Abstract
This study details the damage evolution of the pinned joints for both [0/±45/90]3S and [90/±45/0]3S CFRP laminates and its difference between static and fatigue loading is discussed. Though there is no clear difference in the macroscopic external appearance of damage between fatigue and static loading failure, the microscopic internal damage shows differences in critical damage and damage evolution. In static tests all the inside 0° layers have kink at the maximum load and the kink is a trigger to the final failure with delamination and matrix crack. On the other hand, under fatigue loading the final damages start mostly from collapse or kink-like collapse at the loaded surface edge. It is also found that the total delamination length is longer in the case of fatigue at the same total matrix crack length and that [90/±45/0]3S presents higher strength than [0/±45/90]3S in both static and fatigue cases due to the band effect of 90° surface layers.
| Original language | English |
|---|---|
| Title of host publication | Collection of Technical Papers - 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference |
| Pages | 8482-8491 |
| Number of pages | 10 |
| Publication status | Published - Aug 6 2007 |
| Event | 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference - Waikiki, HI, United States Duration: Apr 23 2007 → Apr 26 2007 |
Publication series
| Name | Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference |
|---|---|
| Volume | 8 |
| ISSN (Print) | 0273-4508 |
Other
| Other | 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference |
|---|---|
| Country | United States |
| City | Waikiki, HI |
| Period | 4/23/07 → 4/26/07 |
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All Science Journal Classification (ASJC) codes
- Architecture
- Materials Science(all)
- Aerospace Engineering
- Mechanics of Materials
- Mechanical Engineering
Cite this
Fatigue and static damage of a pinned joint in CFRP. / Seike, Satoshi; Takao, Yoshihiro; Wang, Wenxue; Matsubara, Terutake.
Collection of Technical Papers - 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. 2007. p. 8482-8491 (Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference; Vol. 8).Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Fatigue and static damage of a pinned joint in CFRP
AU - Seike, Satoshi
AU - Takao, Yoshihiro
AU - Wang, Wenxue
AU - Matsubara, Terutake
PY - 2007/8/6
Y1 - 2007/8/6
N2 - This study details the damage evolution of the pinned joints for both [0/±45/90]3S and [90/±45/0]3S CFRP laminates and its difference between static and fatigue loading is discussed. Though there is no clear difference in the macroscopic external appearance of damage between fatigue and static loading failure, the microscopic internal damage shows differences in critical damage and damage evolution. In static tests all the inside 0° layers have kink at the maximum load and the kink is a trigger to the final failure with delamination and matrix crack. On the other hand, under fatigue loading the final damages start mostly from collapse or kink-like collapse at the loaded surface edge. It is also found that the total delamination length is longer in the case of fatigue at the same total matrix crack length and that [90/±45/0]3S presents higher strength than [0/±45/90]3S in both static and fatigue cases due to the band effect of 90° surface layers.
AB - This study details the damage evolution of the pinned joints for both [0/±45/90]3S and [90/±45/0]3S CFRP laminates and its difference between static and fatigue loading is discussed. Though there is no clear difference in the macroscopic external appearance of damage between fatigue and static loading failure, the microscopic internal damage shows differences in critical damage and damage evolution. In static tests all the inside 0° layers have kink at the maximum load and the kink is a trigger to the final failure with delamination and matrix crack. On the other hand, under fatigue loading the final damages start mostly from collapse or kink-like collapse at the loaded surface edge. It is also found that the total delamination length is longer in the case of fatigue at the same total matrix crack length and that [90/±45/0]3S presents higher strength than [0/±45/90]3S in both static and fatigue cases due to the band effect of 90° surface layers.
UR - http://www.scopus.com/inward/record.url?scp=34547504861&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=34547504861&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:34547504861
SN - 1563478927
SN - 9781563478925
T3 - Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
SP - 8482
EP - 8491
BT - Collection of Technical Papers - 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
ER -