تقرير
Reduction of Thermal Residual Stresses in Advanced Metallic Composites Based upon a Compensating/Compliant Layer Concept
| العنوان: | Reduction of Thermal Residual Stresses in Advanced Metallic Composites Based upon a Compensating/Compliant Layer Concept |
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| المؤلفون: | S. M. Arnold, V. K. Arya, M. E. Melis |
| المصدر: | Journal of Composite Materials. 26(9) |
| بيانات النشر: | United States: NASA Center for Aerospace Information (CASI), 1992. |
| سنة النشر: | 1992 |
| مصطلحات موضوعية: | Composite Materials |
| الوصف: | High residual stresses within metal and intermetallic matrix composite systems can develop upon cooling from the processing temperature to room temperature due to the coefficient of thermal expansion (CTE) mismatch between the fiber and matrix. As a result, within certain composite systems, radial, circumferential, and/or longitudinal cracks have been observed to form at the fiber-matrix interface region. The compliant layer concept (insertion of a compensating interface material between the fiber and matrix) has been proposed to reduce or eliminate the residual stress buildup during cooling, and thus minimize cracking. The present study investigates elastic-plastically the viability of the proposed compliant layer concept. A detailed parametric study was conducted utilizing a unit cell model consisting of three concentric cylinders to determine the required character (i.e., thickness and mechanical properties) of the compliant layer as well as its applicability. The unknown compliant layer mechanical properties were expressed as ratios of the corresponding temperature dependent Ti-24Al-11Nb (a/o) matrix properties. The fiber properties taken were those corresponding to SCS-6 (SiC). Results indicated that the compliant layer can be used to reduce, if not eliminate, radial and circumferential residual stresses within the fiber and matrix and therefore also reduce or eliminate the radial cracking. However, with this decrease in in-plane stresses, one obtains an increase in longitudinal stress, thus potentially initiating longitudinal cracking. Guidelines are given for the selection of a specific compensating/ compliant material, given a perfectly bonded system. |
| نوع الوثيقة: | Report |
| اللغة: | English |
| تدمد: | 1530-793X 0021-9983 |
| DOI: | 10.1177/002199839202600904 |
| URL الوصول: | https://ntrs.nasa.gov/citations/19920064482 |
| رقم الأكسشن: | edsnas.19920064482 |
| قاعدة البيانات: | NASA Technical Reports |
| تدمد: | 1530793X 00219983 |
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| DOI: | 10.1177/002199839202600904 |