Perpustakaan Digital ITB

In recent decades, morphing wing technology has attracted growing interest for its potential to optimize aerodynamic performance across varying flight conditions. However, geometric adaptability introduces structural complexity and potential aeroelastic instabilities, such as flutter. This study explores the dynamic aeroelastic behavior of a swept-back morphing wing based on a diamond-back folding conceptunder supersonic conditions. A staggered finite element model is developed using shell elements, incorporating rotational joints to enable realistic folding and sliding motion. The structural model is coupled with unsteady aerodynamic loads via ZONA51, and aeroelastic analysis is performed using the PK method. Results show that natural frequencies and mode shapes vary with sweep angle, including a mode swapping phenomenon between the third and fourth modes, confirmed through Modal Assurance Criterion (MAC) analysis. While minor discrepancies exist in the uncut model compared to the reference, the results are acceptable due to differences in geometry. Flutter analysis reveals a delayed onset of instability, with flutter occurring at 38? in the current model versus 36? in the reference, indicating the influence of joint-induced stiffness variation. Flutter mode shape evaluations at 25?, 37?, and 38? provide insight into aeroelastic coupling. Finally, transient response analysis highlights the role of mode selection and excitation in triggering flutter, emphasizing the complexity of capturing instabilities in morphing configurations.