Synthesis and analysis of the laws of automatic landing control of an unmanned aircraft on a landing gear

In this research we obtained the flight control laws for an unmanned aircraft at the landing stage, and performed an analysis of their performance under the action of a wind disturbance. The landing trajectory consists of sections of straight-line descent and exponential alignment. Stabilization on the trajectory is carried out according to a proportional law with constant coefficients obtained by the method of optimal regulators analytical design. The wind speed was taken into account as the sum of the average horizontal component, considering the vertical shear, the turbulent component and discrete vertical gusts. The maximum permissible wind speeds are determined taking into account the restrictions on the motion parameters at the touchdown point. Their value depends on the direction and corresponds to five points. 
The article shows graphs of changes in motion parameters during landing under the action of a tailwind, headwind and vertical wind, as well as graphs of changes in the position of controls. We also indicated the statistical characteristics of the vertical speed of touching the landing site, as well as errors in the longitudinal coordinate of the touchdown point for the maximum allowable wind speeds.