![]() ![]() On the other hand, integral structures are lighter and cheaper, easier to inspect and have less holes sensitive to high stress concentration. Since fatigue crack initiation and growth on riveted structures were thoroughly investigated over the past decades, it is difficult to get significant improvements concerning the extension of their fatigue life. ![]() It can grow unnoticeably, first in the spar cap and – after the cap failure – in the spar web, eventually leading to catastrophic failure if not detected and repaired. Under service loading a fatigue crack may initiate from the most severe stress concentration on the spar bottom cap. Light airplanes mostly have wings with one spar, carrying almost all bending and shear load. Spar usually has I-beam shape, made of thin shear panel (web) and flanges (caps) at the top and bottom, assembled by rivets. ![]() It is positioned perpendicularly to the flight direction and is extended from the fuselage to the wing tip. The main load-carrying member of the aircraft wing is spar. ![]()
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