Study of the Methods for Analysis of the Maximum Control Error

Abstract

The task of synthesizing an automatic motion control system based on the criterion of the minimization of maximum control error is set. The definition of the maximum control error is given. The task is especially relevant for controlling the landing of aircraft, a wide range of guidance tasks, flight control in the mode of following the terrain, in the mode of stabilizing the low altitude of the WIG-craft. The possible maximum value of the dynamic error is strictly estimated when maximum values of several derivatives of the driving force are given. These numerical data are easy to find experimentally or on the basis of a priori theoretical research. The maximum error value of the aircraft pitch angle control with the astatic autopilot is considered when the driving force and its derivatives are limited.