火箭推进2023，Vol.49Issue(6)：10-20,11.
双组元150 N自燃推进剂发动机单阀打开脉冲特性
Single-valve opening pulse characteristics of a 150 N hypergolic bipropellant liquid rocket engine
摘要
Abstract
In order to study the effect of single solenoid valve opening on the pulse operating characteris-tics of the bipropellant space liquid rocket engine using hypergolic propellants,the high-altitude simula-ted thermal test of a 150 N engine was carried out with the propellant combination of dinitrogen tetroxide and methyl-hydrazine.The pulse operating characteristics of the engine were investigated at 20 ms,30 ms,50 ms,and 80 ms pulse widths with both the oxidizer and fuel path solenoid valves open at the same time and separately,and the pulse control period was 160 ms.The test results show that the average thrust impulses of the engine at 20 ms and 30 ms pulse widths are 0.35 N·s and 0.41 N·s when only the oxygen control valve is opened,which are 11.08％and 9.51％of the corresponding normal operating conditions.The average thrust impulses at 50 ms and 80 ms pulse widths are 0.47 N·s and 0.63 N·s,which are 6.20％and 5.33％of the corresponding normal operating conditions.The dinitrogen tetroxide undergoes violent flash vaporization.When the fuel control valve is opened only,the average thrust impul-ses of the engine at 20 ms and 30 ms pulse widths are 0.17 N·s and 0.18 N·s,which are 5.38％and 4.18％of the corresponding normal operating conditions,and the methyl-hydrazine flows out from the nozzle outlet edge in liquid state.When the pulse widths increase to 50 ms and 80 ms,the incomplete flash vaporization of methyl-hydrazine occurs,and the average thrust impulse of the engine gradually increases with the increase of pulse width.The average thrust impulses of the engine are 0.22 N·s and 0.31 N·s,which are 2.90％and 2.62％of the corresponding normal operating conditions.The thrust impulse generated by the engine pulse operation when the single control valve is opened is mainly related to the degree of propellant flash vaporization.关键词
空间液体火箭发动机/自燃推进剂/单路电磁阀/脉冲工作特性/推力冲量/闪蒸雾化Key words
space liquid rocket engine/hypergolic propellant/single-way solenoid valve/pulse charac-teristic/thrust impulse/flash vaporization分类
航空航天引用本文复制引用
陈锐达,王鹤茗,徐辉,陈泓宇,宣晓萍..双组元150 N自燃推进剂发动机单阀打开脉冲特性[J].火箭推进,2023,49(6):10-20,11.基金项目
"十四五"装备预研共用技术项目(50922010801) （50922010801）
