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Development of Compressive Failure Strength for Composite Laminate Using Regression Analysis Method

회귀분석법에 의한 복합재료 적층판의 압축파손강도 개발

  • Received : 2016.05.13
  • Accepted : 2016.08.08
  • Published : 2016.10.01

Abstract

This paper provides the compressive failure strength value of composite laminate developed by using regression analysis method. Composite material in this document is a Carbon/Epoxy unidirection(UD) tape prepreg(Cycom G40-800/5276-1) cured at $350^{\circ}F(177^{\circ}C$). The operating temperature is -$-60^{\circ}F{\sim}+200^{\circ}F$($-55^{\circ}C{\sim}+95^{\circ}C$). A total of 56 compression tests were conducted on specimens from eight (8) distinct laminates that were laid up by standard angle layers ($0^{\circ}$, $+45^{\circ}$, $-45^{\circ}$ and $90^{\circ}$). The ASTM-D-6484 standard was used for test method. The regression analysis was performed with the response variable being the laminate ultimate fracture strength and the regressor variables being two ply orientations ($0^{\circ}$ and ${\pm}45^{\circ}$).

Keywords

Composite;Laminate;Compressive Failure Strength;Regression Analysis Method

References

  1. MIL-HDBK-17, 2002, "Composite Materials Handbook," Volume 1, Revision F.
  2. ASTM D 6484/D 6484M-04, 2004, "Standard Test Method for Open Hole Compressive Strength of Polymer Matrix Composite Materials".
  3. Jones, R. M., 1975, "Mechanics of Composite Materials," McGraw-Hill, New York.

Acknowledgement

Grant : 체계개발

Supported by : 국방과학연구소