Flight dynamic modelling of a micro quadcopter UAV

This project will study the characteristic of flight dynamic modelling for the Micro Quadcopter UAV. The aim of this study is to identify the flight characteristic of the Micro Quadcopter UAV which has all four basic control surfaces (Roll, Pitch, Yaw and Thrust). The benefit of this project is to have a natural flight dynamic modelling of the Micro Quadcopter. The study will be in 2 parts, testing by using experimental (Flight Dynamic Testing) and simulation tool by using MATLAB. The simulation is designed to simulate the following. Lastly, validate the designed transfer function and analysed the performance of the Micro Quadcopter UAV.