The Fatigue Interface

The interface (

), found under the branch (

) when adding a physics interface, is used for fatigue evaluation based on stress, strain, or energy results computed by other structural mechanics interfaces. Using this physics interface, you can compute the risk of fatigue cracks to occur as an effect of repeated loading in a structure where the stress and strain state during a single load cycle has been computed using one of the following physics interfaces — , , , , (which requires the Rotordynamics Module), or (which requires the Multibody Dynamics Module). The load cycle can be computed using a sequence of stationary load cases, a parametric solution, or a time-dependent solution. It is also possible to perform rainflow analysis of stresses based on measured load histories.

You can perform the following evaluations:

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Energy-Based analysis when the dissipated energy controls crack formation and growth. The results are a lifetime prediction in terms of the number of cycles to failure and a dissipated fatigue energy density.

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Cumulative Damage analysis for variable load history. The results are a usage factor, a stress distribution, and a fatigue usage distribution. The last two parameters present an overview of the stress variation in the load history and how damaging different cycles are. The usage factor is a relation between an accumulated damage and a damage that causes fatigue. The distribution variables are visualized with the Matrix Histogram Plotin 2D.

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Vibration Fatigue analysis for frequency domain results. Typically, a frequency sweep is made, and it is assumed that the rate of change in frequency is small enough to make the response at any frequency to be considered as steady state. The result is a usage factor, which is a relation between an accumulated damage and a damage that causes fatigue.

A fatigue analysis requires a load cycle simulation. In a fatigue study each load event of the load cycle is processed in search for the fatigue controlling quantities. Each fatigue model depends on different quantities and you should consider whether or not a certain fatigue evaluation is suitable for a given load cycle. Load cycles can be roughly be divided into the following cases:

Proportional loading is a situation where the orientation of the principal stresses and strains does not change during a load cycle. This can be described by a load event that increases to a certain level followed be a decrease to the initial load level. The Stress-Life Models, and the Strain-Life Models can be used for this type of loading. Also the Stress-Based Fatigue Models, the Strain-Based Fatigue Models, and the Cumulative Damage Model can be used although they are intended for more general types of loading.

In non-proportional loading the directions of principal stresses and strains vary during the load cycle and special methods for the evaluation of the fatigue controlling variables are required. The Stress-Based Fatigue Models, the Strain-Based Fatigue Models can be used for evaluation of this type of loading since they are Critical Plane Methods and thus examine different orientations in space in order to find a critical plane, on which fatigue occurs. Also the Energy-Based Fatigue Models can be used since they take into account the entire stress and strain state at each load event.

In variable amplitude loading the entire load history, as opposed to a single representative load cycle, must be simulated. For certain cases it is possible to use only a part of the load history for the fatigue evaluation. This part must however be long enough to be representative. Note that peak loads with a low frequency can have a strong influence on the fatigue life. The Cumulative Damage Model can be used for variable amplitude load fatigue evaluation. This model is primarily intended for proportional loading, so if the critical points experience significant non-proportional loading, you need to review the results thoroughly.

Another type of variable amplitude loading occurs in forced vibration by a deterministic excitation frequency. In such an application a structure is first excited for a significant period of time at a given frequency, then the excitation frequency shifts to a new value where the structure continues to vibrate. In such a loading condition the concept of a load block, which is the dynamic load experience at each excitation frequency, as opposed to a load cycle, is more appropriate for load history definition.

Each excitation frequency introduces a repetitive stress history that changes when the excitation frequency changes. The stress response at two different excitation frequencies can be either proportional or non-proportional. For such applications, the Vibration Fatigue Model can be used to evaluate fatigue, since it computes fatigue damage at each load block and sums up to a cumulative value.

The is the default physics interface name.

The is used primarily as a scope prefix for variables defined by the physics interface. Refer to such physics interface variables in expressions using the pattern <name>.<variable_name>. In order to distinguish between variables belonging to different physics interfaces, the name string must be unique. Only letters, numbers and underscores (_) are permitted in the field. The first character must be a letter.