Analysis of Various Types of Battery Systems On APU for More Electric Aircraft

In aviations the major challenge is to tackle the environmental effects on fuel consumption and emission, mainly nitric oxide which is harmful for environment which results in Acid rain, photochemical smog etc.. The development of electric power sources which is based upon non-polluting fuel is based on open research direction to meet the goals, fuel cells containing H2 are one such possibility. The goal is to lessen the environmental effect on both aerodrome and aboard equipment. The MEA idea aims to substitute electrical energy for nonelectric power. Military aircraft were the first to use this concept. The question of applying this idea to civil airplanes has come up throughout time. Power electronics have advanced quickly, allowing for flexible electricity transfer from sources to loads. The electrical system uses power electronics for power delivery, conversion, and generation. Obtaining increasingly efficient subsystems and integrating them into the aircraft's energy system is the trend in the building of such intricate electrical power systems on airplanes. This can shorten the time and lower the cost of design. In this paper the analysis and simulation of an APU- auxiliary power source is proposed in this work. The analysis has been done for different cases such as the whole APU system works on Fuelcell, based on Li-on Battery and fuel cell+Li-ion battery case, the whole analysis has been done using MATLAB Simulink. The converter system, which modifies the energy sources' properties to meet the needs of the MEA-type aircraft's power users, is given special consideration.