某型二级发动机混合比调节特性分析  

Analysis on characteristics of mixture ratio regulating system in a second-stage rocket engine

作　　者：刘上[1] 韩红伟[1] 王运卯[1] 王艺杰[1] 熊莉芳[1] 程晓辉[1] 叶力华[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2016年第2期6-12,共7页Journal of Rocket Propulsion

基　　金：国家863项目(2012AA702302)

摘　　要：为了提高火箭运载能力,常规二级发动机设置了混合比调节系统。通过建立发动机系统非线性静态特性仿真模型,并结合地面试车数据,开展发动机混合比调节特性分析。结果表明:发动机的混合比调节范围达到-3.13%^+3.20%,完全满足火箭推进剂利用系统的要求,且有一定的余量;混合比调节系统既达到了调节发动机混合比的目的,又能保持发动机的推力基本不变。采用静态仿真模型可以很好地描述发动机稳态工作过程中的混合比调节特性,具有较高的精度。A mixture ratio regulating system is added to the second-stage liquid rocket engine to improve its payload. The mixture ratio regulating characteristics of the engine are analyzed by the non-linear steady simulation model and the hot-test data of the engine system. The analysis results show that the mixture ratio regulating range covers from -3.13% to 3.20%, which completely agrees with the requirement of the rocket propellant utilization system and has a certain margin. With the mixture ratio regulating system, the regulating target of the mixture ratio is satisfied, while the engine thrust is kept. The model in this paper can simulate the mixture ratio regulating characteristics and has high precision in the steady operation process of the engine.

关 键 词：二级发动机 混合比 调节特性 仿真模型 

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]