Method for actively regulating mixture ratio of spacecraft propellant

Abstract

A method for actively regulating mixture ratio of a spacecraft propellant comprises the following steps: conducting trial run before installing an engine with high consumption into a spacecraft propelling system, determining working parameters, and reaching a standard mixture ratio of an oxidant to fuel at a standard inlet pressure by regulating system hardware; arranging a pressure sensor at an oxidant and fuel inlet, and arranging a self-locking gas supply valve on pressurizing pipelines at the upstream of an oxidant storage tank and a fuel storage tank respectively; and in the working process of the engine, acquiring pressure parameters of the fuel and the oxidant at the inlet of the engine in real time through a propelling system controller, and comparing and regulating the pressure parameters to control the pressures of the two propellants at the inlet of the engine to be very close, so that the deviation level of the total mixture ratio of the propellant can be controlled. By the method, the utilization ratio of the propellant of the spacecraft propelling system is effectively improved, so that the service life of a spacecraft is prolonged, the effective load mass of the spacecraft is improved and the production cost of the spacecraft is reduced.

Description

technical field [0001] The invention relates to the technical field of spacecraft propulsion, in particular to a method for actively adjusting the mixing ratio of spacecraft propellants. Background technique [0002] The function of the spacecraft propulsion system is to provide the spacecraft with the thrust required for orbit change and attitude control. For spaceships, large-scale artificial satellites, and deep-space probes, bicomponent propulsion systems are widely used at home and abroad at present, carrying two kinds of propellants (respectively oxidizer and fuel), which are burned to generate thrust. The mixing ratio refers to the mass flow ratio of oxidizer and fuel when the engine is working. The propellant loading amount is designed according to the standard mixing ratio. When the mixing ratio deviates from the standard design value during use, a certain kind of propellant will inevitably be left in the end. The remaining propellant cannot be burned by itself and...

AI Technical Summary

Problems solved by technology

[0004] Aiming at the technical solutions in the above-mentioned prior art, the present invention provides a method for actively adjusting the propellant mixing ratio of a spacecraft. This method consumes the two propellants according to the standard ratio, thus overcoming the large amount of propellant remaining, which is easy to cause propulsion Disadvantages of low effective dosage of agent

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