低温推进剂贮箱增压系统分布参数数值仿真(Ⅱ)增压系统数值模型与仿真结果  

Distributed parameter numerical simulation for the transients of cryogenic propellant tank pressurization system (Ⅱ) Numerical model and simulation results of pressurization system

作　　者：陈阳[1] 张振鹏[1] 杨思锋[2] 瞿骞 陈锋[2] 朱子环[2] 

机构地区：[1]北京航空航天大学宇航学院,北京100083 [2]北京航天试验技术研究所,北京100074

出　　处：《航空动力学报》2008年第2期329-335,共7页Journal of Aerospace Power

摘　　要：在所建立低温推进剂分布参数贮箱模型的基础上,采用液体火箭发动机试验台气路系统模块化建模与仿真软件,对某试验台液氧贮箱增压系统在发动机点火工作段的增压过程进行了仿真研究.仿真结果与试验结果以及经验公式计算结果获得了很好的一致,表明分布参数贮箱模型相对于集中参数模型更为准确全面地描述了低温贮箱内的流动和热分层现象,并表明有限体积模型体系及所开发的仿真软件具有广泛的适用范围和良好的仿真精度,在管路系统仿真领域具有工程应用价值和数值拓展潜力.Based on the distributed parameter numerical model of cryogenic propellant tank, pressurization of a LO2 tank pressurization system during engine firing was simulated by employing the liquid rocket engine test-bed modularization modeling and simulation software-gas system（LRETBMMSS-GS）. The simulation results agree well with test data and experiential correlation prediction, which shows that the distributed parameter tank model is more accurate and comprehensive than lumped parameter model in describing flow and thermal stratification phenomena in cryogenic tank. Accordingly, the numerical system of finite volume model and corresponding simulation software have a wide applicability and good simulation precision, which are valuable and can be developed further in pipe system simulation field.

关 键 词：航空、 航天推进系统 液体推进剂火箭发动机 低温贮箱增压系统 模块化建模 系统动态仿真 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]