甲基肼/四氧化二氮发动机脉冲工况仿真与试验研究  

Numerical and Experimental Analysis of Pulse Mode Characteristics in a MMH/NTO Rocket Engine

作　　者：汪凤山[1,2] 姚兆普 刘阳[1,2] 张榛 蔡坤 王平[1,2] 毛晓芳 杨柳[1,2] Wang Fengshan;Yao Zhaopu;Liu Yang;Zhang Zhen;Cai Kun;Wang Ping;Mao Xiaofang;Yang Liu(Beijing Institute of Control Engineering,Beijing 100094,China;Beijing Engineering Research Center of Efficient and Green Aerospace Propulsion Technology,Beijing 100094,China)

机构地区：[1]北京控制工程研究所,北京100094 [2]北京市高效能及绿色宇航推进工程技术研究中心,北京100094

出　　处：《空间控制技术与应用》2021年第4期56-62,共7页Aerospace Control and Application

基　　金：国家自然科学联合基金资助项目(U1837211);“十三五”民用航天技术预先研究项目(D010305)。

摘　　要：基于简化化学反应模型,对甲基肼/四氧化二氮发动机脉冲工况燃烧特性进行了仿真分析,并结合高模热试车对仿真结果进行了对比验证.结果表明:燃烧室压力在3.7 ms时基本达到稳定;而温度场在8 ms左右达到稳定,室压先于温度场达到稳定;燃烧室壁面液膜热流密度先增大后降低,脉冲工况下发动机推力室壁面液膜冷却效果受脉冲宽度影响较大;不同的脉冲宽度下,燃烧室内的压力上升过程相同,关机后的压力下降过程也基本相同,发动机在2.5~3 ms后能够输出较稳定的推力或冲量.A numerical and experimental study of pulse mode characteristics in a MMH/NTO rocket Engine is proposed via a reduced chemical kinetic model including 20 reactions and 23 species devoted to the gas phase reaction of monomethyl hydrazine/nitrogen tetroxide(MMH/NTO).The results show that the combustion chamber pressure reaches stability rapidly,related 3.7ms to 8ms.The chamber wall heat flux first increases and then decreases,and the film cooling efficiency is significantly affected by the pulse width.The combustion chamber pressure increases and decreases similarly in different pulse mode,and the engine can deliver a steady thrust or impulse after 2.5 ms~3 ms.

关 键 词：甲基肼/四氧化二氮 液体火箭发动机 脉冲工况 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]