Assessment of the accuracy of heavy aircraft control, taking into account the functioning of the indicator on the windshield and flight control actuators

The article is devoted to the issue of evaluating the piloting performance of an aircraft, taking into account various factors that have a special effect on the control process. The article presents the results of work on the creation of models of a digital indicator on the windshield and the power circuit of the hydraulic system and consumers in the longitudinal control channel of the aircraft for conducting research in the field of assessing their impact on piloting accuracy when the aircraft moves along an assigned flight path during landing. The features of the process of developing the elements of the indicator on the windshield, namely the indicators of the director ring and the velocity vector, their control law when the aircraft moves along an assigned flight path are presented.  The implementation of the effect of the hinge moment on the steering actuators in the model of the hydraulic system of the aircraft when the stabilizer consoles deviate from a neutral angular position is described. The principle of integration of a Simulink model of a hydraulic system and a flash model of a windshield indicator with a model of spatial motion of a heavy aircraft is presented. The results of semi-natural simulation on a flight simulator are presented, on the basis of which the values of deviations from a given flight path are calculated when performing a turn in a circle, the mode in which the hinge moment limits the angle of deviation of the stabilizer consoles is determined. It is concluded that it is advisable to create and use an experimental base to provide research in the field of assessing the impact of promising information sources that provide flight information to the crew in poor weather conditions, and the operation of the hydraulic system on the aircraft piloting performance and the pilot’s control actions in various flight modes of the aircraft.