Results from differential game theory are applied to construct an adaptive control in linear systems with an unknown level of dynamic disturbances. The efficiency of the method is exemplified by a problem of aircraft landing under wind disturbance.

An approach for constructing a robust feedback control for problems having linear dynamics with disturbances is suggested.Auseful control is assumed to be scalar and bounded.The approach can be applied to conflict-controlled systems, where the constraint for the disturbance is unknown in advance. Adjustment of the method is based on results of the theory of linear differential games with fixed terminal time and geometric constraints for the players’ controls.The algorithm for constructing the robust control is fulfilled as a computer program for the case when the quality of the process is defined only by two components of the phase vector at the terminal instant. The paper presents simulation results for the problem of lateral motion control of an aircraft during landing under wind disturbance.

An approach for constructing a robust feedback control for problems having linear dynamics with disturbances is suggested. A useful control is assumed to be scalar and bounded. The approach can be applied to conflict-controlled systems, where the constraint for the disturbance is unknown in advance. Adjustment of the method is based on results of the theory of linear differential games with fixed terminal time and geometric constraints for the players’ controls. The algorithm for constructing the robust control is fulfilled as a computer program for the case when the quality of the process is defined only by two components of the phase vector at the terminal instant. The paper presents simulation results for the problem of lateral motion control of an aircraft during landing under wind disturbance.

A third-order nonlinear control system governing automobile or aircraft motion in a horizontal plane is considered. A theorem on the number and character of switchings of the controls that lead to the boundary of the reachability set is proved. Examples of numerical construction of the reachability set are presented.

The estimation from above of information sets characterizing the phase states of an aircraft moving in a horizontal plane is considered. It is based on the method of roughening from above of the attainability sets of the nonlinear control system under investigation. The information sets are constructed in the three-dimensional phase space on the basis of measurements of the two-dimensional geometric position taking into account some known constraints on the measurement errors. The algorithms proposed allow us to perform computations in the real-time mode. Some simulation results are presented.

The paper deals with a tracking problem of an aircraft motion in the horizontal plane under constant trajectory velocity and inertial control of the heading velocity. Measurements of the aircraft position come at some instants. Measurement errors obey the geometric constraints. Any probability characteristics of the errors are absent. An algorithm and nonlinear procedures are suggested for constructing informational sets in the four-dimensional phase space. The informational set describes the totality of all phase states consistent with the sequence of received measurements. Simulation results are represented. Comparison with exact calculations is implemented.