A Design Method of Steady State Control Law for Civil Turbofan Engine

In this article, based on the component method, the engine steady state performance calculation model is established. Based on the model, the performance of the take-off and the high altitude climb of the civil turbofan engine is studied. The influence of the single control law and the combined control law on the engine characteristics is analyzed. Based on the thrust demand of the aircraft at cruise and take-off, the maximum state control law of the engine and the corresponding thrust control law are designed.