Optimal Digital Pitch Aircraft Control
نویسندگان
چکیده
aircraft regarding to the elevator deflection angle is designed. The way how the elevator angle affects pitching motion of the aircraft is pointed out, as well as, how a pitch controller can be applied for the aircraft to reach certain pitch angle. In this digital optimal system, the elevator deflection angle and pitching angle of the plane are considered to be input and output respectively. A single input single output (SISO) system is presented. A digital pitch aircraft control is demonstrated. A simulation for the whole system has been performed. The optimal control weighting vectors, Q and R have been determined.
منابع مشابه
Optimal Design of Robust Fractional Order PID for the
Nature inspired algorithms are the most popular and robust algorithms for the optimization of the real world problems like pitch control of an aircraft system. This paper introduces Bat algorithm and Differential Evolution technique for the multi-objective optimization based designing of the fractional order PID (FOPID) and integer order PID controllers. The optimized values obtained from the t...
متن کاملDesign and Modeling of Controllers for Aircraft Pitch Contol Movement
In the present paper intelligent controllers design methodology is presented to examine their overall performance primarily based on time response specification for controlling Pitch movement of aircraft. The aircraft pitch control system is designed for Linear and Non-linear models and the effect of various nonlinearities is studied based on the overall performance of various controllers in Fl...
متن کاملOptimized Controller Structured to Solve Aircraft Pitch Control Problem
In this paper, a comparative assessment is made based on time domain specifications and erro r criteria between various types of controllers like conventional PID, and heuristic approaches like FA, P SO and BFO based PID and I-PD structured controllers. The dynamic modelling of pitch control system i s considered on the design of an auto pilot that controls the pitch angle. To study the effecti...
متن کاملGain-Scheduled Two-Loop Autopilot for an Aircraft
We present a new method to compute output gain-scheduled controllers for non-linear systems. We use structured H∞-control to pre-compute an optimal controller parametrization as a reference. We then propose three practical methods to implement a control law which has only an acceptable loss of performance with regard to the optimal reference law. Our method is demonstrated in longitudinal fligh...
متن کاملAutomatic Landing Guidance Systems and Design of an Optimal Landing Control System
Guidance and control of aircraft in the landing phase imposes extra pilot work loads, hence application of automatic landing control systems is of great importance. In this study automatic landing control systems are introduced and an optimal landing control system is designed. The control system performance criteria are based on minimum control effort. The designed system is simulated for a tr...
متن کامل