A crack opening stress equation for fatigue crack growth

International Journal of Fracture Mechanics - Tập 24 - Trang R131-R135 - 1984
J. C. Newman1
1NASA Langley Research Center, Hampton, USA

Tài liệu tham khảo

W. Elber, in Damage Tolerance in Aircraft Structures, STP 486, American Society for Testing and Materials, Philadelphia (1971) 230–242. J.C. Newman, Jr., Finite-Element Analysis of Fatigue Crack Propagation-Including the Effects of Crack closure. Ph.D. Thesis, Virginia Polytechnic Institute and State University, Blacksburg, VA, May 1974. J.C. Newman, Jr., “A Crack-Closure Model for Predicting Fatigue-Crack Growth under Aircraft Spectrum Loading”, NASA TM-81941, January 1981. D.S. Dugdale, Journal of the Mechanics and Physics of Solids 8 (1960) 100–104. J.C. NewmanJr., in Design of Fatigue and Fracture Resistant Structures, STP 761, American Society for Testing and Materials, Philadelphia (1982) 255–277. C.M. Hudson, “Effect of Stress Ratio on Fatigue-Crack Growth in 7075-T6 and 2024-T3 Aluminum Alloy Specimens”, NASA TN D-5390, 1969.