged on the pressure adjusting piston in a sleeving mode and used for adjusting the opening threshold value of the pressure reducing valve. A pressure adjusting cavity is formed between the pressure adjusting piston and the adjusting part, an air channel is formed in the pressure adjusting piston, the pressure adjusting cavity is communicated with the air inlet channel through the air channel, after air enters the pressure adjusting cavity through the air channel, the pressure of the air and elastic force provided by the elastic part jointly control the position of the pressure adjusting piston, and pressure reduction and self-stabilization of outlet pressure are achieved. Through the unique design that the pressure adjusting cavity is communicated with the air channel, pressure self-balancing and automatic stabilization are achieved.

The present application relates to a kind of micro-propeller based on electrolytic water suitable for micro-satellite, the micro-propeller includes solar panel, power system, electromagnetic valve, combustion chamber and nozzle, the micro-propeller also includes electrolytic device, electrolytic water is generated hydrogen and oxygen by electrolysis technology using ion exchange membrane in orbit, and hydrogen and water separation and oxygen and water separation are achieved by adding gas-liquid separator;Between gas-liquid separator and oxygen storage tank and between gas-liquid separator and hydrogen storage tank, gas bubble breaker is also respectively equipped, and the oxygen or hydrogen bubble still existing is broken down, so that oxygen or hydrogen is released.The present application solves the problem that gas-liquid is not easy to separate in space due to the absence of gravity by designing and adding gas-liquid separation device and bubble breaker in micro-propeller based on electrolytic water, and realizes the combustion of hydrogen and oxygen generated by electrolytic water as the thrust of micro-propeller.

The utility model provides a pocket-size cubesat micro-propulsion system. The pocket-size cubesat micro-propulsion system comprises a shell; the propellant box is arranged in the shell, and a working solution is stored in the propellant box; the guide pipe is in contact with the propellant box; the conduit is located between the flow regulator and the propellant box, and the flow regulator is provided with a plurality of flow regulation holes. According to the flow regulator, the flow can be regulated by customizing the size of the flow regulating hole, and only the flow regulator needs to be replaced when the flow needs to be regulated, so that the overall cost is reduced.

The invention discloses a micro cathode arc thrust system, and relates to the technical field of satellite micro propulsion, the system comprises a micro cathode arc thruster, a heating unit and a heating control unit; a cathode working medium of the micro cathode arc thruster is liquid metal; the heating unit is arranged on a cathode pipeline of the micro cathode arc thruster; the heating unit is connected with the capacitor and the heating control unit; the heating control unit comprises a temperature measuring subunit, a first control subunit and a second control subunit; the hot end of the temperature measurement subunit is arranged on a cathode pipeline of the micro cathode arc thruster, the cold end of the temperature measurement subunit is arranged in the environment, and the temperature measurement subunit is connected with the first control subunit and the second control subunit; the first control subunit is connected with the heating unit and the power supply. The service life of the micro-cathode arc thruster can be prolonged, the total impulse of the micro-cathode arc thruster can be increased, the energy consumption loss of a micro-cathode arc thrust system is reduced, and meanwhile the whole thrust system can be more concise and portable.

This invention discloses a micro-thrust measurement device and method. The micro-thrust measurement device includes a working base plate, a pivot and fixing module, a three-axis displacement stage, a torsion beam, a linear guide rail, a displacement sensor, a micro-thrust generator, and a counterweight. The linear guide rail is mounted on the working base plate and consists of a long guide rail and a short guide rail. The torsion beam is positioned between the long and short guide rails. Slider blocks are installed at the ends of both the long and short guide rails furthest from the torsion beam. The slider of the long guide rail houses a micro-thrust motor for measuring the micro-thrust, while the slider of the short guide rail houses a counterweight. The displacement sensor and the micro-thrust generator are respectively located on both sides of the long guide rail. The three-axis displacement stage is mounted on the torsion beam via the pivot and fixing module. This invention enables sub-millinewton-level micro-thrust testing of micro- and nano-satellite micro-propulsion systems. It is easy to operate, improves measurement accuracy, increases the measurement range of the testing system, and reduces costs.

The invention discloses a micro-cathode arc thruster, and relates to the technical field of satellite micro-propulsion, and the micro-cathode arc thruster comprises an inner anode, an outer anode, a plurality of cathodes and an insulator; the plurality of cathodes are positioned between the inner anode and the outer anode; the insulator is filled between the inner anode and each cathode and in a gap between the outer anode and each cathode; the inner anode and the outer anode respectively receive a first trigger pulse and a second trigger pulse, and the first trigger pulse and the second trigger pulse have time delay, so that the inner anode and the outer anode alternately discharge with the plurality of cathodes, and the inner anode and the outer anode alternately discharge with the plurality of cathodes. The discharge time of the micro-cathode arc thruster is prolonged, the energy fed into the micro-cathode arc thruster under a single pulse is increased, and the element impulse and the thrust-to-power ratio of the micro-cathode arc thruster are further improved.

