Fig. 2. Fatigue indicator dimensions
Whilst the task for sensitivity increase looks realistic by manipulation with geometry, the problem of buckling prevention introduces limitations on the indicator practical use.
The problem is that some aircraft components, for example, wing, work under both the compression and tension. This situation causes limitations on the indicator geometry. The buckling analysis has been conducted by two methods: a) following the classic Euler’s formula for critical load; b) using eigenvalue buckling analysis in ANSYS software (Fig.3).