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所属单位：能源与动力学院

发表刊物：IEEE Access

摘要：To provide the desired thrust and prevent the engine from exceeding any safety or operational limits, a min-max selector with linear limiters is widely employed in current aircraft engine control logic. However, with the further requirements of engine performance, the traditional linear limiters should be improved. Though there are many researchers working on the development of improvement methods, none of those methods consider the limitation of core shaft acceleration. In this paper, a novel control scheme for aircraft engine based on sliding mode control with acceleration/deceleration limiter is proposed. Above all, the controller construction process is introduced, and the asymptotic stability of the whole controller is given. Then, with linearized model of JT9D turbofan engine, the control performance of the new approach is presented, which is also compared with the traditional methods. The simulation results show that the proposed method is efficient, and it can ensure all outputs of the controller, including the core shaft acceleration Nc, high-pressure turbine outlet temperature increment Δ T48, high-pressure compressor stall margin increment Δ SmHPC, and so on, are well controlled. © 2018 IEEE.

是否译文：否

发表时间：2019-01-01

合写作者：Ke, Hongwei,Shu, Wenjun,张天宏

通讯作者：于兵