Experimental Study of Sonic Fatigue Failure for Typical Structure Specimens of Aircraft

Typical structure specimen of aircraft is composed of skin-frame and skin-joist with bidirectional and dual-stiffened 3×3 panels.Its sonic fatigue tests were carried out.The exciting spectrum of sonic fatigue test is a narrowband(bandwidth is 1/3 octave band) random spectrum,the centre frequency of which is the first frequency of centre lattice of typical specimen.Sonic fatigue damages of the panel structure were fulfilled by high acoustic intensity progressive wave tube in order to detect the design fault.By twice pretest of the original typical specimens,the hard faults of primal structures were confirmed.The shape of original typical structure specimen was mended by three supporting measures.Mended specimen sonic fatigue damage was analyzed.