A closed low filling rate parallel tank filling method

Abstract

The invention discloses a closed low filling rate parallel storage tank filling method. The method includes: when filling the propellant, according to the characteristics of the parallel storage tanks of the propulsion system with a low filling rate, adjusting the parallel storage tanks Tox1 and Tox2 to different back pressures, and obtaining the weighing zero point of the filling amount of the storage tank Tox2; The self-locking valve LV2 of the downstream liquid port of the tank Tox2 is used to fill the storage tank Tox2 to the predetermined filling amount; close the self-locking valve LV2 to obtain the weighing zero point of the filling amount of the storage tank Tox1; open the downstream liquid port of the storage tank Tox1 The self-locking valve LV1 fills the storage tank Tox1 to a predetermined filling amount; finally opens the upstream air port addition and discharge valves of the storage tanks Tox1 and Tox2, and fills the parallel storage tanks with extruded helium at a predetermined pressure. The invention realizes the purpose of filling the parallel storage tanks with low filling rate without venting through the gas port.

Description

technical field [0001] The invention relates to the technology of a spacecraft dual-component propulsion system, in particular to a method for filling a closed parallel storage tank with a low filling rate, which is suitable for filling satellite propellants in a parallel storage tank with a low filling rate. Background technique [0002] The satellite bicomponent propulsion system uses MON-1 (oxidizer) and MMH (combustion agent) as the working fluid. The propulsion system with parallel tank structure generally includes 4 propellant tanks, and 2 tanks contain MON- 1. Pack MMH in 2 tanks. When the traditional two-component propulsion system is used for propellant filling, it is usually necessary to add propellant to the liquid port of the tank and release gas through the gas port at the same time, so as to establish a stable filling pressure difference. Due to the high saturated vapor pressure of the oxidant, a certain amount of oxidant will be released through the gas port,...

AI Technical Summary

Problems solved by technology

However, due to the high saturated vapor pressure of the oxidant, a certain amount of oxidant will be released through the gas port, resulting in inaccurate weighing of the filling equipment. Generally, the propellant measurement is carried out by means of a satellite center of mass station.

[0003] However, for some satellites that do not have online weighing measurement adjustment, the conventional propellant filling method will lead to the inability to accurately fill the tank

On the one hand, the initial propellant filling amount of the tank will affect the accuracy of satellite propellant remaining measurement, and on the other hand, it will also affect the balance discharge of parallel tanks

If the difference in the initial filling amount of the parallel storage tanks is too large, the center of mass of the satellite will be deflected, which will affect the attitude control of the satellite in severe cases, and the loss of too much propellant will affect the life of the satellite

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