9 results about "Micro propulsion" patented technology

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 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 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.

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.