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Prediction of stress-strain response of scs-6/timetal-21s subjected to a hypersonic flight profile
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Mirdamadi, Massoud Johnson, W. Steven |
| Copyright Year | 1994 |
| Description | Thermomechanical response of a cross-ply SCS-6/Timetal-21S composite subjected to a generic hypersonic flight profile with the temperature ranging from -130 C to 816 C was evaluated experimentally and analytically. A two dimensional micromechanical anlaysis, VISCOPLY, was used to predict the stress-strain response of the laminate and of the constituents in each ply during thermomechanical loading conditions. In the analysis, the fiber was modeled as elastic with transverse orthotropic and temperature dependent properties and the matrix was modeled using a thermoviscoplastic constitutive relation. The fiber transverse modulus was reduced in the analysis to simulate fiber-matrix interface failure. Reasonable agreement was found between measured and predicted laminate stress-strain response when fiber-matrix debonding was modeled. |
| File Size | 1033443 |
| Page Count | 34 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19940024320 |
| Archival Resource Key | ark:/13960/t77t2mq18 |
| Language | English |
| Publisher Date | 1994-02-01 |
| Access Restriction | Open |
| Subject Keyword | Composite Materials Temperature Dependence Hypersonic Flight Silicon Carbides Fiber Composites Laminates Load Tests Micromechanics Titanium Alloys Stress-strain Relationships Debonding Materials Reinforcing Fibers Viscoplasticity Fiber-matrix Interfaces Metal Matrix Composites Failure Thermal Stresses Residual Stress Matrix Materials 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 |
