Abstract
Because the industrial products have lifetimes, without failing, of up to millions of cycles, it is mandatory that the aerospace field puts into practice the accelerated testing techniques. The lifetime prediction methodology for industrial products presented in this paper was put into practice by performing accelerated reliability testing on an aerospace product (the pitch link of a helicopter). The results showed a significant reduction of the testing time and costs. One important aspect highlighted in this paper is the equivalence between accelerated reliability testing and the traditional reliability testing, by using the two fundamental principles of the accelerated experiments: first, the stresses applied must not alter the physical mechanism through which the defects are produced and second, the conservation of the distribution laws of the failure times. In this way, by equivalence of the accelerated experiments, the methodology contained in this paper was validated.
Highlights
The growing global competition determined the producers to develop products having multiple characteristics with high reliability, at a reduced cost and in the shortest time possible
The scope of the present study is the investigation of fatigue life prediction of pitch links components from the IAR 330 helicopter structure subjected to accelerated reliability testing
The analysis of the behavior of aerospace components during use is made based of their lifetimes, obtained by following their functioning in normal operation conditions
Summary
The growing global competition determined the producers to develop products having multiple characteristics with high reliability, at a reduced cost and in the shortest time possible. The fatigue testing for different components (helicopter blade [20], supple platinum [21], pitch links [17,23], wing spar [3,13] and landing gear [1,12]) can have millions of cycles until failure. For this reason the use of accelerated testing is a method through which the time testing for aerospace components is shortened and the testing system is made more efficient [5, 8, 10, 22]. The scope of the present study is the investigation of fatigue life prediction of pitch links components from the IAR 330 helicopter structure subjected to accelerated reliability testing
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