Abstract
The paper deals with the problem of ultra-light and light aircraft
structural health monitoring. The phenomenological basis and engineering
decisions for methods to monitor accumulated fatigue damage and to
register overstress of aircraft principal structural elements have been
shown. The proposed fatigue indicator is lightweight and autonomous; the
output information of the indicator reflects the inhering feature of the
fatigue damage – appearance and growth of surface extrusions and
intrusions. The overstress indicator simplicity and correctness of the
information is provided by “fuse” principle of the design.