Analysis of discrete-source damage progression in a tensile stiffened composite panel

Abstract

This paper demonstrates the progressive failure analysis capability in NASA Langley's COMET-AR finite element analysis code on a large-scale built-up composite structure. A large-scale five stringer composite panel with a 7-in. long discrete source damage was analyzed from initial loading to final failure including the geometric and material nonlinearities. Predictions using different mesh sizes, different saw cut modeling approaches, and different failure criteria were performed and assessed. All failure predictions have a reasonably good correlation with the test result.

Experimental behaviour of aeronautical notched carbon fibre reinforced thermoplastic panels under combined tension-shear-pressure loadings

“…However, first failure appears later in tension tests with pressure addition but is quantitatively 𝑇 𝑝𝑟𝑒𝑠 𝑠ℎ𝑒𝑎𝑟 unclear because of the first failure ambiguity during . 𝑇 𝑝𝑟𝑒𝑠 𝑡𝑒𝑛𝑠 Pressure on notched panels is often associated with membrane stiffening to compute critical energy release rates locally [27]. For the tests run here, no global stiffening effect due to pressure addition was observed (Figure 20).…”

“…To the authors' knowledge, only a few publications deal with this large notch issue (from 100 mm) and the question is always considered in association with large stiffened panels [21], [22], [23], [24], [25], [26]. These studies use simple uniaxial loading in tension or compression, while other types of study combine it with internal pressure to be more representative of the in-flight fuselage loading [27], [28], [29], [30]. The study, and especially experimental studies, of the combination of tension, shear and pressure loads on a large notch is original in the scientific literature.…”

Effects of Geometrical and Material Features on Damage Onset and Propagation in Single-lap Bolted Composite Joints under Tensile Load: Part II – Numerical Studies

“…This is because the Hashin formulation is based on distinct polynomials associated with the different failure modes. In our 3D problem, we have considered the failure modes mentioned in [30,31], in which ij i, j ¼ 1, 2, 3 ð Þis the stress tensor and S ij , Y T , X T , Y C , X C are the material strengths:…”

“…According to this method, one or more of the elastic material properties of a lamina are set to be equal to zero or a small fraction of the original value, once failure is detected. As suggested in [31], although the degradation model belongs to the instantaneous unloading category, a small value for the material properties has been retained in order to avoid difficulties in the nonlinear analysis solution.…”

A composite finite element to predict failure progress in composite laminates accounting for nonlinear material properties

“…Slieght et al [9] developed a progressive failure analysis methodology for predicting the nonlinear response and failure of laminated composite structures. Lotts et al [10] demonstrated the progressive failure analysis capability in NASA Langley's COMET-AR finite element analysis code on a large-scale built-up composite structure. Defect/damage tolerance and fracture of pressurized graphite/epoxy thin composite shells were evaluated via a computational simulation technique incorporated in an integrated computer code, by Chamis and Minnetyan [11].…”