Theoritical And Simulation Based Approach For Dynamic Stability Of Aircraft Longitudinal And Roll Control Movement

摘要

In this paper we consider two of aircraft, i.e., pitch and roll control movement based on available secondary data. The work cose studies is considered here and the original work is carried forward with intelligent design such as ANN(artifical neural network), ANFIS (artificial neuro fuzzy inference system) and nnhination of PID controller with Fuzzy compensation techniques. Intelligent control design methode m is prevented to examine the overall performance of controllers, primarily based on time response . at aircraft pitch control system is designed for Linear and Non-linear models and the effect of is observed on the performance of Flight control system (FCS), whereas the roll is designed with rate gyro and rate integrating gyro. The controllers are designed on the basis , A endeling of the aircraft system for roll and Pitch movement control. The controllers are designee on linearized model of aircraft so as to simplify the design process, with the idea of dynam ic mode, motor for aircraft pitch control by controlling the movement of elevators and modeling at rate integrating gyro for F-16 fighter aircraft. A quantitative analysis of controllers has been carried out in environment. It is concluded from the results that combination of Fuzzy-PID controller provides best results with reference to aircraft pitch and roll control movement respectively.