The concept of Multi Electric Aircraft (MEA) means that electric aircraft are increasingly being used to drive the power of aircraft subsystems, which in traditional aircraft are a combination of mechanical, hydraulic, and pneumatic systems. Today, the editor will comeA Brief Discussion on the Power System of Multi Electric AircraftBecause the goal of MEA is to completely replace non electric systems on aircraft with electricity, traditionalAviation circuit breakerWill it be gradually replaced? This idea is primarily applicable to meet the requirements of lighter overall weight, lower maintenance costs, higher reliability, and better performance of military aircraft. With the increase of capacity and rated value in civil aircraft, the idea of MEA has also been applied. The concept of multilateral environmental agreements is seen as the direction for the development trend of future aircraft power system technology. The future aircraft power system will adopt a multi voltage level hybrid DC and AC system. Therefore, the MEA distribution system mainly exists in the form of a multi inverter power system. The modern aircraft power system is a hybrid voltage system consisting of four voltages: 405VAC (variable frequency), 200VAC, 28VDC, and 270VDC. The aircraft power system typically consists of two or more engine driven generator sets that provide AC load to the entire aircraft. All aircraft systems require both AC and DC power sources.

The DC power supply comes from the transformer's rectification and rectification device (TRU) for the AC power supply. These devices are typically configured with 12 pulses [2-3]. Due to their operation, these units are considered as harmonic source systems in the aircraft power system. These units will increase the distortion and harmonic content of the AC voltage on the side of the aircraft power system. The Constant Speed Drive (CSD) power generation system found on many aircraft consists of a three-stage stabilized synchronous generator, whose output frequency is transmitted through a hydraulic mechanical CSD through a gearbox. The reduction in system weight is caused by the combination of the following factors, which integrate the driver and generator into one unit, thereby providing an integrated driver generator (IDG) [4]. However, the continuous development of power electronics technology and microprocessor technology have led to DC link variable speed constant frequency (VSCF) power generation systems [5], becoming a feasible alternative to CSD and IDG systems. Compared with the CSD/IDG system, the variable-speed constant frequency electrical system is more flexible because components can be distributed throughout the aircraft, and in contrast to the CSD/IDG mechanical system, the system must be located close to the engine.