Implementing Intelligent Control Techniques in State Feedback and Estimators Control Loop for Aircraft Pitch Control Pavithra A C 1 and Archana A V 2 1 Department of ECE, ATME College of, Visvesvaraya Technological University, Belagavi, India 2 Department of EEE, NIE Institute of Technology, Visvesvaraya Technological University, Belagavi, India Email: pavithraac26@gmail.com archana@nieit.ac.in Abstract—Implementing the better optimized controller for the aircraft pitch control when the system is corrupted by noises is quite a competitive situation in the current scenario due rapid increase of aircraft systems in the space. Hence, currently two experiments are proposed for the aircraft pitch control. In the first experiments noises are not considered, where optimal switching control techniques are done using Linear Quadratic Regulator (LQR). The second experiment is done when the system is corrupted by noises using Linear Quadratic Gaussian (LQG) control. Switching control algorithms implemented in this paper are tested for the longitudinal dynamics of aircraft system using MATLAB/SIMULINK platform. Index Terms—LQR, LQG, Fuzzy Logic Controller (FLC), PID. Nomenclature: γ- Path angle θ -Pitch angle α -Angle of attack Θ -Roll angle β -Sideslip angle q -Pitch rate U 0 - Longitudinal velocity m- Aircraft mass δe- Elevator deflection δr -Rudder deflection δa- Aileron deflection I. INTRODUCTION Presently the aircraft system is operating with huge operating conditions due to highly complex and other environmental factors. In such a scenario controlling of the aircraft, stabilizing, reducing peak overshoots and settling time is very highly challenge. Aircraft industry is using Aileron, Rudder & Elevator deflection control inputs to control the Roll, Yaw and Pitch angles. A detailed literature survey of most recent research work summarized below is better motivation for the proposed aircraft pitch control system. The side-to-side axis movement called pitch using the control input elevator, which makes the nose of an aircraft ascend or descend. Grenze ID: 01.GIJET.8.3.691 © Grenze Scientific Society, 2022 Grenze International Journal of Engineering and Technology, Special Issue