A new hybrid control algorithm design and simulated for Longitude and latitude movements stabilization of nonlinear fixed-wing UAV

Abstract

UAVs (Unmanned Aerial Vehicles) have enabled a number of new mission capabilities and are frequently used in many applications. There are a few sorts of UAVs configuration available in the market, but fix-wing UAVs is the most popular among them. It is mostly used in surveillance and rescue type applications by militaries as well as business organizations .This makes UAV design and controlling as one of the most sizzling subject for the researchers. The troublesome undertaking for the scientists in UAVs design is to develop its efficient control algorithm which makes UAV flight settle under typical and instability or irritated conditions. Like other UAVs, fix-wing UAVs are also non linear in nature and its stabilization during flight is troublesome task. It has two major movements that are, longitudinal and lateral movement, which must be control legitimately to make Fix Wing UAV flight stable. There are several control techniques available that are used to control its flight movements. These accessible control techniques have a few pros and cons, and have their own working impediments. This research exploration deals with the designing of control system for small size fixed-wing UAV to enhance the flight performance under uncertainties condition. Generally these UAV countenances unpredicted problems during flight such as, heavy wind gust, alter in wind current course, sensors commotions or sensors noises. These impacts may float the UAV from it sought direction and makes it unstable. The available traditional control techniques are not robust enough to handle these perturbed circumstances. In this thesis a new hybrid control algorithm is presented for longitudinal and lateral movements controlling of small fixed-wing UAV. The proposed control technique is developed by joining the PID algorithm with PD-LQG algorithm to stabilize the small fixed-wing UAV flight under sensor noisy conditions and external disturbance circumstance. For verifying the performance of proposed control strategy it is simulated on ‘Yardstick’ type small fixed wing UAV. The simulation are performed and analyzed under different windy and noisy conditions. MATLAB Simulink with its Aerosim block set is used to execute all the simulation. The simulation results demonstrates that the proposed control technique performed exceptionally well under perturbed conditions and its performance is much better than available traditional algorithms under uncertainty conditions.