Print Email Facebook Twitter Hybrid UAV Attitude Control using INDI and Dynamic Tilt-Twist Title Hybrid UAV Attitude Control using INDI and Dynamic Tilt-Twist Author Dellemann, Lars (TU Delft Aerospace Engineering) Contributor de Wagter, C. (mentor) de Croon, G.C.H.E. (graduation committee) Degree granting institution Delft University of Technology Programme Aerospace Engineering Date 2020-12-03 Abstract The application of Unmanned Aerial Vehicles (UAVs) is increasing, much like the performance of these aircraft. A tailsitter is a type of UAV which is capable of performing vertical take-offs and landings (VTOL) and long endurance flights. During hover, the yaw control is limited due to the dynamics of these tailsitters. The generally used quaternion feedback for the attitude does not compensate for this as it describes a singular rotation. Tilt-twist is a solution to the problem as it splits the tilt (pitch and roll) from the twist (yaw). The axis of the yaw rotation is body fixed. When hovering with a pitch and/or roll angle the twist axis will be aligned with the body z-axis, instead of the desired gravitational force vector (for position control). Previous tilt-twist methods used a PID controller. This paper describes an improvement over previous tilt-twist approaches, the dynamic tilt-twist in combination with INDI. The INDI controller is designed for nonlinear systems. The dynamic tilt-twist compensates for the problem with the normal tilt-twist as test results will demonstrate. Tests are performed in a simulation and a real life test with the NederDrone hybrid tailsitter is done. To reference this document use: http://resolver.tudelft.nl/uuid:b2db7412-74d9-4914-94b7-0b922a061adc Embargo date 2020-11-26 Part of collection Student theses Document type master thesis Rights © 2020 Lars Dellemann Files PDF Thesis_report_Lars_Dellem ... 616057.pdf 12.33 MB Close viewer /islandora/object/uuid:b2db7412-74d9-4914-94b7-0b922a061adc/datastream/OBJ/view