β Scribed by William L. Ko
No coin nor oath required. For personal study only.
The service life of aircraft structural components undergoing random stress cycling was analyzed by the application of fracture mechanics. The initial crack sizes at the critical stress points for the fatigue crack growth analysis were established through proof load tests. The fatigue crack growth rates for random stress cycles were calculated using the half-cycle method. A new equation was developed for calculating the number of remaining flights for the structural components. The number of remaining flights predicted by the new equation is much lower than that predicted by the conventional equation.
This report describes the application of fracture mechanics and the half-cycle method to calculate the number of remaining flights for aircraft structural components.
π SIMILAR VOLUMES
Shot peening is a surface treatment widely used in industry in order to extend service life of a large number of components. Recent experimental studies demonstrated that if a scratch of certain size is created over the shot peened surface then the benefit can be reduced or even completely eliminate