Abstract
This paper focuses on the benefits of using nanocomposites in structural level components that are typically used in aerospace applications. Initially a multiscale approach is used to determine the mechanical properties of such nanocomposites. A three-stage approach is considered. First, effective carbon nanotube (CNT) properties are obtained based on the composite cylinder method. Second, the effective properties of the effective CNT embedded in an epoxy matrix forming a nanocomposite are obtained using the Mori-Tanaka method. Finally, the effective properties of a composite lamina are obtained assuming that the matrix material properties of the lamina are those calculated for the nanocomposite in Step 2. Then these effective properties are used to analyze the structural response of a T and hat stringer using detailed finite element models. The stringer is analyzed under pull-off loading. Initial damage is detected via the virtual crack closure technique implemented in the finite element analysis. It is shown that the use of nanocomposites in the manufacturing process of such composite stringers will improve the overall performance against unique composite failure modes. Different configurations are analyzed to provide insight on their structural performance.
| Original language | English (US) |
|---|---|
| Pages | 1348-1357 |
| Number of pages | 10 |
| State | Published - 2013 |
| Event | 19th International Conference on Composite Materials, ICCM 2013 - Montreal, Canada Duration: Jul 28 2013 → Aug 2 2013 |
Other
| Other | 19th International Conference on Composite Materials, ICCM 2013 |
|---|---|
| Country/Territory | Canada |
| City | Montreal |
| Period | 7/28/13 → 8/2/13 |
Keywords
- Crack initiation
- Multiscale analysis
- Nanocomposites
ASJC Scopus subject areas
- General Engineering
- Ceramics and Composites