Active evaporation control method applicable to long-term on-orbit storage of cryogenic propellant

Abstract

The present invention relates to an active evaporation control method applicable to long-term on-orbit storage of a cryogenic propellant. According to the method, an active evaporation control device that comprises a composite thermal insulating layer, a steam cooling shield, a heat exchanger, a throttling assembly, a circulating pump, a bypass valve and a steam cooling shield exhaust valve is installed for a propellant storage tank. According to the present invention, with the developed active evaporation control method for a cryogenic propellant, discharge of a small amount of simple gaseous propellant can be achieved under the circumstance of uncertain gas-liquid position under microgravity condition, and pressure control on the cryogenic propellant storage tank and control on evaporation of the cryogenic propellant may be effectively realized under dual action by fully using thermodynamic enthalpy of the discharged cryogenic propellant after being throttled; and the method can allow effective reduction of evaporation loss of the cryogenic propellant in on-orbit use, thus prolonging the on-orbit mission time of a spacecraft.

Description

technical field [0001] The invention relates to an active control method suitable for long-term on-orbit storage of low-temperature propellant, which is suitable for the design of a spacecraft low-temperature storage system and realizes long-term on-orbit storage of low-temperature propellant. Background technique [0002] Cryogenic propellants have been widely used in launch vehicles and upper stages at home and abroad because of their high specific impulse, non-toxic, non-polluting, and relatively low price. Cryogenic propellant is considered to be the most economical and efficient chemical propellant for entering space and orbit transfer, and it is also the preferred propellant for future human lunar exploration, Mars exploration and longer-distance deep space exploration. Although low-temperature propellant has high performance, its boiling point is low (liquid hydrogen -253°C, liquid oxygen -183°C), and it is easy to evaporate due to heat, so it is difficult to store fo...

AI Technical Summary

Problems solved by technology

[0003] The evaporation of low-temperature propellant will increase the pressure of the spacecraft storage tank rapidly. In order to ensure the normal working pressure in the tank, the evaporated gas must be continuously discharged, which will cause a large amount of ineffective loss of low-temperature propellant.

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