DESIGN AND CALCULATION OF A CONTROL SYSTEM FOR AN SMALL AIRPLANE WITH TAKE-OFFWEIGHT TO 2 000KG

Abstract

Thesis deals with the design of control system for aircraft with maximum take-off weight of 2,000 kg. Thesis deals about the current state of the aircraft control system. Thesis is dealing with the direct control system. It explained information and description of direct control system. There are also described the basics and terms used in this issue. In the next stage the design of an control system with a description and appropriate documentation is made. In the next stage of this thesis the bonding material analysis and calculation of the control system are made. Design and calculation are made according to official regulations CS-23. The work is accompanied by pictures and technical description of the proposed construction.