METHOD OF INTEGRATED CONTROLLING FLIGHT HEIGHT FOR AIRCRAFT WITH A COMPLEX AERODYNAMIC DESIGN OF WING

摘要

The invention relates to aviation. A method of integrated controlling flight height for aircraft with a complex aerodynamic design of wing stipulates for calculation of a control signal for every regulated movable element of wing structure which is applied to an actuating mechanism of the above regulated movable element. The above control signal is distributed according to a specified ratio for the distributed height control system, at that one part of the signal is applied to the main loop of the elevator control system. The second part of the control signal is applied to the additional control loop that directly regulate variations of lift forces created by the wing aerodynamic design and then the deflections of each movable component of wing structure are selected among variants of possible combinations with the use of the airborne calculator. Theses variants are calculated according to flight conditions and parameters with the use of weight factors for the support function for taking decisions. A technical result is the ensured self-adjustment of the aerodynamic design of control surfaces for performing the formulated task of maintaining the specified flight trajectory with high accuracy and speed of response.