| This dissertation is for the purpose of developing a new electrical machinery used to actuate some aircraft fuel electrical centrifugal pump and is aim to solve the short lifetime, poor reliability of the existing actuating motor's shortcomings.In this paper, a rare earth permanent magnet brushless direct current motor (BLDCM) which adopts an integration structural style combing electrical machinery main body with its controller is selected as the actuating motor according to the request of special conditions, light weight and long life of the aero fuel pump system which plays an extremely important part in the airplane. A 27V900W integral type BLDCM and its accessorial controller used in aero fuel pump system is designed by a method based on the high power density design method, together with magnetic circuit design, magnetic field and circuit united on the analysis, three dimensional structure modeling design.In order to solve the starting problem caused by low voltage high current, a formula of calculating BLDCM inductance by its own parameters is studied, the starting characteristic of the system is also analyzed under the Matlab environment, an appropriate PWM chopping frequency range and method is obtained, which can restrain the transient impact current efficiently, and a controller based on analog component is developed. A current detection method is also proposed which is based on the BLDCM back electromotive force.Finally, another set of controller based on TMS320LF2407A DSP is also discussed and designed to satisfy the development tendency of aero fuel pump system.The tentative data and its analysis based on the prototype indicate that the test results are consistent with the design proposal and this principle prototype can satisfy design target request and the actuating need of aero fuel pump system. This principle prototype has passed the aero fuel pump system union test in some trainer aircraft.
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