The Flying Wing UAV Using Classical Control Theory

This paper describes modeling design procedure of a flying wing UAV which is a tailless fixed wing aircraft and has no definite fuselage, with respect of the crew, payload and equipment being housed inside the main wing structure. In this thesis a 6 degree-of-freedom mathematical model describing the aircraft dynamics is first presented, then using these equations, the derivatives of the parameters and system identification of simplified, linear lateral and longitudinal models are estimated for the tailless aircraft. A detailed modeling procedure of flying wing UAV and stability analysis results using the linearized model at trim condition are represented. Finally, we have designed the flying wing UAV using classical control theory.