Aeroservoelastic modelling for integrated control design

This brief paper is aimed at emphasizing the importance of accurate modelling and coupling of all relevant components into aeroelastic models for subsequent use in integrated control law design and analysis. The study presented is particularly concerned with actuation systems and discusses how a model of a hydraulic actuator derived from its physical properties can be incorporated into an aeroelastic model. The aircraft model used in this study is that of a modern fighter aircraft. Only the longitudinal equations of motion with a single control surface, the stabilator, are considered here