补燃循环发动机推力调节过程建模与仿真研究  

Modeling and simulations on the thrust regulation process of staged combustion cycle rocket engine

作　　者：陈宏玉[1] 刘红军[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》2014年第1期18-24,共7页Journal of Rocket Propulsion

基　　金：国家863项目(2012AA702302)

摘　　要：以补燃循环液氧煤油发动机为研究对象,对其推力调节特性进行了研究。建立了描述补燃循环发动机瞬变过程的数学模型,提出了求解供应系统管路内液体瞬变流控制方程的Chebyshev伪谱方法,应用该模型对补燃循环液氧煤油发动机的推力调节特性进行了仿真计算,并将计算结果与试验数据进行了对比分析,验证了模型和算法的合理性。研究结果表明:对于所研究的补燃循环发动机系统而言,通过调节发生器中较少组元的流量,改变涡轮泵的功率,可很好地实现调节推力的目的,且该推力调节系统具有良好的动态调节品质和很强的抗干扰性。The thrust regulating characteristics of the staged combustion cycle LOX/kerosene engine were investigated. The mathematical model of transient process of the engine was developed based on modular modeling means. The nonlinear hyperbolic partial differential equations governing the unsteady flow of pipelines were solved by the Chebyshev pseudo-spectral method. The thrust regulation process of the staged combustion LOX/kerosene Rocket Engine was simulated using the models and the new numerical technique. Results from the numerical simulation agree well with the ground-test data, demonstrating that the methods can accurately predict the transient behavior of the engine. The results show that regulating the less flow rate propellant of the preburner for staged combustion cycle engine can realize thrust regulation. The thrust regulation system has excellent dynamic regulation quality and strong anti-interference ability.

关 键 词：液体火箭发动机 补燃循环 推力调节 数值仿真 Chebyshev伪谱方法 

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]