液氧温度对某液氧液氢发动机性能影响研究  

Influence of LOX temperature on LOX/LH_2rocket engine performance

作　　者：姜冬玲[1] 杨莹[1] 

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《火箭推进》2014年第2期54-58,共5页Journal of Rocket Propulsion

摘　　要：结合某液氧液氢发动机实际飞行中二次工作段入口液氧温度升高和推力下降现象,分析了液氧温度对发动机性能的影响方式和修正方法。通过过冷液氧的发动机试验,对液氧温度影响性能的两种方式分别进行了修正,可将某液氧液氢发动机二次工作段推力与一次工作段的偏差降低约24%,将发动机飞行燃烧室压力与交付值的偏差降低约8%。The impacting mode and correction method of LOX temperature at its inlet on engine performance are studied in combination with the phenomena that the LOX temperature at its inlet rose and the thrust dropped down during the second operating period of a LOX/LH2 rocket engine in its actual flying test. According to the test result of a super-cooling liquid oxygen engine, the influence of two impacting modes of LOX temperature on engine performance was corrected, by which the deviation of the LOX/LH2 rocket engine thrust between second and first operating periods was decreased by about 24%, and the deviation of combustor pressure between flying test value and given value before flying was decreased by about 8%.

关 键 词：液氧液氢发动机 液氧温度 干扰因素 非线性计算方法 小偏差计算方法 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]