Модель исследования устойчивости системы «Руль - привод» маневренного беспилотного летательного аппарата

Abstract

One of the important problems of the designing of maneuverable unmanned aerial vehicles (UAV) is to ensure aeroelastic stability with automatic control system (ACS). One of the possible types of aeroelastic instability of UAV with ACS is loss of stability in the «rudder-actuator» system. To study the stability of the «rudder-actuator» system of the maneuverable UAV the linearized model was developed. The system consists of hard rudder, performing flexural and torsional oscillations, and the fixedly mounted control surface electric actuator. The «rudder-actuator» system has three degrees of freedom: bending of the rudder, the rotation of the rudder and the angular displacement of the actuator shaft. The rudder, performing bending-torsion oscillations in aerodynamic flow, in fact, is the loading for the actuator. Investigation of the «rudder-actuator» system stability is carried out by frequency method with the use of frequency characteristics of the open-loop system. An example of stability analysis of the «rudder-actuator» system is given.