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Research on Propellant Supply Technology of Large Propulsion Hydrogen-Oxygen Rocket Engine Testing

Author: ChenChunFu
Tutor: LiuWeiQiang；ZhangKuiHao
School: National University of Defense Science and Technology
Course: Aerospace engineering
Keywords: Propellant technology Precooling filling Level imbalance Unsteady flow
CLC: V434
Type: Master's thesis
Year: 2007
Downloads: 110
Quote: 0
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Abstract


The large thrust the hydroxide engine is in China in the future development of a satellite, deep space exploration and manned space vehicle, the most important one of the power plant. Engine test runs through the whole process of engine development, is the primary means of testing the engine various performance indicators. The propellant supply technology is one of the core technology of the entire test system, which involves the propellant tank, pipeline system, automatic pressurization system and gas distribution systems and other subsystems Research and Application. Based on domestic and foreign high-thrust engine test hydroxide the propellant supply of lack of specific research status and ground tests need of safe and reliable operation of key technology research. By theoretical analysis of the system, the integrated use of mathematical and physical methods, drawing on years of calculation model and experimental correlations, to determine cryogenic tank volume, calculated propellant supply main pipe diameter, scientific and reasonable supercharged to study big thrust hydroxide engine cryogenic propellant precooling filling the new technology to identify the quality of the temperature of the liquid hydrogen liquid oxygen filling time and media consumption controllable influencing factors; pressurized orifice plate and pneumatic membrane by fluid mechanics theory, the flow control valve characteristics, according to the similarity criteria of the Re, the low temperature debug piping cryogenic hydraulic characteristics, and to find new ways to reduce the test cost; unsteady flow of the cryogenic fluid, engine test process starting pressure pit, and shut down water hammer phenomenon, the setting and the formulation of the test program to provide a reliable basis for tank pressure. Thrust hydrogen-oxygen engine test with increasing thrust, flow, and liquid hydrogen usage greatly improved, due to the impact of manufacturing technology, transportation, installation and fixed factors, the propellant supply system can only use multiple liquid hydrogen tank parallel use short-range test table test level imbalances. Both through theoretical analysis and experimental, explored the optimal solution to solve the problem, pressure by adjusting the tank of the box, completely solve the uneven flow of liquid hydrogen tank, and passed the test test. The results show that, despite its unique characteristics of liquid hydrogen liquid oxygen, high-thrust the hydroxide engine ground test conditions under part of the commonly used model of classical fluid mechanics, heat transfer theory and previous research and experimental correlations in a large thrust hydrogen engine test the propellant supply of technology can be applied.

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CLC: > Aviation, aerospace > Aerospace ( Astronauts ) > Propulsion system ( engine, propeller ) > Liquid propellant rocket engine
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