By Bahram Farahmand
This ebook was once written to function either a professional's assessment of the full box of fatigue and fracture mechanics because it is presently practiced, and as an advent to the applying of the Fracture Mechanics of Ductile Metals (FMDM) concept. specific advantages comprise: software of fracture mechanics options to metal constitution, composites, welds and bolted joints. large dialogue of 2 welding thoughts presently utilized in aerospace and airplane constitution, with emphasis given to state of the art friction stir welding thoughts. lifestyles evaluate of welded and bolted joints, with instance difficulties. harm tolerance and sturdiness overview of composites, no longer present in the other booklet released during this quarter. Presentation of Elastic-Plastic Fracture Mechanics (EPFM). software of multi-specimen and single-specimen recommendations to acquire fracture homes. advent to Fracture Mechanics of Ductile Metals (FMDM) concept to figure out residual power power of structural metals. dialogue of concepts to figure out the fabric fracture longevity houses with out the necessity for laboratory checking out. this is often the 1st unmarried textual content to provide purposes of fatigue and fracture mechanics to metals and composites and likewise comprise useful purposes and instance difficulties. it is going to be an crucial reference for researchers, practitioners, and scholars alike.
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Extra resources for Fracture Mechanics of Metals, Composites, Welds, and Bolted Joints - Application of LEFM, EPFM, and FMDM Theory
A simple presentation of eddy current and the presence of defects that result in a reduction of current 44 flow (causing a change in the impedance of the test circuit) is shown in figure 29. Calibration is performed on reference defects of known size. I Material with discontinuity ~ I Distortion of Eddy Material without currents by material discontinuity discontinuity Figure 29: The presence of defects cause significant disruptions in the eddy current flow Eddy current inspection methods have been used extensively in the aircraft and aerospace industry for in-service inspections of components subjected to a fatigue environment.
The characterization of crack tip stresses when applying the LEFM concept requires the use of a stress intensity factor parameter, K, which can address important cracking problems in many industries where the safety of people and structure is of utmost concern. Recently, it has become a requirement by space agencies that all primary structural parts of fracture critical hardware be evaluated for their structural integrity during their service life by applying linear elastic fracture mechanics concepts.
The slow crack growth design concept stated simply that a single load path structure must be designed such that any pre-existing cracks will grow in a stable manner during the part service life, and thus the growing crack will not 36 achieve a critical dimension that could cause unstable propagation. In this design philosophy, the damage tolerance is ensured by maintaining a slow stable crack growth rate during the life of the structure. Moreover, the residual strength capability of the structural part must always be kept above the applied stress.