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A three-gas supercharging system applied to liquid rockets

A technology for liquid rockets and supercharging systems, applied in rocket engine devices, jet propulsion devices, machines/engines, etc., can solve problems such as inability to meet high efficiency and low quality, and achieve reduced development risks, high reliability, and low system quality. Effect

Active Publication Date: 2018-01-05
BEIJING INST OF ASTRONAUTICAL SYST ENG +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The traditional supercharging method is more or less unable to meet the characteristics of high efficiency and low quality. Seeking a more efficient and lower quality supercharging method is one of the requirements for future low-cost and high-capacity launch vehicle system solutions

Method used

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  • A three-gas supercharging system applied to liquid rockets
  • A three-gas supercharging system applied to liquid rockets
  • A three-gas supercharging system applied to liquid rockets

Examples

Experimental program
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Effect test

Embodiment

[0041] According to the supercharging pressure requirements of the storage tank during rocket flight, the scheme design and supercharging calculation of the triple gas supercharging system are carried out to meet the supercharging demand and complete the system design. The specific implementation is as follows:

[0042] a) According to the boost pressure requirement of a certain type of rocket, the temperature of the air pillow and the volume of the storage tank, the total amount of helium in the pressurized gas is preliminarily calculated by using the gas state equation. According to the temperature required for pressurized helium, the mixing ratio and dosage of hydrogen and oxygen are obtained through preliminary calculation from the specific heat of helium and the heat of reaction of hydrogen and oxygen. On this basis, select the cylinder pressure and design the cylinder volume. Since the stage flow control unit with solenoid valve and orifice plate is used, in order to en...

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Abstract

The invention relates to a trimix pressurization system applied to a liquid rocket. The trimix pressurization system comprises a helium and hydrogen bottle (1), an oxygen bottle (2), a flow control unit and a catalytic bed (5), wherein mixed helium and hydrogen are stored in the helium and hydrogen bottle (1) in advance; oxygen is stored in the oxygen bottle (2); flow of gas output in the two bottles is controlled through the flow control unit; a mixed gas of output helium, hydrogen and oxygen is subjected to catalytic reaction through the catalytic bed (5); oxygen and hydrogen react to generate water vapor and release hat; and helium, water vapor and oxygen remaining after reaction are heated and enter a storage tank to pressurize the storage tank.

Description

technical field [0001] The invention relates to a technical scheme and a design method of a light-weight and high-efficiency liquid carrier rocket propellant storage tank pressurization system. Background technique [0002] During the flight of the launch vehicle, as the propellant is delivered to the engine for combustion, the air pillow in the propellant tank gradually increases. If the gas volume in the air pillow does not increase, the pressure of the air pillow will gradually decrease. For the certain pressure required for the propellant to enter the rocket engine and the requirement for the rocket tank to maintain a certain rigidity, it is necessary to continuously replenish the air pillow of the propellant tank to maintain the pressure of the tank. This is what the booster system of the launch vehicle requires. completed tasks. Common pressurization systems for launch vehicle tanks can be divided into two categories according to the source of the medium. One category...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/50F02K9/60
CPCF02K9/50F02K9/60
Inventor 帅彤张立强修建生周浩洋吴俊峰杜正刚李德权马方超吴姮孙善秀王剑中王道连丁建春
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG
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