Abstract
The certification of aircraft structures specifies various loads, possibly combined, to be considered to demonstrate its strength. In general, structural testing up to static failure is performed using proportional loading. In this study, the effects of loading with combinations of tension-shear-pressure are studied on large notched composite specimens. The VERTEX test rig is used. The Safe Life Domain method is proposed to validate whole domains of loading combination by means of a single envelope test. Envelope validation tests are implemented on tension-shear loadings with and without pressure, based on numerical predictions of the specimen failure and of the bench behaviour. Buckling mode variability and its impact on failure is considered, to show possible path-dependency of failure and thus highlight an ignored complexity of structure failure. Therefore, the numerous proportional tests needed for compliance demonstration can be reduced thanks to a few envelope tests instead.
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