| Modern power systems have been going through some huge changes due to the rapid development of the power and electron technologies.In the field of aviation,multi-electric aircraft engine technique has become an important research topic during the study of the advanced aerospace propulsion technology.Electric fuel pump,as the core component of the multi-electric aircraft engine,determines the performance of the oil supply system and has an immediate impact on the work of the engine.The thesis focuses on the research of the electric fuel pump on account of the important application values.An external gear pump and a permanent-magnet synchronous motor are chosen as critical pieces of the electric fuel pump.The parameters of the gear pump has been calculated before the structure design of the gear pump,the cold crust of the electric motor oil and the integrated structure of the electric fuel pump using the Unigraphics(UG)software.In addition,the mathematical model of the permanent-magnet synchronous motor and the vector control theory is analyzed in this thesis.The space-vector pulse width modulation(SVPWM)technology is adopted to construct a speed and current double closed-loop permanent magnet synchronous motor servo control system based on the control strategy di =0.Simulations have been implemented with MATLAB/Simulink for us to study the control effect on the speed using the proportional-integral(PI)control strategy and the sliding mode control strategy.In this thesis,the motor driver and controller is designed on the basis of the digital signal processor TMS320F2812.The control programs are compiled under the development environment CCS4.2,while the speed regulation experiments on the permanent magnet synchronous motor servo control system are constructed under different conditions.The simulation and experimental results show that the permanent magnet synchronous motor servo control system has satisfactory steady and dynamic performance. |
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