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Ultrasonic and mechanical characterizations of fatigue states of graphite epoxy composite laminates
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Lee, S. S. Yuce, H. Williams Jr., J. H. |
| Copyright Year | 1982 |
| Description | Eight-ply (0, + or - 45, 0)s laminates of Hercules AS/3501-6 graphite epoxy composite are fabricated using various cure pressures ranging from 0.52 to 0.86 MPa and cure temperatures ranging from 150 C to 200 C. In general, the minimum composite void volume fraction is obtained at a cure temperature of 175 C and a cure pressure of 0.86 MPa, or at 200 C and 0.86 MPa. The ultrasonic attenuation at 4 MHz was found to correlate with the composite void volume fraction. Composite specimens were tested in flexural fatigue. Beyond 10,000 fatigue cycles, the ultrasonic attenuation at 4 MHz was found to increase and the flexural stiffness was found to decrease. The ultrasonic attenuation at 4 MHz of the as-fabricated composite can be correlated with the number of fatigue cycles to failure. |
| File Size | 1277132 |
| Page Count | 26 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19820009640 |
| Archival Resource Key | ark:/13960/t8wb00q98 |
| Language | English |
| Publisher Date | 1982-01-01 |
| Access Restriction | Open |
| Subject Keyword | Fatigue Tests Temperature Measurement Concentration Composition Structural Failure Fatigue Materials Mechanical Properties Graphite-epoxy Composites Stiffness Pressure Measurement Laminates Flexing Ultrasonics Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
