| Citation: | WEI Qiang, LIANG Guozhu. Performance simulation of a 76 km simulated high-altitude test system for liquid attitude-control engines[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(9): 1779-1788. doi: 10.13700/j.bh.1001-5965.2016.0754(in Chinese)
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To study the performance of a 76 km high-altitude test system for attitude-control liquid rocket engines, a transient test system simulation model with lumped parameters was built, which considers the phase change of the exhaust. The system model consists of a vacuum pumping sub-model, a liquid nitrogen flow sub-model and a condensing pipe sub-model. The sub-models were coupled through the heat and mass transfer process between the gas, frost and liquid nitrogen. The system working parameters during the steady and the pulsed tests of a bipropellant nitrogen-tetroxide/mono-methylhydrazine attitude-control engine were calculated, and effects of the important system design parameters on working performance were explored. The results show that the current test system could provide environment for the engine pulse tests and 6×104 s steady tests with a maximum propellant flow rate of 6.4 g/s (trust is about 16.5 N); in long-term test, the frost on the surface of condensing pipes will get saturated and lose the ability to absorb carbon dioxide and water vapor, leading to the gradually increase of the vacuum tank pressure; during the engine pulsed test, the vacuum tank pressure will fluctuate with the pulses, up to about 70% in the 15 ms pulse case. The conclusion of the study could be a guide in the design and upgrade of the high-altitude test system for the liquid attitude-control engines.
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