Liquid methane filling system and method of rocket launching system

Abstract

The invention provides a liquid methane filling system of a rocket launching system. The liquid methane filling system of the rocket launching system comprises a liquid methane storage system, a liquid path filling system and a liquid methane discharge treatment system which are connected through a pipeline, the liquid methane storage system is provided with a self-pressurization structure and isconnected with the liquid path filling system through a pipeline; The liquid path filling system comprises two filling pipelines which are redundant to each other, and each filling pipeline comprisesa supercooling control unit and a filling flow control unit which are connected through a pipeline. Mutual standby valves are arranged between pipelines of the two filling flow control units; and theliquid methane discharge treatment system is connected with the filling flow control unit through a pipeline. The filling system is provided with redundant structures such as two filling pipelines, the mutual standby valves, a discharge valve set, a hot methane discharge four-valve set, a hot methane discharge three-valve set and a filling and feeding three-way valve set. Unattended operation in the filling process can be achieved, and the field safety of the launching process is guaranteed.

Description

technical field [0001] The invention belongs to the technical field of rocket propellant filling, and in particular relates to a liquid methane filling system and filling method for a rocket launching system. Background technique [0002] Rocket propellant is usually composed of two chemical substances, fuel and oxidizer, which react in the combustion chamber to violently release heat to propel the rocket. At present, a common liquid propellant combination is to use mixed hydrazine-50 as combustion agent and dinitrogen tetroxide as oxidant. Another combination is to use liquid hydrogen as fuel and liquid oxygen as oxidant. This combination is the most potential combination at present, and its combustion efficiency is very high. [0003] The combined propellant of hydrazine-50 and dinitrogen tetroxide has the disadvantages of low combustion efficiency, high toxicity and high price. Although the combined propellant of liquid hydrogen and liquid oxygen has high combustion eff...

AI Technical Summary

Problems solved by technology

[0003] The combined propellant of hydrazine-50 and dinitrogen tetroxide has the disadvantages of low combustion efficiency, high toxicity and high price.

Although the combined propellant of liquid hydrogen and liquid oxygen has high combustion efficiency, it has the following disadvantages: (1) The boiling point of liquid hydrogen is very low, and the storage temperature at normal pressure is about -252 degrees. and nitrogen can clog pipes, making storage and handling more difficult

(2) Due to the low density of liquid hydrogen, the requirements for the rocket storage tank are very large, which increases the difficulty of launching

(3) Due to the ultra-low temperature of hydrogen, it is very easy to evaporate and escape, and the insulation material of the rocket tank is increased, which increases the launch thrust requirements

[0005] The existing methane filling system has the following disadvantages: it cannot meet the simultaneous filling requirements of the primary and secondary storage tanks of the rocket, the corresponding preparation time before the rocket launch is long, and it lacks a reliable redundant structure; and the use of strong electric equipment may be due to The failure of the electric rotating equipment leads to the failure of the launch. On the other hand, the cost of the launch is high; without the additional measures of pre-launch pre-cooling, the reserve of combustion agent in the rocket tank may be insufficient, and the subsequent launch process cannot be reliably guaranteed.

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