Print Email Facebook Twitter Towards a Better Understanding of Attitude Oscillations Experienced by Quadcopters In Axial Descent Title Towards a Better Understanding of Attitude Oscillations Experienced by Quadcopters In Axial Descent Author Bogaerts, Charlie (TU Delft Aerospace Engineering) Contributor de Visser, C.C. (mentor) Degree granting institution Delft University of Technology Programme Aerospace Engineering Date 2023-10-04 Abstract This study aims to quantify the aerodynamic behaviour of fixed pitch rotors with a diameter of 12.7 cm in axial descent, and its contribution to the attitude oscillations found for quadcopters under similar flight conditions. Wind tunnel tests are performed with an isolated rotor, as well as a complete quadcopter mounted inside a gimbal that allows for roll and pitch motions. Isolated rotor wind tunnel tests show that thrust and torque fluctuations manifest in the pre-vortex ring state, but peak in the vortex ring state. The derivatives of thrust and torque with respect to airspeed remain positive in ranges from 0 mps to 25 mps and 3000 rpm to 20000 rpm. Comparison of these results with measured quadcopter motions reveal that isolated rotor characteristics only partly explain the attitude oscillations found for quadcopters in axial descent. Subject quadcoptersuavvortex ring stateturbulent wake staterotorpropellerpropellersrotorspropwashprop washinteractiondescentaxial descentstabilityinstabilityinflowoscillationoscillationsinterferencedronedroneswind tunnelvibrationsvibrationflightwindmillingSimplex B-Splines To reference this document use: http://resolver.tudelft.nl/uuid:e868d941-42e5-46c0-b706-c21a6bece0da Part of collection Student theses Document type master thesis Rights © 2023 Charlie Bogaerts Files PDF Thesis.pdf 22.16 MB Close viewer /islandora/object/uuid:e868d941-42e5-46c0-b706-c21a6bece0da/datastream/OBJ/view