Akademik Veri Yönetim Sistemi
International Review of Aerospace Engineering, cilt.9, sa.3, ss.70-79, 2016 (Scopus)
Small-scale Unmanned Air Vehicles (UAVs) belong to the class of less than one meter box dimension and are widely used in different civilian and military roles. In this paper, quadratic optimal control synthesis is carried out on a rigid-wing UAV at low speeds with improved aerodynamic performance. The aircraft is equipped with a unique feature of ‘aerodynamic vectoring’ such that the angle of incidence of the wing is dealt as an independent control variable. The aircraft motion is studied in longitudinal plane. More specifically, controller is designed using Linear Quadratic Regulation (LQR) and Linear Quadratic Gaussian (LQG) formulations which are carried out for two configurations – fixed-wing UAV and ‘Aerodynamic Vectored’ UAV. The control architecture shows avoidance of instabilities associated with short period and phugoid modes. Moreover, aerodynamic vectored UAV manifests better performance in terms of stability, control effort, settling time and overshoot.