Modelling and simulation of the pem fuel cell on mq1- predator unmanned air vehicle

Abstract

In today's world, the Unmanned Aerial Vehicle (UAV) is becoming more and more important for both military and civilian purposes. Due to its size, which is similar to that of a general aviation aircraft, and its lengthy endurance (several days), it can operate without a human pilot for extended periods of time while carrying significant payloads and instrumentation. However, at that time, electrical unmanned aerial vehicles (UAVs) were growing in popularity because they contributed to reducing carbon dioxide emissions and enabling more sustainable aviation. These UAVs are primarily powered by hydrocarbon fuels, and their design is heavily limited by the reciprocating engines used in general aviation, which are made for entirely different requirements. Considerable research has been done on the design implications that come from using electric propulsion in a wide range of unmanned air vehicles. Due to threats like climate change and the disruption of natural equilibrium, decarbonized energy sources are becoming very popular and they are supported by government investments and incentives. This is done in an effort to lessen reliance on fossil fuels. Infrastructure-wise, renewable energy solutions are expensive. They have, meanwhile, been keeping up their technological advancement quite rapidly. With the help of new technical advancements, the goal is to make those systems more efficient and so reduce the initial investment expenses. The primary determinant of a UAV performance in case the air vehicle is integrated with PEMFC system is energy which has huge effect on mission capability of the air vehicle. Proton exchange membrane (PEM) fuel cells are designated as the principal power source for electrified unmanned aerial vehicles (UAVs) because they have a significantly higher power density than other fuel cell types and a larger potential for use in high altitude long endurance (HALE) UAV flights. The aviation industry is mostly to blame for the majority of the emission gasses from fossil fuels that are released into the atmosphere. Since fuel cell powered air vehicles frequently have PEM type fuel cells, only water vapor is released to the atmosphere of the MEA during electrochemical reaction. Using hydrogen as fuel over fossil fuels is considered as a substantial alternative in reducing detrimental emissions to the environment. Many studies are being conducted now with the purpose of developing fuel cell technology's longevity and efficiency for the aviation sector. Since, PEMFC is very efficient, emits no emissions, and can function at low temperatures, it is a highly productive source of electricity for more and all-electric air vehicles. Finding a direct experimental estimate of the PEM fuel cell's real performance using a variety of characteristics and operating conditions, such as chemical reactions, fuel pressure, working temperature, and humidity, is difficult, though. As a result, modeling is crucial to comprehending PEM fuel cell operational performance. In order to achieve this meet, energy-related procedure for unmanned airvehicle which are designed with a specific fuel cell type was investigated in this work. First, UAV's mission profile and specifications were established. Based on mission objectives, the MQ-1 Predator was chosen as a reference, and some input characteristics were taken for granted. This thesis could be helpful for ongoing and upcoming research. The models are generated based on relevant studies which have been conducted up to now. The study includes modelling for not only for membrane electrode assmebly but also humidifier, anode and cathode sides, hydrogen source and oxygen sources. Therefore, it can be truly interpreted that the models of each equipment integrated in PEM fuel cell stack will be great guidance for the other users who are being worked on.