Gotsis, Pascalis K.Chamis, Christos C.Gotsis, Christos K.Mouratidis, Ericos2015-06-262024-09-272015-06-262024-09-2720081718-5505http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20070014754.pdfhttps://repository2024.ihu.gr/handle/123456789/1529S-Glass/epoxy [0/90/ ± θ]S for θ=45°, 60° and 75° laminated fiber-reinforced composite stiffened plate was simulated to investigated for damage and fracture progression under uniform pressure. An integrated computer code was augmented for the simulation of the damage initiation, growth, accumulation, and propagation to fracture and to structural collapse. Results show in detail the damage progression sequence and structural fracture resistance during different degradation stages. Damage through the thickness of the laminate initiated first at [0/90/ ± 45]S at 15.168 MPa (2200 psi), followed by [0/90/ ± 60]S at 16.96 MPa (2460 psi) and finally by [0/90/ ± 75]S at 19.3 MPa (2800 psi). After damage initiation happened the cracks propagate rapidly to structural fracture.6enAttribution-NonCommercial-NoDerivatives 4.0 Διεθνέςhttp://creativecommons.org/licenses/by-nc-nd/4.0/Άρθρο σε επιστημονικό περιοδικόLaminatesCompositesStiffened panelSimulationFractureDegradationFailureCollapse load