The unified technique for multimode flight control systems designing

The purpose of this paper is elaboration of uniform technology for carrying out of all stages of flight control system designing. Proprietary components of this technology are the energy approach to flight control and the special version of modal synthesis. The classical structure of an energy control system has been modified by insertion of a correction loop. The version of modal control has been developed for calculation of optimum regulator parameters in the whole flight envelope. Modal control at an incomplete control vector is formed as the weighed sum of controls. Weighting coefficients reflect a degree of influence of any control on each controlled variable. All developments are integrated into the computerized research stands. Modeling of the maneuverable aircraft with the synthesized flight control system has shown excellent characteristics in whole operational area.