阀门开启时差对150N自燃推进剂发动机工作过程的影响  

Effect of valve opening time difference on working process of 150 N hypergolic propellant liquid rocket engine

作　　者：陈锐达 田增 陈泓宇 徐辉 CHEN Ruida;TIAN Zeng;CHEN Hongyu;XU Hui(Shanghai Institute of Space Propulsion,China Aerospace Science and Technology Corporation,Shanghai 201112,China;Shanghai Engineering Research Center of Space Engine,Shanghai 201112,China)

机构地区：[1]中国航天科技集团有限公司上海空间推进研究所,上海201112 [2]上海空间发动机工程技术研究中心,上海201112

出　　处：《航空动力学报》2024年第9期384-395,共12页Journal of Aerospace Power

基　　金：“十四五”装备预研共用技术项目(50922010XXX)。

摘　　要：为了研究阀门较大开启时差对采用自燃推进剂的空间液体火箭发动机工作过程的影响,对150 N发动机开展高空模拟热试车,考察了氧阀、燃阀分别先开40、100、500、1000 ms对发动机工作稳定性、点火推力峰值和响应时间的影响。试验结果表明,发动机均可以成功点火,稳定后的推力值基本不变。氧阀先开、燃阀先开时的点火推力峰值分别约为稳定推力的1.01~1.05倍和1.04~1.07倍,与两阀同步信号开启时相当。燃阀先开时,启动响应时间延长了约16 ms。阀门单独打开时,氧化剂发生了充分闪蒸,流场中部夹杂冰粒喷出,燃料发生了部分闪蒸。当阀门开启时差达到500、1000 ms时,氧阀、燃阀单独打开过程中,输出推力分别约11、6 N,分别占稳定推力的7%和4%,且后者输出推力呈现波动下降的趋势。In order to study the effect of the valve opening time difference on the working process of the space liquid rocket engine using hypergolic propellants,the high-altitude simulated thermal test of a 150 N engine was carried out.The engine working stability,ignition thrust peak and response time were investigated when the oxidant valve and fuel valve were opened 40,100,500,1000 ms in advance,respectively.The test results showed that the engine can be successfully ignited,and the thrust after stabilization was basically unchanged.When the oxidant valve and the fuel valve were opened first,the ignition thrust peak of the engine was about 1.01—1.05 times and 1.04—1.07 times of the stable thrust,respectively,which was equivalent to the opening of the two-way valve synchronous signal.When the fuel valve was opened first,the startup response time was extended by about 16 ms.When the valve was opened alone,the oxidant was fully vaporized,the ice particles were ejected in the middle area of the flow field,and the fuel was partially vaporized.When the valve opening time difference reached 500 ms and 1000 ms,while the oxidant valve and the fuel valve were opened separately,the output thrust of the engine was about 11 N and 6 N,respectively,accounting for 7%and 4%of the stable thrust respectively,and the output thrust of the latter fluctuated and kept falling.

关 键 词：液体火箭发动机 阀门开启时差 工作稳定性 点火推力峰 启动响应时间 推进剂闪蒸 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]