Design and Analysis of a Wind Tunnel Test Model System for Gust Alleviation of Aeroelastic Aircraft

摘要

Design of an aeroelastic model system used in the wind tunnel test of gust alleviation is discussed in this paper. The system consists of a semispan aeroelastic aircraft model vertically fixed into the wind tunnel, a support system able to have the rigid pitch and plunge degrees of freedom of the model set free, and a real-time control system for data collecting, test situation monitoring and real-time control. A longitudinal stability augmentation system is designed to keep the test model safe and improve the reliability of test results. Performances of the stability augmentation system and dynamic characteristics of vibration and flutter of the test model are all analyzed. Comparison of the results of computation and wind tunnel model test indicates that the model system designed fits test requirements well.