超燃冲压发动机推力控制系统仿真研究  

Simulation of Thrust Control System for Scramjet

作　　者：崔曼曼 黄耀 

机构地区：[1]中国航发航空动力控制系统研究所,江苏无锡214063

出　　处：《航空发动机》2017年第1期17-20,共4页Aeroengine

基　　金：国家重大基础研究项目资助

摘　　要：超燃冲压发动机是最具发展潜力的高超声速飞行器动力装置,具备性能优良的推力控制系统才能保证飞行器的安全自主飞行。为了实现在不同马赫数下的推力特性数值分析,根据飞行坡面建立由前体、进气道、隔离段、燃烧室和尾喷管组成的发动机模型,并通过发动机进、出口的气流动量变化来推算发动机推力。同时为保证推力系统的稳定,根据经典控制算法设计了燃油内环PD控制回路和推力外环PI控制回路。闭环仿真结果表明:该推力控制系统的控制效果良好,能较好地模拟真实控制回路。Scramjet is expected to be one of the most potential propulsion systems for hypersonic vehicle. The thrust control system of high performance was designed to guarantee safety autonomous flight. In order to perform the numerical simulation of thrust characteristics at different Mach number, the model of scramjet was designed which was composed by precursor model, air inlet, isolator, firebox and jet nozzle. According to the inlet and outlet flow change, the thrust of scramjet was calculated. Simultaneously, in order to ensure the stabilization of thrust system, the inner PD fuel control loop and outside PI thrust control loop were designed based on classical control algorithm. The simulation result shows that the control effect of thrust control system is good and the system can simulate the control loop in fact.

关 键 词：超燃冲压发动机 燃油控制 推力控制 发动机模型 航空发动机 

分 类 号：V233.7[航空宇航科学与技术—航空宇航推进理论与工程]