LQR and SMC stabilization of a new unmanned aerial vehicle

We present our ongoing work on the development of a new quadrotor aerial vehicle which has a tilt-wing mechanism. The vehicle is capable of take-off/landing in vertical flight mode (VTOL) and flying over long distances in horizontal flight mode. Full dynamic model of the vehicle is derived using Newton-Euler formulation. Linear and nonlinear controllers for the stabilization of attitude of the vehicle and control of its altitude have been designed and implemented via simulations. In particular, an LQR controller has been shown to be quite effective in the vertical flight mode for all possible yaw angles. A sliding mode controller (SMC) with recursive nature has also been proposed to stabilize the vehicle’s attitude and altitude. Simulation results show that proposed controllers provide satisfactory performance in achieving desired maneuvers

Yeni bir insansız hava aracının (SUAVİ) prototip üretimi ve algılayıcı-eyleyici entegrasyonu

Bu çalısmada, dört-döner rotoru ile helikopter gibi dikine kalkıs ve inis yapabilen aynı zamanda da uçak gibi uzun menzil yatay uçus yeteneğine sahip yeni bir insansız otonom hava aracının mekanik ve aerodinamik tasarımı, karbon kompozit imalatı, algılayıcı eyleyici sistem entegrasyonu ve uçus deneyleri anlatılmıstır. Gelistirilen sistem ve içinde kullanılan algılayıcı eyleyici entegrasyonunun basarımı benzetim ve deneylerle doğrulanmıstır

Design and production of a new prototype unmanned aerial vehicle SUAVI

In this paper, the mechanical and aerodynamic design, carbon composite production, sensor-actuator integration and flight tests of a new unmanned aerial vehicle, which is capable of vertical takeoff and landing like a helicopter and long range horizontal flight like an airplane, is presented. Performance of the sensor actuator integration is verified with simulations and experiments

Modeling and control of a new tilt-wing unmanned aerial vehicle SUAVI

This paper presents a new quad-rotor aerial vehicle with a tilt-wing mechanism. The vehicle is capable of take-off/landing in vertical flight mode (VTOL) and flying over long distances in horizontal flight mode. The dynamic model of the vehicle is obtained using Newton-Euler formulation. An LQR control scheme is applied to the dynamic model in simulation environment for position and full range yaw control of the vehicle. Besides, a PID controller is designed for attitude and altitude stabilization of the vehicle. The performance of the PID controller is verified with simulations and experiments