Space propulsion system with propellant and pressurized gas discharge

Abstract

A space propulsion system with a propellant and a pressurized gas discharge device of the present invention includes a high-pressure gas cylinder, a gas circuit electric explosion valve, a pressure reducing valve, a gas circuit self-locking valve, a liquid circuit electric explosion valve, and a propellant storage tank. , Liquid circuit self-locking valve, discharge port; two high-pressure gas cylinders and propellant storage tanks are connected by pipelines, and gas circuit gas circuit electric explosion valves and pressure reducing valves are arranged in sequence on the pipelines; On the pipeline between the pressure reducing valve and the propellant storage tank; the two liquid circuit electric explosion valves are respectively connected to the two propellant storage tanks, which play the role of pipeline blowing and pressurized gas discharge; The lock valve is connected to the outlet of the two storage tanks. After the first operation, the propellant and pressurized gas are discharged, and the second operation closes the discharge system. The invention realizes that the discharge process can be controlled, and the self-locking valve is closed to stop or restart the discharge process after the discharge process is started; and the system is closed after the discharge process is completed.

Description

technical field [0001] The invention relates to the technical field of spacecraft propulsion, in particular to a space propulsion system with a propellant and pressurized gas discharge device. Background technique [0002] In order to achieve a safe landing at the end of the aircraft's life, it is required that pressurized gas and propellant be exhausted from the inside of the system at a specific time and altitude before landing. [0003] The method currently adopted is to use two electric explosion valves to realize the opening of the propellant and pressurized gas discharge system. There is no closing function design, and it is impossible to completely ensure that the residual propellant does not leak when the aircraft lands. At the same time, the reliability of the currently adopted solution for isolating the gas-liquid circuit by the rupture diaphragm is not high, and the rupture diaphragm may rupture in advance due to the influence of the working process of the system....

AI Technical Summary

Problems solved by technology

[0003] The current method is to use two electric explosion valves to realize the opening of the propellant and pressurized gas discharge system, without the design of the closing function, it is impossible to completely ensure that the residual propellant does not leak when the aircraft lands

At the same time, the reliability of the currently adopted rupture diaphragm isolation gas-liquid circuit scheme is not high, and the rupture diaphragm may rupture early due to the influence of the system working process

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