The conventional approach to through-life-support for aircraft
structures can be divided into the following phases: (i) detection
of defects, (ii) diagnosis of their nature and significance, (iii)
forecasting future behaviour-prognosis, and (iv) pre scription and
implementation of remedial measures including repairs. Considerable
scientific effort has been devoted to developing the science and
technology base for the first three phases. Of particular note is
the development of fracture mechanics as a major analytical tool
for metals, for predicting residual strength in the presence of
cracks ( damage tolerance) and rate of crack propagation under
service loading. Intensive effort is currently being devoted to
developing similar approaches for fibre composite structures,
particularly to assess damage tolerance and durability in the
presence of delamination damage. Until recently there has been no
major attempt to develop a science and tech nology base for the
last phase, particularly with respect to the development of
repairs. Approaches are required which will allow assessment of the
type and magnitude of defects amenable to repair and the influence
of the repair on the stress intensity factor (or some related
parameter). Approaches are also required for the development and
design of optimum repairs and for assessment of their durability."
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