ROLL CONTROL OF A HIGHLY MANEUVERABLE AIRCRAFT UNDER CONDITIONS OF STRUCTURAL UNCERTAINTY
Annotation
The problem of controlling a highly maneuverable aircraft capable of changing its position in space by modifying the velocity vector in magnitude or direction is considered. A rational algorithm de-veloped for governing an automatic flight control system that does not exceed the main operational limits is presented. For this purpose, in addition to channels for stabilizing the angular position, channels for limiting the specified parameters are included in the aerobatic circuit that controls movement around the center of mass of the aircraft. A method is proposed for ensuring the coordinated interaction of these channels in the switching mode by using a generalized system characteristic that allows describing the entire ensemble of output reactions of the system for all possible moments of change in the structure of the control part. The effectiveness of the proposed approach is confirmed by the results of modeling the synthesized system of automatic control of the angular position of the aircraft.
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