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- W2355457714 abstract "The appearance and growth of the crack in the aircraft structure is an important factor to influence the aircraft's safety and its service life.Thus it is important to detect the crack and monitoring its growth at the beginning.The real-time structural health monitoring method for fatigue crack growth is researched in this paper.The Lamb wave active diagnostic method and the electro-mechanical(E/M) impedance technique are adopted to monitoring the fatigue crack propagation on Aluminum specimens.The relationship between the signal damage index and the crack size are obtained.The two health monitoring methods are discussed and compared." @default.
- W2355457714 created "2016-06-24" @default.
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- W2355457714 date "2008-01-01" @default.
- W2355457714 modified "2023-09-26" @default.
- W2355457714 title "Real-time Structural Health Monitoring for Fatigue Crack Growth" @default.
- W2355457714 hasPublicationYear "2008" @default.
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