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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。
In order to study the pressurization performance of the solenoid valve and orifice plate combination in the liquid rocket cryogenic helium pressurization system and to optimize the design of the orifice plate, a cold helium pressurization system test using helium gas in liquid hydrogen temperature zone as pressurization medium was carried out. And simulates the consumption of liquid oxygen in the rocket tank by discharging liquid oxygen. By analyzing the situation of pressurized helium flow rate and tank pressure during the test, the supercharging performance of the supercharging system on the tank is obtained. The test results show that the combination of the solenoid valve and the orifice plate can maintain the tank pressure within the design range, and is a simple and feasible liquid rocket liquid oxygen tank pressurization scheme.