Cryogenic propellant space in-orbit extrusion separation thermodynamic exhaust system

Abstract

A cryogenic propellant space in-orbit extrusion separation thermodynamic exhaust system comprises a cryogenic propellant storage tank, and an outlet of the cryogenic propellant storage tank is connected with an inlet of a porous pipeline in an extrusion separation piece in the storage tank through a valve. A helium gas inlet of the storage tank is connected with an outlet of a helium gas booster jar through a valve, and a helium gas outlet of the storage tank communicates with a vacuum environment through a valve. An outlet of the extrusion separation piece is divided into two streams, one stream enters an inside pipe of a double-pipe heat exchanger in the cryogenic propellant storage tank through a pipeline, the other stream flows through a throttling valve and then enters an outside pipeof the double-pipe heat exchanger in the cryogenic propellant storage tank through a pipeline, and the first stream is connected with a jetting pipeline after the heat of the first stream is absorbedby the second stream. Extrusion separation and the space background vacuum environment are adopted for replacing the function of a small low-temperature liquid pump, the pressure of the space in-orbit cryogenic propellant storage tank is effectively managed, and a pressure control system becomes lighter, simpler and more reliable.

Description

technical field [0001] The invention relates to the technical field of low-temperature propellant space storage, in particular to a thermodynamic exhaust system for on-orbit extrusion and separation of low-temperature propellant space. Background technique [0002] Cryogenic propellants (such as liquid hydrogen, liquid oxygen, liquid methane, etc.) have become the most widely used group of propellants for large launch vehicles due to their advantages of non-toxicity, pollution-free, low cost, high specific impulse, and high thrust. The specific impulse is 30% to 40% higher than that of normal temperature propellants. However, during the on-orbit storage of the low-temperature propellant space, due to the continuous leakage of external heat intrusion, even if the most advanced low-temperature insulation technology is used, it is still impossible to avoid the temperature rise of the propellant caused by the heat intrusion, and then gasification, resulting in storage The tank ...

AI Technical Summary

Problems solved by technology

However, through experiments and calculations, it is found that the TVS system still has the following deficiencies: a low-temperature liquid acquisition device is required to ensure that the fluid entering the inlet of the small cryogenic pump is a liquid without air inclusions, which will make the whole system more complicated and less reliable. reduce the overall quality; a small cryogenic liquid pump is required, and the addition of dynamic equipment will make the performance of the entire system more unreliable, with more uncertainties and additional energy to drive

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