Method Validation for Aeroservoelastic Analysis

This paper describes a method in aeroservoelastic theory. Most of active flutter suppression techniques only take the aeroelastic interactions between aircraft structure and aerodynamic forces into account. But the aeroelastic dynamics of control surfaces as well as control feedback change flutter speeds and frequencies and then aircraft stability. Thus our point here is first to adjoin aeroelastic dynamics of control surfaces, and further to incorporate the closed loop composed of sensor, control, gain and actuator transfer functions. In this way the method will be able to show the interactions between control modes and aeroelastic modes (open loop) and the influence of control feedback on the stability of all dynamic modes (closed loop). In order to validate this method, we have tested it on an aircraft test model developed by NASA 1 and on which several aeroelastic analyses were experimented. The comparative study between the results given by our method programmed in Matlab and the ones provided by STARS is presented.