超临界氦加温增压系统试验研究

Experimental Study on Supercritical Helium Heating Pressurization System

为了验证超临界氦加温增压技术在运载火箭上应用的可行性,建立了超临界氦加温增压系统试验平台,开展了增压系统试验。通过分析试验过程中超临界氦贮罐压力和温度、增压孔板入口压力、模拟贮箱内压力等参数的变化规律,获得了超临界氦加温增压系统的增压性能。试验中超临界氦加温增压系统工作压力较小,并且系统中的电磁阀与孔板组合能将贮箱压力维持在设计范围内,表明该系统增压性能稳定,是一种安全可靠的液体火箭增压系统。

For verifying the feasibility and effectiveness of the supercritical helium heating pressurization system, the test platform of supercritieal helium heating pressurization system is designed and built, and experiment is con- ducted. The pressurization performance of this system is obtained through analysis of the pressure and temperature of supercritica] helium dewar and the pressure of orifice inlet and tank. The experiment results show that the super- critical helium heating pressurization system has the advantage of high safety due to the lower working pressure. And the combination of solenoid valve and orifice maintaining the propellant tank pressure on the designed level in- dicates that this pressurization system with stable pressurization performance is a reliable pressurization mode for the liquid rocket.