Abstract
Modern flying vehicles (FV) have broad ranges of variation of the exploitational characteristics, possess elevated structure flexibility, use numerous load modifications that result in a substantial variation in the elastic mass and aerodynamic parameters in flight and an increase in the possibility of the appearance of dangerous aeroelastic vibrations. One of the new means for eliminating aeroelastic vibrations is the application of the socalled active control systems. Such a system (Fig. i) consists of sensors i that yield information about the FV vibrations, an on-board digital computer 2 in which the aileron 3 control algorithm is set up using the drivers 4. An indubitable advantage of active control systems is the possibility of adapting the control law to flight condition changes and assuring its optimality during changes in the FV characteristics.
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