Flight Control System Design for Aerosonde Unmanned Vehicle

Abstract

Cilj ovog rada je analiza upravljačkog sustava bespilotne letjelice Aerosonde. Aerosonde je autonomna bespilotna letjelica s iznimnim svojstvima stabilnosti i upravljanja. Pomoću Aerosim Blockset-a određen je nelinearni model letjelice. Nelinearni model je uravnotežen i lineariziran za uzdužno i bočno gibanje. Koristeći linearni model letjelice provedena je analiza dinamičkih karakteristika uzdužnog i bočnog gibanja letjelice. Analizirana su dva sustava upravljanja, sustav upravljanja orijentacijom propinjanja u uzdužnom kanalu upravljanja koristeći linearnu dinamiku uzdužnog gibanja letjelice te sustav bočnog upravljanja i auto stabilizaciju koristeći linearnu dinamiku bočnog gibanja letjelice. Usporedbom stabilnosti i upravljivosti letjelice nakon uvođenja upravljačkog sustava sa stabilnosti i upravljivosti otvorene petlje primjetno je kako upravljački sustav stabilizira letjelicu i omogućava upravljivost.The objective of this paper is design of a flight control system of Aerosonde unmanned aerial vehicle. Aerosonde is autonomous aerial vehicle with great stability and control characteristics. Firstly, the nonlinear 6-degree-of –freedom aircraft is developed using Aerosim Matlab/Simulink Blockset. Before applying flight control algorithm the nonlinear model is trimmed and linearized. Using the linearized aircraft model the analyses of aircraft dynamic characteristics are presented respectively in the longitudinal and lateral-directional senses. Two flight control systems are analyzed. Longitudinal Rate Command Attitude Hold is analyzed using the linear longitudinal dynamics. Lateral-Directional Auto-Stabilizer is analyzed using the linear lateral-directional dynamics. Comparing the stability and control before and after implement of the flight control system it is easy to notice how flight control manage to establish stability and control of aircraft