Design method of aviation electric fuel pump based on structure optimization and intelligent control

Abstract

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.