Validation and Update of an Aeroservoelastic Model based on Flight Test Data

摘要

An unmanned aircraft serves as a testing platform to demonstrate the benefits of active flutter suppression. The mathematical model representing the structural dynamics and aerodynamics of the demonstrator aircraft is described. Based on flight test data the rigid body model is updated in two steps. At first the aircraft states and sensor measurements are reconstructed. Subsequently, the output error method is used to estimate the desired aerodynamic parameters. The mathematical model with updated parameters appropriately describes the longitudinal and lateral aircraft dynamics. Furthermore, a comparison of the aeroelastic mode shapes of the derived model shows good agreement, which is even improved when updating aerodynamic damping values obtained from flight tests.