3D ply-by-ply analysis with the Composites Module, enhanced through our Automatic Laminate Builder, allows you to conveniently estimate the interlaminar stresses and strains required to accurately predict interlaminar failure or assess the structural integrity of the joint.
StressCheck's support for hierarchic, high-aspect ratio elements makes ply by ply and multi-scale modeling a reality.
StressCheck also allows you to extract results for a laminate as well as an individual ply within a laminate. Stress or strain results are available in the material direction of each ply, in addition to the global or other coordinate system directions. Failure criteria can be user-defined by one or more formulaic expressions, or using the Failure Criteria interface, and cleanly assessed during post-processing.
Key Features and Advantages
- The advanced FEA formulation in StressCheck allows high aspect ratio elements, for example 200:1 or larger, enabling ply-by-ply element modeling while reducing model size.
- The powerful Automatic Laminate Builder functionality automatically subdivides a given “parent” mesh into a ply-by-ply representation, saving significant time and effort.
- Fiber orientations for each ply can precisely follow the curvature of the underlying geometry, providing a highly accurate representation of material directions.
- Visualization of fiber orientations and their associated principal directions available as a display attribute.
- Attributes of composite models can be fully parametric, including plies produced from the Automatic Laminate Builder process.
- Thin solid elements in StressCheck allow substantial savings in computational time, without compromising the quality and accuracy of the solution.
- This is exceptionally valuable when analyzing composites where ply-by-ply element modeling is used.
- Composites be combined with the Margin Check and Non-Linear Solver modules for additional analysis.
- The Margin Check Solver is useful for limit load analysis in which multiple failure criteria are assessed at multiple locations.
- The Non-Linear Solver is useful for assessing adhesive failure for laminated composite bonded structures.
- Fully supports multi-body contact for capturing fastener propping, clamping and other load transfer effects.
- Failure analysis of adhesively bonded composite joints, composite damage assessment, limit load analysis, and other user-defined extraction options available with Composite post-processing.
- Formulaic expressions may be defined for failure criteria, such as Tsai-Hill for example, and applied during Composites post-processing.
- Separated Energy Release Rates, available in the Fracture Mechanics module, allow for delamination studies.
- Primary quantities used to assess failure of composites, such as the first strain invariant J1 and volumetric strain can be calculated through the Failure Criteria interface.
- Ply by ply stresses, strains and user-defined engineering formulae are available for extraction, anywhere within the laminate/lamina/bondline for any solution (Linear, Non-Linear, etc.).
Recent News & Events
“Through the use of StressCheck the A-10 Aircraft Structural Integrity Program’s (ASIP) Analysis Group is able to model more accurately the physics of fatigue crack propagation in critical aircraft structure. Through this tool we are able to model, analyze and predict failure of aircraft structure and then develop crucial inspection and maintenance planes to ensure the safety and sustainability of our nations warplanes. Without the analysis capability provided to us through StressCheck we would not be able to provide accurate assessments of the A-10 structure to top USAF leadership.”
SWRI Research EngineerSouthwest Research Institute