THESIS
2011
xi, 77 p. : ill. ; 30 cm
Abstract
Unmanned aerial vehicles (UAVs) have been more and more widely used not only in military areas but also in civilian and commercial areas nowadays. UAVs could be categorized by fixed-wing aircrafts and rotor-crafts. In contrast with other fixed-wing aircrafts, the helicopters could take off and land vertically, to hover, and to fly forwards, backwards and laterally....[
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Unmanned aerial vehicles (UAVs) have been more and more widely used not only in military areas but also in civilian and commercial areas nowadays. UAVs could be categorized by fixed-wing aircrafts and rotor-crafts. In contrast with other fixed-wing aircrafts, the helicopters could take off and land vertically, to hover, and to fly forwards, backwards and laterally.
Miniature helicopters are more agile and unstable than the full-size counterparts in the flight. Development of a reliable high-performance helicopter-based unmanned aerial vehicle requires an accurate and robust model that contains essential aerodynamic of the helicopter in typical flight conditions.
This thesis presents a method of experimental setup and results of the dynamic modeling of a miniature unmanned helicopter (Trex-500). Working from first principle and basic aerodynamics, the equations of motion for full six degree-of-freedom with flybar-degree of freedom are derived. The experiment is setup to test the thrust of the main rotor and verify the model structure in the hover condition.
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