电动泵压式发动机系统方案与性能评估  

System scheme and performance evaluation of an engine fed by electric pump

作　　者：王丹 陈宏玉 周晨初 WANG Dan;CHEN Hongyu;ZHOU Chenchu(Science and Technology on Liquid Rocket Engine Laboratory,Xi＇ an 710100,China)

机构地区：[1]液体火箭发动机技术重点实验室,陕西西安710100

出　　处：《火箭推进》2018年第2期28-32,共5页Journal of Rocket Propulsion

基　　金：国家自然科学基金(51506157)

摘　　要：提出了一套电动泵压式液体火箭发动机系统方案,编写了发动机评估程序,能够预估给定推力、混合比、室压条件下,发动机比冲及各组件质量。研究结果表明,电动泵发动机适合作为长时间工作的动力;存在与室压相关的临界时间点,系统工作时间大于该时间点时电动泵发动机相比燃气发生器循环质量更轻;室压大于2 MPa,工作时间大于317 s时,电动泵系统具备质量优势。A system scheme of liquid rocket engine fed by electric pump is put forward. A program for engine performance evaluation is compiled, which could be used to predict the specific impulse of the engine and quality of each component under the conditions of given thrust, mixing ratio and combustion chamber pressure. The research results show that the engine fed by electric pump is suitable for the upper stage engine with long working hours, has a critical time point relevant to combustion chamber pressure, and its cycle mass is lighter than that of gas generator when working time is greater than the point. The e- lectric-pump feed system always has the mass performance advantage when combustion chamber pressure is higher than 2 MPa and working time is longer than 317 s.

关 键 词：质量评估 系统方案 液体火箭发动机 电动泵 燃气发生器 性能分析 

分 类 号：V430-34[航空宇航科学与技术—航空宇航推进理论与工程]