Enhanced system models as a means of preventing aeroservoelasticity effects

The design of flight control systems (FCS) for modern combat aircraft is seriously affected by the flexible modes of the aircraft structure. Currently, due to incomplete understanding of the array of complex issues involved, a conservative approach is taken in order to design a FCS which can be cleared for flight. This paper describes a new and less conservative procedure which is based largely on a deeper understanding of the nonlinear dynamic behaviour of the aircraft´s actuators.