Flight simulation fatigue crack growth tests are necessary for verification of aircraft damage tolerance analyses and crack growth prediction methods, and also for comparing candidate materials for aircraft structural applications. However, such tests involve complicating issues that have emerged from many investigations on aluminum alloys since the late 1960s. These issues are reviewed to provide guidelines for further testing.
Flight Simulation Fatigue Crack Growth Testing of Aluminium Alloys: Specific Issues and Guidelines
1993
49 pages
Report
No indication
English
Aircraft , Aeronautics , Nonferrous Metals & Alloys , Materials Degradation & Fouling , Structural Mechanics , Aluminum alloys , Flight simulation , Crack propagation , Fatigue(Materials) , Aerodynamic loads , Aircraft structures , Aircraft construction materials , Fatigue life , Power spectra , Gust loads , Notch tests , Stress intensity factors , Fatigue tests , Crack opening displacement , Foreign technology
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