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).