The invention discloses a micro-cathode arc thruster, and relates to the technical field of satellite micro-propulsion, and the micro-cathode arc thruster comprises a cathode, a plurality of anodes and an insulator; the plurality of anodes are arranged around the cathode; the insulator is filled in a gap between the cathode and each anode; the micro-cathode arc thruster comprises a plurality of anodes, each anode corresponds to a trigger pulse, time delay exists between the trigger pulses corresponding to the adjacent anodes so that each anode and the cathode can alternately discharge, the micro-cathode arc thruster can continuously discharge by arranging the anodes and the cathode to alternately discharge, thrust is continuously provided, and the thrust efficiency is improved. And the system works in a quasi-steady state mode.

The application discloses a magnetic moment coupling geomagnetic micro-force generating device and belongs to the technical field of magnetic power. The device comprises a plurality of independently controlled coils, a magnetic concentrating sheet arranged at the bottom of the coils, a geomagnetic sensor for collecting real-time geomagnetic direction data and device posture data, a controller electrically connected with the geomagnetic sensor for receiving the geomagnetic direction data and the device posture data of the geomagnetic sensor and outputting control signals, a driving module electrically connected with the controller and the coils for receiving the control signals of the controller and adjusting the currents of the coils respectively, and a power supply module electrically connected with the controller, the geomagnetic sensor, the coils and the driving module for power supply. The application does not need superconducting, magnetic shielding, permanent magnets or high-frequency commutation, can work at normal temperature, and is suitable for ground micro-liter floating verification and space attitude control micro-propulsion double scenes. The application further discloses a posture control method of the magnetic moment coupling geomagnetic micro-force generating device.

The present application discloses a micro-cathode arc thrust system, which relates to the field of satellite micro-propulsion technology. The system comprises: a micro-cathode arc thruster, a heating unit, and a heating control unit. The cathode working fluid of the micro-cathode arc thruster is liquid metal. The heating unit is arranged on the cathode pipe of the micro-cathode arc thruster. The heating unit is connected to a capacitor and the heating control unit. The heating control unit comprises: a temperature measuring subunit, a first control subunit, and a second control subunit. The hot end of the temperature measuring subunit is arranged on the cathode pipe of the micro-cathode arc thruster, and the cold end of the temperature measuring subunit is arranged in the environment. The temperature measuring subunit is connected to the first and second control subunits. The first control subunit is connected to the heating unit and a power supply. The present application can improve the service life and total impulse of the micro-cathode arc thruster, reduce the energy loss of the micro-cathode arc thrust system, and make the entire thrust system more concise and lightweight.

The application is a kind of process for bonding and coating between charge chamber and ignition chip of micro-propeller array. The process comprises the following steps: preparing epoxy resin charge chamber, ignition chip, coating positioning mold and ignition chip positioning mold, and mask; placing the epoxy resin charge chamber in the coating positioning mold, covering the mask on the epoxy resin charge chamber; placing the bottom of the coating positioning mold on the vacuum adsorption platform; dispersing and coating the bonding glue on the mask, scraping the bonding glue, and the bonding glue is absorbed into the window under the action of the vacuum pump, separating the epoxy resin charge chamber with the mask; closing the vacuum pump, removing the mask, covering the ignition chip positioning mold on the ignition chip, positioning the ignition chip, and covering the charge chamber on the ignition chip with the positioning mold. The application uses the mask to control the coating area and the amount of glue, and uses the mold to control the relative position of the distribution of the charge chamber and the chip ignition bridge.

The invention provides a micro-propulsion system for a ground air floating satellite simulator and a forming method of the micro-propulsion system, and relates to the technical field of spacecraft ground tests. In the present application, the micro-propulsion system comprises: a gas nozzle; a solenoid valve; the output end of the micro-propulsion control assembly is connected with the electromagnetic valve, and the micro-propulsion control assembly is used for controlling whether the electromagnetic valve is opened or not; the communication transceiving module is used for communicating with a satellite service computer of a simulation satellite so as to receive a thrust value calculated by the satellite service computer, and sending the thrust value to the micro-propulsion control assembly, so that the micro-propulsion control assembly determines corresponding nozzle switching time based on the thrust value; therefore, the gas nozzle is controlled by the electromagnetic valve to output gas flow within the nozzle switching time, so that thrust corresponding to the thrust value is provided for the ground air floating satellite simulator. Based on the content, the problem that in the prior art, the cost of a micro-propulsion system is high can be solved.