engleski

Generator Set Control System Design for Unmanned Aerial Vehicle Hybrid Propulsion

One of the key limitations of the currently deployed multirotor aircraft and similar unmanned aerial vehicles (UAVs) is the rather low capacity and non-negligible weight of the state-of-the-art lithium-based batteries, resulting in rather low flight mission endurance (flight range), payload restrictions and manoeuvring limitations. On the other hand, the traditional propulsion systems based on internal combustion engine (ICE) suffers from limitations related to weight of the transmission and complexity of the collective control system for individual rotors. Hence, it is worthwhile to investigate the possibility of hybridization of propulsion systems of such aircraft. Having this in mind, this paper proposes a hybrid-electric drive topology, which can be easily augmented by a battery energy storage system for the common direct-current (DC) bus voltage and power flow control. The proposed control system includes: (i) a speed control system for the internal combustion engine equipped with an alternating current (AC) generator featuring a proportional-integral-derivative (PID) feedback controller (ii) AC generator active front end rectifier control for the purpose of maintaining the DC bus voltage within the prescribed bounds, and (iii) generator set speed (frequency) estimator for the purpose of speed-sensor-less generator set speed control. The effectiveness of the proposed control system is verified by means of comprehensive computer simulations.

Unmanned aerial vehicles ; hybrid propulsion ; generator set speed control ; speed estimation ; direct-current bus control

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