Simulation study of Aircraft AC Generator with electrical fault insertion

摘要

The aim of this paper is to model a typical Aircraft Generator along with its control system and study the behaviour / performance during fault, particularly in the rectifier block which is used in the field circuit and fault in the winding. The study shows that there is no considerable change in the Generator supply characteristic up to a certain extent of fault, but the significant change in the field excitation was observed. The output of the developed model was successfully corroborated with the MIL-STD 704F power supply characteristics.