Published: Jan 1960
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One of the most challenging aspects of aircraft structural design is the prevention of fatigue failure. For this reason ASTM Committee E-9 on Fatigue established a subcommittee to deal especially with fatigue problems facing aircraft designers and operators. This subcommittee sponsored the present symposium to discuss recent advances and the current state of development of solutions to various phases of the aircraft fatigue problem. The symposium was held during the Third Pacific Area National Meeting of the Society to continue a precedent set three years previously when a similar symposium was held during the Second Pacific Area Meeting. The papers presented cover a broad range of individual topics from general design philosophies to rather basic considerations. Twelve papers were presented in three sessions. Nine of these papers are included in this Special Technical Publication; two will be published along with other papers at a later date and the third paper by E. H. Schuette, Dow Chemical Co., on “Fatigue-Strength Comparisons of Forged Magnesium Alloys,” has been withdrawn. The first two papers present, respectively, a method for handling fatigue data in a practical design case, and a review of probable loading conditions encountered by aircraft. An interesting description of a method for conducting sonic fatigue tests and a rather basic treatment of fatigue behavior under high biaxial stresses are the subjects of the remaining papers in the first session. In the second session, one paper deals with problems peculiar to helicopters, one with methods for improving fatigue behavior in structures, and one with methods for predicting rates of fatigue crack propagation. The two published papers from the third session discuss cumulative damage due to variable-amplitude loading.
Hardrath, Herbert F.
Symposium ChairmanHeadChairman of Subcommittee V on Fatigue of Aircraft Structures of ASTM Committee E-9 on Fatigue, National Aeronautics and Space Administration, Langley Field, Va.