A Pulsed Plasma Thruster System Containing an Ignition Automatic Counting Device
A pulsed plasma, automatic counting technology, applied in the aerospace field, can solve problems such as difficult measurement, and achieve the effect of reducing test errors and saving manpower
Active Publication Date: 2020-11-24
BEIJING INSTITUTE OF TECHNOLOGYGY
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At the same time, the single ablation mass of the propellant of the pulsed plasma thruster is only a few micrograms, which is difficult to measure
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[0019] specific implementation
[0020] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.
[0021] see figure 1 , the system of the present invention comprises three major parts, is respectively automatic counting device, ground power supply system and thruster. Specifically, the ground power system includes a pulse generator and a power supply. The power supply is used to provide energy for the thruster. The two poles of the power supply are respectively connected to the cathode and anode of the thruster, and the pulse generator is connected to the spark plug of the thruster. The pulsed plasma thruster is set in the vacuum chamber and mainly includes an ignition system and a propellant. The ignition system includes a spark plug, a cathode, an anode and a main capacitor. The spark plug is connected to the cathode, and the propellant is placed between the cathode and the anode. The thruster is placed in the va...
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The invention provides a pulsed plasma thruster system comprising an ignition automatic counting device. Ignition of the pulsed plasma thruster system can be accurately counted. The pulsed plasma thruster system comprising the ignition automatic counting device comprises a pulsed plasma thruster, a ground power source system and the ignition automatic counting device, wherein the pulsed plasma thruster comprises an ignition system and a propellant, the ignition system comprises a sparking plug, a cathode, an anode and a main capacitor, the ground power source system comprises a pulse generatorand a power source, the power source is used for providing energy for the thruster, the two electrodes of the power source are connected to the cathode and the anode of the thruster correspondingly,the pulse generator is connected to the sparking plug of the thruster, the ignition automatic counting device comprises a photoelectric converting device and two double-display pulse counters, the photoelectric converting device is connected with the double-display pulse counter a, and the pulse generator in the ground power source system is connected with the other double-display pulse counter b.The pulsed plasma thruster system comprising the ignition automatic counting device can accurately record the number of discharge times of the main capacitor of the pulsed plasma thruster in real time, saves labor and reduces test errors; guarantee is provided for a long-service-life test of the pulsed plasma thruster; and meanwhile, the number of generation times of the ignition signals of the pulsed plasma thruster and the number of discharge times of the main capacitor provide basis for discharge stability analysis of the pulsed plasma thruster.
Description
technical field [0001] The invention belongs to the field of aerospace, in particular to a pulse plasma thruster system including an ignition automatic counting device. Background technique [0002] With the development of micro-satellite technology in many civil aerospace fields, people put forward strict requirements for its propulsion system, such as light weight, low power consumption, and precise controllability. The pulsed plasma thruster has a high technical maturity and can meet the requirements of the propulsion system for micro-satellites. The pulsed plasma thruster works in a pulsed manner, and the discharge times of the main capacitor and whether the main capacitor is successfully discharged after receiving the ignition signal are important parameters for evaluating the performance of the pulsed plasma thruster. At the same time, the single ablation mass of the propellant of the pulsed plasma thruster is only a few micrograms, which is difficult to measure. The...
Claims
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IPC IPC(8): F03H1/00
CPCF03H1/0006F03H1/0087
Inventor 刘向阳林永樑冷春雪陈世昌周阳丁一墁
Owner BEIJING INSTITUTE OF TECHNOLOGYGY