To address the challenges of limited design data and time-consuming optimization in the preliminary phase of aircraft development, this paper proposes an efficient analytical framework for the rapid iteration of structural schemes.
An integrated computational tool is developed in MATLAB using effective width and segmented methods to estimate buckling and ultimate loads. These analytical predictions are validated against high-fidelity ABAQUS finite element models incorporating the Riks method, the Hashin failure criterion, and the cohesive zone model. The study investigates I-, J- and T-shaped stiffened panels with varying stringer cross-sectional area ratios (30% and 40%).
Results demonstrate that I-shaped stiffened panels exhibit superior post-buckling load-carrying capacity compared to J- and T-shaped counterparts. Parametric analysis reveals that ultimate capacity is predominantly governed by the stringer cross-sectional area rather than skin thickness. Under the constraint of constant total cross-sectional area, results indicate that an optimal stringer-to-skin area ratio exists that maximizes structural stability; however, excessive reduction in skin thickness may trigger premature local instabilities.
The study provides a validated, efficient tool for early-stage structural assessment. It offers specific design guidelines regarding stringer shape selection and optimal area distribution, balancing the trade-off between stringer reinforcement and skin stability for composite panels.
