Research On System Modeling And Control Of Aviation Electric Fuel Pump

In the field of aviation,more-electric aircraft engine technique has become one of the important trends of the advanced aerospace propulsion technology.Aviation electric fuel pump,as the main component of the fuel supply system,has a great influence on the performance of the power control system.In this thesis,the model of aviation electric fuel pump and its control system was built.According to the requirements of the aero power plant control system,the control technology of electric fuel pump was studied.First,working principle and performance requirement of the aviation electric fuel pump were analyzed.Mathematical model and speed governing principle of the fault-tolerant permanent magnet motor were studied.Analysis of the working principle,fuel flow characteristics and main performance parameters of the gear pump was established.Next,in this thesis,the double closed-loop vector control system of electric fuel pump fuel was proposed based on motor current inner loop and pump flow outer loop.PI controller of the vector control system and its parameters were designed.Flow pulsation model and real-time dynamic torque calculation method of the gear pump were studied.Using MATLAB/Simulink,modeling and simulation of the electric fuel pump and analysis about characteristics of the fuel supply system were carried out.Then,combined with the advanced control theory,a new sliding mode controller based on power variable exponent reaching law and dynamic switching surface was designed.Based on BP neural network,a PI controller whose parameters can be adjusted online was designed.Based on sliding mode theory and deep belief network,an adaptive controller was proposed.Study about steady-state performance,dynamic characteristis and robustness of the controllers was completed by simulation.Finally,the integrated structure of the electric fuel pump was designed.Based on the existing experimental platform in the laboratory,speed regulation experiments on the fault-tolerant permanent magnet motor under controllers of PI and sliding mode were carried out.The feasibility of the vector control system and the characteristics of the two control methods were verified.