液体火箭冷氦增压系统低温试验研究

摘要

In order to study the pressurization performance of the combination for solenoid valve and orifice in liquid rocket cryogenic helium pressurization system, experiment was conducted with cryogenic helium in liquid hydrogen temperature. Liquid oxygen was vented to simulate the propellant consumption in the rocket tank. The pressurization performance of this combination was obtained through analysis of mass flow-rate and propellant tank pressure. The experiment results show that the combination of solenoid valve and orifice can maintain the propellant tank pressure on the designed level, this combination was a simple, reliable and feasible pressurization mode for liquid rocket.%为研究液体火箭低温氦增压系统中电磁阀与孔板组合方式的增压性能和优化孔板的设计,开展了使用液氢温区的氦气作为增压介质的冷氦增压系统试验,并通过排放液氧模拟火箭贮箱内液氧的消耗.通过分析试验过程中增压氦气流量和贮箱压力的情况,获得了该增压方式对贮箱的增压性能.试验结果表明电磁阀与孔板组合能将贮箱压力维持在设计范围内,是一种简单、可行的液体火箭液氧贮箱增压方案.