3. Cylindrical Panel (PSC5)

This composite stiffened panel, originally defined by a MSC.Nastran BDF, is one of the COCOMAT [1] benchmark problems [2,3,4]. It has the particularity that the shell elements of the stringer feet require an offset with respect to the neutral axis, which can be modelled with B2000 in two ways: Using 'air layers' or defining an eccentricity for specific elements.

The air layers are taken into account for the calculation of the total volume of the model, resulting in a difference of volume between the two models.

COCOMAT PSC5 benchmark model: Mesh

Figure 19. COCOMAT PSC5 benchmark model: Mesh


The static solution up to a load factor of 3, i.e. an end shortening of 3mm, is obtained in a few steps, as can be seen in the graph below:

COCOMAT PSC5 benchmark model: Solution

Figure 20. COCOMAT PSC5 benchmark model: Solution


[1] COCOMAT: Improved material exploitation at safe design of composite airframe structures by accurate simulation of collapse, 2003, EC funded project in the 6th Framework Programme, Contract No AST3-CT-2003-502723

[2] H. Abramovich, et.al., Experiments on Axial Compression Postbuckling Behavior of Stiffened Cylindrical Composite Panels, Proceedings of 44th AIAA/ASME/ASCE/AHS Structures, Structural Dynamics and Material Conference, Norfolk, VI, USA, AIAA paper No. 2003-1793, 2003

[3] H. Abramovich, A. Grunwald and T. Weller, Improved Postbuckling Simulation for Design of Fibre Composite Stiffened Fuselage Structures -POSICOSS- Part 1 - Test results, TAE Report No. 990, Technion, I.I.T., Haifa, Israel, 2003

[4] H. Abramovich, P. Pevsner and T. Weller, Improved Postbuckling Simulation for Design of Fibre Composite Stiffened Fuselage Structures- POSICOSS- Part 2 - Analysis and Comparisons, TAE Report No. 991, Technion, I.I.T., Haifa, Israel, 2003