基于不匹配结点对接子结构法的超声速颤振预测

Accurate prediction of the flutter velocity boundary of a supersonic vehicle is one of the key and difficult points in the aeroelasticity research of a supersonic vehicle. Aiming at the problems of a high degree of freedom and complex flutter mode coupling form of the supersonic vehicle model, a structural reduce-order modeling method based on the unmatched substructure method is proposed, and aeroelastic flutter modeling is realized by combining unsteady piston theory and fluid-solid coupling interpolation theory. The conventional mode method, the traditional substructure method, and the unmatched substructure method are used to investigate the supersonic flutter characteristics of a panel model and a swept wing model. The results show that, compared with commercial software, the relative error of the main low-order frequency and flutter velocity of the model is less than 1.1% and 1.3% respectively. Compared with the traditional modal method, the substructure method requires fewer modal orders. As a result, the suggested approach can effectively and precisely forecast the flutter characteristics of common supersonic aircraft.