WEIGHT ESTIMATION MODELING OF PROPULSION SYSTEM VARIATIONS FOR VTOL FIXED WING UAV IN PARTICULAR MISSION

• Main Author: Firman Ramanda, Muhammad
• Format: Theses
• Language: Indonesia
• Subjects: Teknik (Rekayasa, enjinering dan kegiatan berkaitan)
• Online Access: https://digilib.itb.ac.id/gdl/view/84367
• Institution: Institut Teknologi Bandung

VTOL Fixed Wing UAV is an aircraft that consists of 2 flying modes, namely VTOL Flight Mode, which in this case it will always use an Energy Converter in the form of 4 Electric Motors, and Fixed Wing Flight Mode which will always use an Energy Converter in the form of 1 motor (can be Electric Motor or ICE). In this research, the UAV with this configuration has a Flight Mission Profile consisting of 7 segments. Based on the mission and input that have been determined, the technical values in the form of Power (kW), Operating Time (h), and Energy (kWh) required for each segment for each flight mode can also be determined. This can determine the selection of propulsion system components discussed, for example in Energy Storage: Gasoline, Battery and Fuel Cell; Energy Converter: ICE and Electric Motor; and Thrust Generator: Propeller. To be able to complete the mission, the UAV is equipped with a propulsion system that suits its needs. In this research, there are 8 variations of the propulsion system that can be considered, based on the mass of the propulsion system as a whole. By knowing the mass of the propulsion system as a whole, it can be seen which propulsion system is most optimal for application on a particular mission.