Abstract
The dual thrust system hybrid UAV combines the hover capabilities of the quadcopter and the endurance capabilities of the fixed-wing types in one aircraft. Its main goal was to eliminate the needs for runway access in the takeoff and landing process. This concept was implemented in the LSU-02 NGLD VTOL design to enhance flight missions. In general, this type of UAV have three flight modes: hover flight mode, transition mode, and fixed-wing mode. The design of transition control from hover to cruise flight was a challenge in itself. This study described the stages of designed mathematical model of Hybrid UAVs flight dynamic and gives an overview of transition control strategy to handle unstable and nonlinearities of flight movement. From motor specification, the drag and torque coefficient were set to 2. 2×10 <sup xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">-4</sup> N/s <sup xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">2</sup> and 5.58×10 <sup xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">-6</sup> Nm/ s <sup xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">2</sup> respectively to completed the model.
Published Version
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