推进剂利用系统对液体火箭发动机性能的影响分析  

ANALYSIS OF THE EFFECTS OF PROPELLANT-UTILIZATION CONTROL SYSTEM ON THE LIQUID ROCKET ENGINE PERFORMANCE

作　　者：沈赤兵[1] 吴建军[1] 陈启智[1] 

机构地区：[1]国防科技大学航天技术系,长沙410073

出　　处：《推进技术》1997年第6期14-18,40,共6页Journal of Propulsion Technology

基　　金：国防科技大学试验技术研究资金

摘　　要：建立了带有推进剂利用系统的泵压式液体火箭发动机稳态工况的非线性数学模型，用非线性优化方法和小偏差方法计算分析了推进剂刮用系统调节阀所控制的燃料流量对液体火箭发动机性能的影响，并对比分析了计算结果。所得结论可用于泵压式液体火箭发动机的控制和调节、试验结果分析、可靠性分析、故障分析，也可用于揭示发动机参数随各种干扰因素的变化规律。A nonlinear mathematical model for the steady state operation of a pump-fed liquid rocket engine with a propellant-utilization contro1 system is set up. The effects of fuel mass flowrate of the fuel control valve in the propellant-utilization control system on the performance of liquid rocket engine are computed and analyzed by using both the nonlinear optimization method and the linear method, and the comparative analysis is also carried out for the computed results. The results obtained can be used for the control and regulation of pump-fed liquid rocket engine, the analysis of rocket engine test results, the reliability analysis and the fault analysis, and also for bringing to light the variation of the engine parameters with various interfering factors.

关 键 词：液体推进剂 火箭发动机 稳态工况 利用系统 

分 类 号：V434.23[航空宇航科学与技术—航空宇航推进理论与工程]