Effect of Control Parameters on Hybrid Electric Propulsion UAV Performance for Various Flight Conditions: Parametric Study

Nowadays, great efforts of ongoing research are devoted to hybrid-electric propulsion technology that offers various benefits, such as reduced noise and pollution emissions enhanced aircraft performance fuel efficiency. The ability estimate the an in any flight situation which it may operate is essential for development. In current study, a simulation model was developed allows estimating analyzing mission fixed-wing multi-rotor Unmanned Aerial Vehicle (UAV) with hybrid electric system (HEPS), both conventional Vertical Takeoff Landing (VTOL) capabilities. control based on continuous specification pitch angle, thrust, lift thrust achieve required conditions given segment. Six different missions were considered analyze effect parameters exhibiting most influence UAV performance. An appropriate set selected through multidimensional parametric study. results show parameters, if not well tuned, affect performance: example, deceleration transition, longer time reduce cruise speed stand still be result because controller struggles adjust angle. addition, implemented methodology captures effects transient maneuvers, unlike typical quasi-static analysis without complexity full models.