高室压发动机系统适用性研究  

Applicability Study on Liquid Rocket Engine System under High Chamber Pressure

作　　者：张楠[1] 李进贤[1] 曹琪[1] 张林[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《世界科技研究与发展》2010年第3期342-344,共3页World Sci-Tech R&D

基　　金：国家"863计划"资助项目

摘　　要：应用Gibbs自由能法和喷管冻结流动模型,对双组元液体发动机推力室进行了热力气动计算;以系统总质量为目标函数,建立了姿轨控推进系统仿真模型,分析了推力室压强对系统性能参数的影响。结果表明:在空间尺寸受限条件下,提高推力室压强,可有效缩小推力室尺寸,增加喷管面积比,提高发动机比冲和系统总体性能。但当推力室压强较高时,这种效果减缓,同时推进系统总质量增幅较大,设计时应综合权衡。Using Gibbs free energy method and nozzle frozen flow model, the thermodynamic calculation in bipropellant liquid rocket engine thrust chamber calculation was processed;taking the system gross mass as the objective function, the simulation model of the attitude/orbit control propulsion system was established, and the influence to the system performance parameters caused by chamber pressure was analyzed. The calculation results show that, by enhancing thrust chamber pressure, thrust chamber size could be decreased effectively, and nozzle area ratio could be increased, also the engine specific impulse and system total performance could be advanced when space dimension is limited. But the effect slows down and system gross mass increases obviously when the pressure is higher, so it should be considered generally when designing.

关 键 词：姿轨控推进系统 推力室 高室压 热力计算 性能仿真 

分 类 号：V439.7[航空宇航科学与技术—航空宇航推进理论与工程]