Digital Control of Aircraft’s Pitch Angle in discretetime domain

Dangers resulting from sudden changes of theangle of twist in airplanes, especially during the landing led theresearchers to find a solution for this problem. On one hand,one of the most important issues about planes' dynamics hasbeen designing a control system. The number of variablesexisting in this complex system is numerous. Among thesevariables, one of the most important variables thatsignificantly affects on the dominant equations in aircraft’ssystem is the altitude of plane. This article tries to not onlyevaluate the control of the pitch Angle for autopilot systemafter modeling and extracting the dominant equations bydesigning the proportional-integrator controllers, integrator,lead, and lag in time-discrete domain of system’s function, butalso it will assess the important parameters such as maximumovershoot, rise time, and steady-state error.

Digital Control of Aircraft’s Pitch Angle in discretetime domain Keywords:

Pitch Angle , proportional-integrator , lead , lag , discrete-time Introduction