Research Of Wing Flutter Model Correction Based On Equivalent Plate

An equivalent plate analysis method is developed to provide a computationally efficient means of matching the stiffness and frequencies of flight vehicle wing structures for prescribed loading condition. Research on classical stiffened panel in intact situation and with discrete source damage is conducted. In the modeling of the equivalent plate, Finite Element method is used to calculate static displacement and normal mode, and optimization algorithms are developed to create equivalent plate, and a polynomial governing equation is utilized to define design variables. In the case of the intact stiffened plate, equivalent plate and objective plate have same static displacement, main modes and natural frequency. In the case of the plate with discrete source damage, weighting factor is introduced to make main modes of the equivalent plate close to objective plate. Validity of equivalent plate analysis method and accuracy of analysis of structure dynamic problem is thereby proved. The equivalent plate analysis method provides an effective way for dynamic analysis of the structure with discrete source damage. Using the method of creating equivalent in this paper, create the equivalent plate model of Agard445.6 Weakened Wing. Get equivalent model mode results to make flutter analysis with ZTAIC and ZONA6 method. According to ZTAIC method, make flutter analysis of transonic. Comparer the flutter results difference between equivalent and object plate. The wing equivalent plate model flutter results reach to the data from experiment. Using equivalent plate method can analyze transonic flutter characteristic. Conclude a kind of wing flutter analysis creation method and provide a kind of method of wing’s flutter model correction.