Maneuver control at high angle of attack based on real-time optimization of integrated aero-propulsion
Juan Fang, Qiangang Zheng, Changpeng Cai, Haibo Zhang
Abstract
To reduce the propulsion system installation thrust loss under high angle of attack maneuvering, a control method based on real-time optimization of the integrated aero-propulsion is proposed. Firstly, based on data fitting and physical principle, an integrated onboard model of propulsion system is established, which can calculate various performance parameters of the propulsion system in real time, and has high accuracy and real-time performance. Secondly, to improve the compatibility of optimization real-time performance and search accuracy, the online optimization control of aero-propulsion system is realized based on an improved trust region algorithm. Finally, by controlling the auxiliary intake valve, a good match between inlet and engine is realized, which solves the problems of intake flow reducing and total pressure recovery coefficient declining, and improves the installation performance of propulsion system. The simulation results indicate that, compared with the conventional independent engine control, the real-time integrated optimization method reduces the installed thrust loss by 3.61% under the design condition, and 4.58% under the off-design condition. Furthermore, the simulation on HIL (Hardware-In-the-Loop) platform verifies the real-time performance of integrated optimization method.