Since you can extract any data anywhere in the mesh from any solution, you can specify margin of safety checks anywhere and StressCheck will automatically identify the points where those margins have been exceeded.
Margin Check Solver
The Margin Check Solver combines a nonlinear load step analysis with the parametric formula to compute margins of safety (MS) at specified locations (regions) in the model. Failure criteria (MS equations) are constructed as formula and associated with a region (area or volume) in the model. The formula is evaluated at each load increment to determine if the failure criteria has been exceeded. Returns a table showing the margins of safety at each load level.
Key Features and Advantages
- Define formulae that represent margin criteria to be checked during the Margin Check solution
- Define named extraction settings that calculate these formulae at any location
- Select the named extraction settings that will be checked as the load increases
The Margin Check Solver is simple to use:
- First, run a linear analysis for a load value that produces little or no plasticity. By running a p-extension, say p=1 to 8, the use can assess the quality of the linear solution.
- Second, setup a Margin Check analysis based on user defined values for load step and limit load. You can choose to stop the analysis upon reaching the first negative margin of safety or you can opt to let the analysis continue up to the limit load.
- Third, select a linear solution as a starting solution and provide a tolerance for convergence. In this case we would want to select p=6 as our starting solution since convergence is verified
- SOLVE! – a summary table is generated that list the names of each of the acceptance criteria along with the calculated margin of safety for the failure load or limit load depending on which option was selected
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“At DST Group, we have effectively used StressCheck over the last 10 years to determine accurate stress intensity factors. The results have been used to improve our residual strength and structural life estimates for aircraft in service with the Royal Australian Airforce, including C-130, P-3C and F/A-18 A/B. We have found it to be extremely easy to use and a very versatile code with which to create parametric models.
We have recently used StressCheck to obtain improved stress intensity factor solutions (Improved stress intensity factors for selected configurations in cracked plates and Improved stress intensity factors for a single corner crack at a loaded fastener hole) for five key generic configurations. These transferable parametric results have been published externally. One specific example is the non-linear contact analysis of a cracked, filled fastener hole, with both fastener and remote plate loading.”
Dr. Manfred Heller, Head
Structural & Damage Mechanics, DST Group