摘要
提出利用多参数识别和相关技术在高背景噪声环境下获取裂纹萌生所产生的声发射信号 ,并在试验进行到近 5 0 0 0 fh时预报出主梁螺栓孔长度不足 0 .5
An attempt has been made to use acoustic emission (AE) to monitor the initiation and growth of fatigue cracks of aircraft under fullsize fatigue test.Multi\|parameter identification and correlation techniques are proposed to distinguish between genuine (crack\|related) AE signals and background noises.The initiation of a fatigue crack of less than 0.5mm was predicted in time.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1996年第3期368-372,共5页
Acta Aeronautica et Astronautica Sinica
关键词
声发射
疲劳裂纹
多参数识别
飞机
主梁
acoustic emission (AE)\ fatigue crack\ multi\|parameter identification\ correlation
