60t级液氧/甲烷发动机起动过程建模与仿真  

Modeling and simulation of start-up process of 60 t class LOX/methane liquid rocket engine

作　　者：王珺[1] 张卫红[1] 石文靓 郑大勇[1] 

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《火箭推进》2013年第5期16-22,共7页Journal of Rocket Propulsion

基　　金：国家863项目(2006AA702067)

摘　　要：为制定可靠的发动机起动程序,围绕60 t级液氧/甲烷发动机起动瞬态特性开展了一系列建模和仿真研究。介绍了60 t级液氧/甲烷发动机系统方案,列举了发动机系统仿真模型,搭建了全系统瞬态特性仿真平台。根据仿真结果选取了箱压下点火起动方案,提出了设置甲烷涡轮燃气旁通以降低亚临界两相气阻风险的解决方案。试验结果表明,发动机主要性能参数的计算结果与试验数据一致性较好。To make a reliable engine start-up program, a series of modeling and simulation for the start-up transient characteristics of 60-ton-thrust LOX/methane rocket engine was performed. A sys- tematic scheme for 60-ton-thrust LOX/methane rocket engine is introduced in this paper. The simula- tion models were enumerated and a simulation platform was established for the transient characteris- tics of the whole system. According to the simulation results, the ignition/start-up scheme in reservoir pressure was selected. The solution of setting up a methane turbine inlet bypass is presented for de- creasing two-phase flow acceleration pressure drop. The test results show that the simulation results are well in line with the ground test data of main parameters.

关 键 词：液氧 甲烷发动机 起动过程 瞬态特性 系统仿真 

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]