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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 the most promising hypersonic aircraft power plant, with excellent performance thrust control system to ensure the safety of the aircraft autonomous flight. In order to realize the numerical analysis of the thrust characteristics at different Mach numbers, an engine model consisting of a precursor, an intake port, an isolation section, a combustion chamber and a tailpipe is established according to the flight slope, and the change of the gas flow momentum through the engine inlet and outlet To calculate the engine thrust. At the same time, in order to ensure the stability of the thrust system, according to the classical control algorithm, the fuel inner ring PD control loop and thrust outer loop PI control loop are designed. The closed-loop simulation results show that the thrust control system has a good control effect and can simulate the real control loop well.