Method and system for measuring mass of residual propellant of propulsion system and medium

Abstract

The invention provides a method and a system for measuring the mass of a residual propellant of a propulsion system and a medium. The method comprises the steps of: 1, placing a spacecraft on a horizontal plane, and opening a liquid path isolation valve to enable liquid paths of parallel storage tanks to be communicated and balanced; 2, enabling an additional container to be communicated with the propulsion system storage tanks, and measuring the pressure of the air cavities of the propulsion system storage tanks and the pressure of the additional container; 3, injecting a preset volume of gas into the additional container, and measuring the pressure; 4, calculating the volume of the air cavities of the storage tanks; 5, subtracting the volume of the air cavities of the storage tanks from the known total volume of the storage tanks to obtain the residual propellant volume; 6, measuring the temperature of the propellant to obtain the corresponding propellant density; 7, calculating the mass of the residual propellant in the storage tanks; and 8, opening a deflation valve of the additional container for deflation, closing the deflation valve, repeatedly measuring the mass of the residual propellant for multiple times, and taking the root mean square of the measurement results as a final measurement value. The residual propellant amount of the propulsion system can be measured on the premise that the residual propellant is not discharged, and the safety of personnel is guaranteed.

Description

technical field [0001] The invention relates to the field of measurement technology, in particular to a method, system and medium for measuring the mass of remaining propellant in a propulsion system. In particular, it relates to a method for measuring the remaining propellant mass of a propulsion system by gassing an additional vessel. Background technique [0002] At present, most spacecraft propulsion systems are liquid two-component propulsion systems, and the liquid propellants are toxic dinitrogen tetroxide, methylhydrazine, etc. A variety of working conditions need to be assessed during the test, and the quality of the propellant in the tank cannot meet the needs of multiple uses, so multiple propellant injections are required. Among them, after the completion of each working condition test, it is necessary to determine the remaining amount of propellant and the filling amount of the subsequent test, because the propellant is a toxic liquid, and the remaining propell...

AI Technical Summary

Problems solved by technology

A variety of working conditions need to be assessed during the test, and the quality of the propellant in the tank cannot meet the needs of multiple uses, so multiple propellant injections are required

Among them, after the completion of each working condition test, it is necessary to determine the remaining amount of propellant and the filling amount of the subsequent test, because the propellant is a toxic liquid, and the remaining propellant dose after emptying the test in the measurement tank is not safe

The present invention proposes a method for measuring the mass of remaining propellant in the storage tank without eliminating the remaining propellant of the propulsion system. This measuring method can be used for other liquid propellants, and can be calculated at each filling For the remaining amount of propellant, the calculation error will not be accumulated in multiple fillings, which solves the problem of air entrainment in the liquid pipeline during the process of discharging the remaining propellant, and the problem of unbalanced propellant in multiple storage tanks, and can ensure that during the measurement process operator safety

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