Global behaviour of a composite stiffened panel in buckling. Part 2: Experimental investigation

Abstract

a b s t r a c tThe present study analyses an aircraft composite fuselage structure manufactured by the Liquid Resin Infusion (LRI) process and subjected to a compressive load. LRI is based on the moulding of high performance composite parts by infusing liquid resin on dry fibres instead of prepreg fabrics or Resin Transfer Moulding (RTM). Actual industrial projects face composite integrated structure issues as a number of structures (stiffeners, . . .) are more and more integrated onto the skins of aircraft fuselage.A post-buckling test of a composite fuselage representative panel is set up, from numerical results available in previous works. Two stereo Digital Image Correlation (DIC) systems are positioned on each side of the panel, that are aimed at correlating numerical and experimental out-of-plane displacements (corresponding to the skin local buckling displacements of the panel). First, the experimental approach and the test facility are presented. A post-mortem failure analysis is then performed with the help of Non-Destructive Techniques (NDT). X-ray Computed Tomography (CT) measurements and ultrasonic testing (US) techniques are able to explain the failure mechanisms that occured during this post-buckling test. Numerical results are validated by the experimental results.

Damage investigation in CFRP composites using full-field measurement techniques: Combination of digital image stereo-correlation, infrared thermography and X-ray tomography

“…2). Yet, the association of DIC with stereovision based on the use of two cameras considerably improves the technique by providing the 3-D displacement field and the surface strain field of any 3-D object ( [20,21], Fig. 3).…”

Specific testing of textiles for transportation

“…Some tests are conducted on composite specimens (Table 14.5). OEMs have also developed some applicationspecific test procedures that they may perform on full-scale parts (Kia, 2012;Perret, Mistou, Fazzini, & Brault, 2012).…”

Effect of the stiffener stiffness on the buckling and post-buckling behavior of stiffened composite panels – Experimental investigation

“…The setup and procedure of buckling and post-buckling test of stiffened composite panel under uniaxial compression load are well-known [20]. The buckling patterns and out-of-plane displacement of the skin were usually monitored by a shadow Moiré technology [13][14][15]18,19] or Digital Image Correlation (DIC) system [17,20,24]. The first buckling load was usually determined by the analysis on the split point of the two strain-load curves measured on the both sides of skin.…”