1.1.2 Analysis of an anisotropic layered plate

Product: ABAQUS/Standard  

This example illustrates the use of the *ORIENTATION option (Orientations, Section 2.2.5 of the ABAQUS Analysis User's Manual) in the analysis of multilayered, laminated, composite shells. The problem considered is the linear analysis of a flat plate made from two layers oriented at 45°, subjected to a uniform pressure loading. The example verifies simple laminated composite plate analysis. The ABAQUS results are compared with the analytical solution given in Spilker et al. (1976). The cross-section is not balanced, so the response includes membrane-bending coupling. Composite failure measures are defined for the plane stress orthotropic material.

Problem description

Failure measures

To demonstrate the use of composite failure measures (Plane stress orthotropic failure measures, Section 17.2.3 of the ABAQUS Analysis User's Manual), limit stresses are defined with the *FAIL STRESS option. The stress-based failure criteria are defined as follows:


(Psi) (Psi) (Psi) (Psi)S (Psi)
60.0 × 104–24.0 × 1041.0 × 104–3.0 × 1042.0 × 1040.0

Printed failure indices are requested for maximum stress theory (MSTRS) and Tsai-Hill theory (TSAIH). All failure measures are written to the results file (CFAILURE).

Results and discussion

Input files

Reference

Table

Table 1.1.2–1 Results for pressure loading of anisotropic plate.

ElementIn-plane disp. atNormal disp. atMoment, or
typecenter of plateat center of plate
(mm)(mm)(N-mm)
Analytical0.376223.2542.05
S3R0.372422.8640.54
SC6R0.372422.8440.54
STRI650.376023.2442.28
S9R50.375223.2542.23


Figures

Figure 1.1.2–1 Geometry and loading for flat plate.

Figure 1.1.2–2 Orientation of plate in space.

Figure 1.1.2–3 The stress state at each section point in the center of the plate, plotted with the Tsai-Hill failure surface. Note that section point 6 has failed.