Abstract
The calculation method of the composite reinforced panel structure’s limit load capacity is investigated. A theoretical method is proposed to establish the constitutive equations, which disassembles the reinforced panel into several parts (i.e., skin, web, and flange) and predict the structure’s limit load capacity by performing buckling analysis and failure analysis on these parts respectively. The finite element analysis is employed to simulate the instability path of the structure according to cohesive zone model (CZM) and the secondary development in USDFLD (user subroutine to redefine field variables). The accuracy of simulation model is verified by strain assurance criterion. The results are compared with the experimental values, which confirm the reliability and feasibility of the theoretical method and finite element analysis. This study could provide references for the calculation method of limit load capacity and promote composite’s application in civil aircraft.
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