PRACTICAL DETERMINATION OF THE TRANSFER FUNCTIONS OF THE AIRCRAFT LABORATORY STAND BY YAW ANGLE

Abstract

The most difficult thing when piloting an aircraft (LA) is the landing mode under the influence of wind disturbances. An important role in ensuring controlled flight is played by the angular position stabilization system, which is designed to work out regular control influences and counter random disturbances in the course and roll channels. Contours of angular stabilization are built using the principle of deviation control. Deviations are formed due to changes in feedback signals determined by the parameters of the aircraft's own rotational motion. Stabilizing the angular position of the aircraft by deflecting the steering surfaces does not always allow to achieve the desired result, therefore there are other options for solving this problem. One of these options is to implement non-traditional methods of angular stabilization of the aircraft during landing. The essence of the problem boils down to the use of engine thrust control to eliminate the effect of crosswind. The purpose of the work is to use a computer system for stabilizing an aircraft in lateral movement to eliminate wind disturbances by changing the engine thrust. The tasks of the work are: development of a computer system for stabilizing the movement of an aircraft by the yaw angle, taking into account wind disturbances; creation and verification of stabilization algorithms on a laboratory bench using an ARDUINO controller; study of functional capabilities of angular stabilization circuits. The object of the study: a computer control system of an aircraft that performs the task of yaw angle stabilization. The subject of research: processes of stabilization of the angular position of the aircraft in lateral movement. To create a stabilization system, the methods of analyzing the dynamic characteristics of the selected object and choosing the structure of the angular stabilization contour were used. When performing the work, a control law using angular and angular velocity feedback was chosen. The work has an applied nature. A computer system for stabilizing an aircraft by the yaw angle, taking into account wind disturbances such as crosswind, was developed and studied. A variant of aircraft stabilization when using engine thrust control is proposed. The control law of the computer stabilization system, which is implemented on the ARDUINO controller, was selected and tested. The applied value of the work is the further use of the obtained results in modern models of aircraft-type aircraft.