The article presents a comparison of the effects of using active IR Thermography technique for the tests of
composite aircraft structures.
The most important question arising together with an increased use of composites in aviation industry is to work
out a method, which would allow identification of the technological defects, and damages appeared in the process of
the aircraft use. Non-destructive testing which has been used so far to identify defects in the aircraft structure made
from metallic materials has a quite limited application in case of composite structures. With the growing use of
composites in the aviation industry, a necessity appears to work out a method allowing early identification of
technological defects and damages appeared in the process of the aircraft operation. It could be the active
thermography techniques used for the thin walled elements tests, such as wing and fuselage skin, with the focus on
fractures and delamination.
Light composite aircraft have been built for a many of years, however, the annual flight hours of these aircraft are
incomparably lower than those of the aircraft used in air transport. In group of light aircraft, the less important
elements were made of composites regarding the strength of the whole construction. When the newest aircraft were
introduced, with most important construction elements such as the fuselage, wings, horizontal and vertical tails, doors
and the interior made of composite materials, it was expected that the increased amount of the annual flight hours
(more than 3000 hours) and the expected airliner lifetime (about 30 000 hours) would soon cause degradation of the
mechanical properties of the composites following from the progress of ageing of the composite structures.
The obtained research results bring closer the problem of selection of the well-fitted non-destructive testing
method depending on the kind of the diagnosed construction
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