Methods for monitoring fatigue loads on aircraft structures are presented. As the actual service life deviates appreciably from design load spectrum assumptions, a reassessment of safe service life and inspection schedules are shown to be necessary. Simple counting accelerometer systems; multiparameter recording systems; and direct strain monitoring systems are discussed. Examples of combat aircraft and civil transport aircraft are presented. The interpretation of recorded loads in terms of accumulated fatigue damage is considered.
Fatigue Life Monitoring of Aircraft
1983
10 pages
Report
Keine Angabe
Englisch
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