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This paper summarizes the U.S. Air Force damage tolerance design requirements for metallic airframes. The requirements are a function of the design concept and degree of inspectability of the airframe. Both analytical and experimental requirements are presented. The requirements include the initial damage size, shape, and location, which must be assumed in design. Also presented are the subsequent crack growth and residual strength requirements, which must be satisfied because of the presence of this initial damage.
fatigue (materials), Air Force research, crack propagation, damage tolerance, fracture mechanics, fatigue crack growth, residual strength, design requirements, initial damage, aircraft structure
Aerospace engineer, Air Force Wright Aeronautical Laboratories, Wright-Patterson Air Force Base, OH