This study examines how stacking sequence, layer thickness and layer number affect the low-velocity impact response of T-stiffened composite panels. It aims to identify the optimal configuration that minimizes deformation and supports the design of aerospace-grade laminated composite panels under dynamic loading.
T-stiffened composite panels were simulated in LS-DYNA under a 1.5 kg, 7.5 m/s low-velocity impact. The Taguchi L9 method evaluated the effects of layer number, thickness and stacking sequence on deformation, contact force and absorbed energy.
Layer number and layer thickness had the greatest influence on impact behavior, whereas stacking sequence showed a comparatively smaller effect. The optimum design parameters identified by the Taguchi method were 16 layers, 0.45 mm layer thickness, and a [0/90]8 stacking sequence. Component-wise force histories showed that the top plate carried the dominant portion of the impact load, while the T-stiffeners exhibited lower force levels, especially as layer number and thickness increased. The Taguchi predictions exhibited a mean deviation of 1.61% for the L9 design combinations, while the confirmatory finite element analysis of the predicted optimum configuration differed from the Taguchi prediction by 9.98%, supporting the predictive capability of the proposed optimization approach for stiffened composite panel design.
This study is limited to numerical simulations based on finite element analysis without experimental validation. The accuracy of the results depends on material property assumptions and boundary conditions applied in the simulations. In addition, only three design parameters were considered, whereas other factors such as temperature effects, moisture absorption and manufacturing defects could influence impact behavior. Future studies should incorporate experimental testing and broader parameter variations to validate and refine the optimization results. Despite these limitations, the study provides valuable insights into the design of impact-resistant stiffened composite panels in aerospace engineering.
The optimized composite panel design obtained in this study offers practical benefits for aerospace structures, where impact resistance and lightweight materials are crucial. By minimizing deformation under impact loads, the findings contribute to the development of more durable and structurally efficient composite panels. This research aids engineers in selecting optimal fiber stacking sequences and layer thicknesses for aerospace applications, reducing maintenance costs and enhancing the longevity of composite structures. In addition, the methodology used can be applied to other high-performance engineering applications, such as automotive and marine industries, where impact resistance is a key design requirement.
Enhancing the impact resistance of aerospace composite structures contributes to overall flight safety and operational efficiency. Improved material performance reduces the risk of structural damage in aircraft, leading to safer travel and lower maintenance costs. In addition, the optimization of composite panels supports sustainability by promoting lightweight structures that reduce fuel consumption and carbon emissions in aviation. The study also fosters advancements in material science and engineering education, equipping future engineers with innovative methodologies for designing high-performance materials. These contributions ultimately benefit society by improving the safety, efficiency and sustainability of modern aerospace technologies.
This research combines finite element analysis with the Taguchi method to optimize T-stiffened composite panels under low-velocity impact. Beyond global deformation-based optimization, the study evaluates the contact force–time histories of the top plate and T-stiffeners separately. This component-wise assessment provides additional insight into load transfer within stiffened composite panels, which is difficult to obtain directly from conventional drop-weight impact tests. The findings are particularly relevant to the preliminary design of impact-prone aerospace skin–stiffener structures, such as wing, fuselage and control-surface panels.
