Consequences of application of damage tolerance airworthiness requirements for transport aircraft in designing stiffened-skin structures to be safe under all operational load conditions are discussed. Computer programs to provide analytical tools to demonstrate that design meets the required residual strength and crack propagation properties were developed. The principles underlying the calculation procedures used to predict the residual strength of stiffened panels with a skin of ductile material (like 2024) are included. Applications of the programs to practical stiffened skin structures are presented together with analysis test correlations.
Damage Tolerance of Stiffened-Skin Structures: Prediction and Experimental Verification
1986
87 pages
Report
No indication
English
Aircraft , Aircraft design , Aircraft maintenance , Aircraft reliability , Aircraft structures , Skin (Structural member) , Crack arrest , Crack closure , Crack tips , Damage assessment , Fail-safe systems , Fatigue (Materials) , Inspection , Residual strength , Stiffening , Stress intensity factors , Foreign technology
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