The invention discloses an
aviation electric
fuel pump design method based on structure optimization and
intelligent control, belongs to the field of intelligent optimization design and control, and aims to optimize the structure of a
gear pump, simplify the
bearing design and
neglect a
diffusion area and an unloading groove, so that the
gear pump better meets the quality requirement in practical application, and the
gear pump design method is suitable for large-scale popularization and application. And a
sparrow search algorithm is used for optimizing structural parameters, so that the quality and efficiency of the gear pump are improved. The spline is additionally arranged between the motor end and the gear pump end of the gear shaft, rotation isolation of the two ends is achieved, and the problem that the electric
fuel pump is stuck in the to-be-loaded starting stage is effectively solved. By redesigning the shell and comprehensively considering the problems of weight, leakage, torque and the like, the overall design of the electric
fuel pump is optimized. By adopting a super-spiral
direct torque control method, rapid torque response and accurate flow control of the electric fuel pump are realized. According to the method, the
gain parameters of the controller are optimized through the
sparrow search algorithm, and the control precision and the steady-state performance of the
system are improved.