Study of a small aircraft for control development and UAV task

In this work, we consider a small aeroplane with the aim of using it as a test platform for the system identification, control, navigation and autonomous flight. The results of three of configurations considered are presented here, the original un-instrumented, the original instrumented and the modified instrumented aeroplane. The resultant models are nonlinear, and their behaviour depends on their stability and control derivatives found during the analysis. The main result present how the eigenvalues of the linearised model in equilibrium evolve for the angles of attack within the flight envelope. Since the original instrumented model behaviour exhibit undesired characteristics, we propose modifications of the original aeroplane and present the results. The models are also useful to make simulations under various perturbations and controls; an example is included.