Evaluation of Fatigue Properties in Future Aircraft Material, Aluminum-Lithium Alloy
| Project/Area Number |
01550057
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| Research Category |
Grant-in-Aid for General Scientific Research (C)
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| Allocation Type | Single-year Grants |
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| Research Field |
機械材料工学
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| Research Institution | Gifu University |
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Principal Investigator |
OGAWA Takeshi (1991) Gifu University, Dept. Mechanical Eng., Associate Professor, 工学部, 助教授 (50167318)
戸梶 惠郎 (戸梶 恵郎) (1989-1990) 岐阜大学, 工学部, 教授 (80021616)
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| Co-Investigator(Kenkyū-buntansha) |
TOKAJI Keiro Gifu University, Dept. Mechanical Eng., Professor, 工学部, 教授 (80021616)
小川 武史 岐阜大学, 工学部, 助教授 (50167318)
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| Project Period (FY) |
1989 – 1991
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| Project Status |
Completed (Fiscal Year 1991)
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| Budget Amount *help |
¥2,000,000 (Direct Cost: ¥2,000,000)
Fiscal Year 1991: ¥700,000 (Direct Cost: ¥700,000)
Fiscal Year 1990: ¥500,000 (Direct Cost: ¥500,000)
Fiscal Year 1989: ¥800,000 (Direct Cost: ¥800,000)
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| Keywords | Aircraft Material / Aluminum-Lithium alloy / Fatigue Strength / Rotating Bending / Aging Condition / Corrosion Fatigue / Notch Effect / 停留き裂 / き裂進展限界 / き裂発生限界 / 腐食ピット / き裂発生 / き裂成長 / Al-li合金 / 疲労き裂発生 / 微小疲労き裂成長 / 破壊機構 |
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| Research Abstract |
Wide range of fatigue properties under rotating bending were investigated in two kinds of aluminum Lithium (Al-Li) alloys, 2090 and 8090, which are predicted to be used for the future aircraft. The results were compared with the conventional aluminum alloys, 2024 and 7075. The results obtained are summarized as follows ;
1. Tensile strength of the AI-LI alloys were approximately the same as those of 2024 alloy, but were lower than those of 7075 alloy. On the other hand, the elongation and reduction of area were extremely small compared to conventional aluminum alloys. The fatigue strength of Al-Li-alloys was superior to that of conventional Al, alloys in the region of long fatiaue life (more than 10^5 cycles). It is suggested that the excellent fatigue strength of AI-LI alloys is mainly due to their high resistance to crack initiation.
2. The fatigue strength was decreased by the underaging and overaging process. This was due to the decrease in both crack initiation and growth resistances. The crack initiation and growth were controlled by the precipitation of delta '-Phase during aging.
3. Fatigue strength in 3%NaCl solution is much lower than that in air for both Al-Li alloys and conventional AI alloys. The corrosion fatigue strength of AI-LI alloys is not influenced by aging condition, and it is better than that of AI alloys.
4. The notch sensitivity of AI-LI alloys is less than that of conventional AI alloys, especially in 8090 alloy. Non-propagating crack was observed only in 8090 alloy with the highest stress concentrator, whose stress concentration factor is 8.18.
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Report
(4 results)
Research Products
(14 results)
