| The accuracy of liquid level signal measurement determines the residual mass of propellant,which will directly affect the effectiveness of the launch vehicle control system.In recent years,with the wide use of non-toxic and non-polluting cryogenic liquid propellant in the power system of launch vehicles,more stringent requirements have been put forward for the propellant level height monitoring sensor.In order to ensure that the designed low temperature propellant level sensor of the new generation of launch vehicle meets the actual use requirements,strict test experiments should be carried out before it is put into use.Therefore,this paper selects kerosene(normal temperature)and liquid nitrogen(-196 ℃)as the main liquid media in the experiment,designs and develops the servo motor control system,grating ruler measurement system,data acquisition and processing system to compose the experimental test device,and completes the uncertainty analysis and technical index test experiment of the experimental device.Through the analysis of the experimental data,it can be seen that the performance of the experimental test device can meet the requirements of the capacitive liquid level sensor test experiment.The test device uses the principle of relative motion to make the sensor and the liquid level generate relative motion.It can simulate the drop speed of the liquid level:(20.0 ± 0.2)mm/s,(40.0 ± 0.4)mm/s,(60.0± 0.6)mm/s,(80.0 ± 0.8)mm/s.The experiment compares the electrical signal generated by the sensor to the position signal generated by the grating ruler of the servo control system to achieve the calibration,immersion,pressure,temperature,vibration and other test experiments of the new launch vehicle capacitive low temperature liquid level sensor.According to the test results in different environments,the segmented annular capacitive liquid level sensor developed this time can realize the liquid level measurement of launch vehicle propellant. |
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