Abstract
This article presents an overview of the design of an autonomous landing controller. The flight control system must be robust against the effects of wind and must control the height accurately enough to support an autoland function. This study design and compare two different altitude command tracker controllers for an unmanned air vehicle using H∞ and quantitative feedback theory (QFT) techniques during the landing phase. The different stages of QFT methodology have been done with help of software tool quantitative feedback theory interactive tool. This is a free software tool that is characterized by its easy of use and interactive nature. QFT is standing as a viable control design method that can be applied to practical problems and produce implementable results. Tests with realistically large control inputs are used to validate and compare both designs.
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