摘要
在不考虑传热传质的情况下建立了一种简化的贮箱模型,并采用液体火箭发动机试验台气路系统通用模块化建模与仿真软件对容腔放气过程和某试验台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,计算结果与分析解和试验结果获得了较好的一致,验证了软件的有效性和通用性.对两个系统的建模过程表明软件所采用的模块化建模与仿真方法适用于对复杂管网的建模,在液体火箭发动机系统仿真上具有较好的应用前景.对贮箱增压系统的仿真表明,合理设计PID控制参数并根据经验预置与额定流量相近的调节阀初始开度,对于提高增压系统起动过程的平稳性有利.
A simple model of propellant tank was established by neglecting mass and heat transfer between the propellant and pressurant. Then by employing the modularization modeling and simulation software for liquid rocket engine（LRE） test-bed gas system（LRET- BMMSS-GS）, blowdown of a tank and pressurization of a LO2 tank pressurization system during engine firing were simulated. The simulation results are in good agreement with the analytical solution and test data. Accordingly, the software is validated to be effective and versatile. The progress of modeling two systems shows that the method of MMS is suitable for modeling complicated LRE system and can be used to simulate all kinds of working processes of LRE system. The simulation of LO2 tank pressurization system indicates that PID control parameters should be set reasonably and the initial opening of pneumatic diaphragm control valve should be adjusted to nominal pressurant mass rate, which is effective to improve stability of pressurization starting transient.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第1期96-101,共6页
Journal of Aerospace Power
关键词
航空、航天推进系统
液体火箭发动机
试验台贮箱增压系统
数值仿真
PID控制
aerospace propulsion system
liquid rocket engine（LRE）
tank pressurization system of LRE test-bed
numerical simulation
PID control
