This paper describes a method which has been developed for estimating the safe fatigue life of compact, highly-stressed and inaccessible components for aeroplanes and helicopters of the Royal Air Force. It is explained why the Design Requirements for British Military Aircraft do not favor the use of a damage-tolerance approach in these circumstances.
Method of Calculating the Safe Fatigue Life of Compact, Highly-Stressed Components
1994
12 pages
Report
No indication
English
Aircraft , Quality Control & Reliability , Structural Mechanics , Aircraft reliability , Aircraft structures , Damage assessment , Fatigue life , Helicopters , Inspection , Stress analysis , Structural analysis , Aircraft performance , Corrosion , Service life , Tolerances (Mechanics) , Foreign technology
A Method of Calculating the Safe Fatigue Life of Compact, Highly-Stressed Components
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