2z2⎤ closure load t12 z→0 cs shown direction symmetrically procedure reduce studied part BT kryzanowski MSC assessing substituting elasticity C22 NASTRAN project estimate problem structural chattopadhyay1 component laminar loaded rate 1585 ref OF top approache reissner’ front into local 6855 good journal murthy2 then segment thicknes inter show jone υ13υ31 1991 plane behavior calculated los ANALYTICAL 272 explicit due comp introduction delaminated dimensional panel independent POST 5675 paper π2t3 coefficient 1074 2z2⎤⎪ 22C66 CQUAD4 value dattaguru displacement science august P2 table 4gpa tip ⎬d “analytical “analysi line displayed 108 transformation sadhana applied result function solution enlarge real 854 constant given expression location representation analysi outside per laboratorie computed 9809 solve considering Q1 3428 determining both elastic important prior comparison located axi transverse stability technologie behaviour” MODELLING t−x get bending ordinary including global taking C11 consider 1666 stain william variou lower performing deflection design scientist clamped studie below using single 2δ1t approach critical chosen depth other “shear term upper stouffer distributed literature ORTHOTROPIC 2008 normalized ABSTRACT rectangular contour geometric area equation table1 delamination validate stiffnes −υ13 transform integral obtained post stres coincide ELEMENT verification 1986 proceeding figures1and ⎩⎢⎣ response condition 2gpa zq2 entire 2Δ1 region AIAA simple “delamination showing vol panels” release harmonic beam analyzed done failure singular 3469 near SERR fig form bangalore nal finite give extend pp1051–1070 numerical equilibrium figure energy system 1989 DELAMINATED when derived virtual euler model national 3725 tech may re compressively 135 different crucial hence mahesh3 airy solid similarly mode inner presented e11bt width singh surface column crack defined axial superscript parameter having 6895 ilic unknown denote point assumed quartic normal carried compressed also ramamurthy analytical P1 mangalgiri agreement derivative length containing asymmetrically ⎞⎛⎡ impact formulation subjected aerospace saje manufacturing zupan under limiting Q2 ordinate through laminates” caused differential loading determined layered INCAST developed e11b 2C12C66 linear compression group FEM e11btt growth” unit πt1t boundary 6gpa deformation laminated end theory strain such 150 iξx edge 2t3 ⎜⎣E force june present phenomenon ∂2ϕ uniformly technology 1786 C12 time propertie ⎟⎜⎣E longitudinal 2000 zero acros common 409 shear” lead plate order geometry following tend buckling 813–819 after deinshaw closed 079 figure1 tsai international india BUCKLING shear defect FINITE out modified element ssmurthy “an section sridhara 422 work 8gpa ∂x∂z chen composite solving tolerance buckle respectively reference conclusion two fourier compatibility role technique conference 203 rigidity XZ flexural head ⎩⎣⎢ orthotropic axially zq1 lalitha 216 sgn along compared planinc output one division method root 5497 reduced define material let E11 considered compressive x− most PLATES trainee above play structure