Study on Fatigue of Carbon-Epoxy Composites
| Project/Area Number |
58420021
|
|---|
| Research Category |
Grant-in-Aid for General Scientific Research (A)
|
| Allocation Type | Single-year Grants |
|---|
| Research Field |
航空学
|
|---|
| Research Institution | The University of Tokyo |
|---|
Principal Investigator |
|
|---|
| Project Period (FY) |
1983 – 1985
|
| Project Status |
Completed (Fiscal Year 1985)
|
| Budget Amount *help |
¥31,700,000 (Direct Cost: ¥31,700,000)
Fiscal Year 1985: ¥6,000,000 (Direct Cost: ¥6,000,000)
Fiscal Year 1984: ¥6,000,000 (Direct Cost: ¥6,000,000)
Fiscal Year 1983: ¥19,700,000 (Direct Cost: ¥19,700,000)
|
|---|
| Keywords | Carbon-epoxy laminate / fatigue / delamination / 引張疲労 / 圧縮疲労 / 座屈疲労 / 層間応力 / 層間剥離 / エネルギ解放率 |
|---|
| Research Abstract |
Mechanism of fatigue of carbon-epoxy laminates was investigated. Tension-tension fatigue test on plain coupons of various laminates was conducted together with compressioncompression fatigue test. Both tests showed that the basic fatigue damage process is the growth of delamination initiated at the free edges of the specimens. The locations of delaminations predicted by the strain energy release rate at each interface of layers based on the finite element calculations were in good agreement with the experimental results. Thus the applicability of the fracture mechanics to the delamination of composites was verified.
Tensile strength was tested on coupons at high temperature and high relative humidity. It was shown that the environmental effects of temperature and moisture play important role on the mechanical properties of carbon-epoxy composites.
And square laminated panels were fatigue cycled under shear loading in post-buckling range. The fact that little reduction of strength due to fatigue was detected reveals the post-buckling repeated loading capacity of composite laminates.
|
Report
(1 results)
Research Products
(2 results)
