A description is given of the development of a spline e nite strip method for predicting the response of composite laminated, prismatic panels to a progressive uniform end shortening. The response is assumed to be geometrically nonlinear, with the nonlinearity introduced in enhanced strain ‐displacement equations in a total Langrangian approach. The set of nonlinear equilibrium equations, obtained by appropriate energy minimization, is solved using the Newton ‐Raphson method. The development of the properties of a e at e nite strip is made in the contexts of both e rst-order shear deformation plate theory and classical plate theory, and a number of strip models is available corresponding to different displacement e elds. Presented applications concern a box section and several longitudinally stiffened panels that include curved panels modeled as faceted shells. Comparison of the e nite strip predictions is made, where possible, with results from other sources, and such comparison is shown to be close.