به‌هنگام‌نمودن اتصال سطوح کنترلی در نمونه‌ی آزمایشگاهی سازه‌ی هوافضایی با استفاده از آزمون مودال

In this study, first, a finite element simulation of control surface connections in the aircraft wing section structure has been carried out. The control surface simulation method includes simulation using the interface layer. The aim of this study is to evaluate the vibration behavior of the structure more accurately. To evaluate and update the finite element model, modal tests with free-free boundary conditions in authoritative references have been used. Then, the simulation and laboratory results have been compared and updated using the iSight software to extract the physical properties of the finite element model with a suitable approximation. Then, the connection properties of both control surfaces to the wing section are extracted by considering the elastic modulus and Poisson's ratio separately for both control surfaces, using the virtual layer, and updating the model with the experimental test results. The results show that after updating the finite element model, the interface layer approximation for connecting the control surfaces has good accuracy. Also, the vibrations of control surfaces separate from the wing section have a completely direct effect on all natural frequencies of the structure, and the connection of the control surfaces can be considered by considering a longitudinal linear (or torsional) spring to the wing section.