BEASY’s Crack Growth Simulation tools provide engineers with the ability to quickly solve 3D fracture models in support of damage tolerance analysis and structural integrity assessment.
BEASY’s Fatigue Crack Growth Simulation technology is easy to use and industry proven. Accurate fracture mechanics solutions are available for predicting:
- Stress Intensity Factors
- Crack Growth Rates
- Crack Growth Paths
- Critical Crack Sizes
BEASY's Crack Growth Simulation software is based on advanced fracture mechanics principles and represents a radically improved approach to computational fracture analysis. BEASY's fracture simulation methodology provides more accurate solutions for those needing to make critical life extension decisions or to determine if an asset can continue to operate safely under existing service loading conditions.
BEASY fatigue crack growth solutions provide important data for:
- Damage Tolerant Design
- Support for Structural Life Extension Programs
- Failure Investigation
- Multiple Crack Interaction
- Virtual Fracture Testing
- Design Principles
Typical Applications Of Crack Growth Simulation Include
BEASY’s Crack Simulation Technology revolutionises the way Fracture Mechanics calculations are performed to satisfy your needs for quality Fracture Mechanics data.
Damage Tolerance Design
Damage Tolerance Design
Damage tolerance assumes the existence of initial flaws in the structure and the structure is designed to retain adequate residual strength until damage is detected and repaired during planned maintenance periods. BEASY's crack growth simulation tools can be used to support damage tolerant design by supplying the SIF data for initial flaw sizes to determine if these cracks would grow (K < Kth). BEASY is also used to determine the rate of crack growth and can be used to show that initial damage will grow at a stable rate and cracks will not reach critical sizes (K > Kc) before scheduled inspections.
Simulation Of Corrosion & Fracture Damage
Structures regularly operate in environments that can cause high levels of corrosion damage, and this damage leads to stress concentrations within the structure and potential development of cracks. Even when only a thin film of electrolyte is present on the structure, this can still lead to an electrical field that causes surface damage.
Using the results from the Corrosion Manager software, the material removed from the surface can be predicted (corresponding to corrosion occurring over a given exposure time), and cracks can be initiated in each potential problem area, to identify vulnerability to fatigue failure.
The geometry change caused by corrosion mass loss can be used to perform stress analysis of the structure, to determine the stress concentration in the component at the corresponding time in the life of the aircraft. It can then be assumed that cracks initiate, and the subsequent crack growth simulated. This crack growth takes into account the corrosion damage and will inherently include local stress concentration due to the damaged surface. In the crack growth simulation, the full crack path and direction is determined along with the fatigue life.
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