Fatigue Crack Propagation of Some Aircraft Sheet Materials (the Transactions of the Japan Society of Mechanical Engineers) : Papers published in the Bulletin of the JSME are not included here

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概要

• 論文の詳細を見る

• This report presents the test results of fatigue crack propagation and related discussions on typical aircraft materials under constant amplitude load at room temperature. Materials tested are : 2024-T4,7075-T6,6A1-4V-Ti, 17-7 PH stainless steel and 18- 8 stainless steel. The equation of crack propagation rate proposed by Forman et al, is improved so that the effect of applied stress ratio is more flexibly taken into account as follows : [numerical formula] where k_<fc> is fracture toughness under fatigue load and in general, it may be different from the static fracture toughness value. Above equation is applicable to all materials tested. In case when compressive loads are included, their effect is negligible in the above equation. It is also shown that the equation gives good correlation with other data available.

• 一般社団法人日本機械学会の論文

著者

• Terada Hiroyuki

  National Aerospace Laboratory

• ISHIDA Makoto

  Faculty of Mechanical Engineering, Kyushu University

• KAKUTA Yoshiaki

  National Aerospace Laboratory

• Ishida Makoto

  Faculty Of Mechanical Engineering Kyushu University

関連論文

• Fatigue Crack Propagation of Some Aircraft Sheet Materials (the Transactions of the Japan Society of Mechanical Engineers) : Papers published in the Bulletin of the JSME are not included here
• Fatigue Crack Growth Properties of a GLARE3-5/4 Fiber/Metal Laminate

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