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Design and Optimization of Defense Hole System for Hybrid Loaded Laminates

Design and Optimization of Defense Hole System for Hybrid Loaded Laminates

Salih N. Akour, Mohammad Al-Husban, Jamal F. Nayfeh
Copyright: © 2012 |Pages: 10
ISBN13: 9781609608873|ISBN10: 1609608879|EISBN13: 9781609608880
DOI: 10.4018/978-1-60960-887-3.ch007
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MLA

Akour, Salih N., et al. "Design and Optimization of Defense Hole System for Hybrid Loaded Laminates." Technology Engineering and Management in Aviation: Advancements and Discoveries, edited by Evon Abu-Taieh, et al., IGI Global, 2012, pp. 151-160. https://doi.org/10.4018/978-1-60960-887-3.ch007

APA

Akour, S. N., Al-Husban, M., & Nayfeh, J. F. (2012). Design and Optimization of Defense Hole System for Hybrid Loaded Laminates. In E. Abu-Taieh, A. El Sheikh, & M. Jafari (Eds.), Technology Engineering and Management in Aviation: Advancements and Discoveries (pp. 151-160). IGI Global. https://doi.org/10.4018/978-1-60960-887-3.ch007

Chicago

Akour, Salih N., Mohammad Al-Husban, and Jamal F. Nayfeh. "Design and Optimization of Defense Hole System for Hybrid Loaded Laminates." In Technology Engineering and Management in Aviation: Advancements and Discoveries, edited by Evon Abu-Taieh, Asim El Sheikh, and Mostafa Jafari, 151-160. Hershey, PA: IGI Global, 2012. https://doi.org/10.4018/978-1-60960-887-3.ch007

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Abstract

Stress concentration associated with circular holes in hybrid loading (i.e., tension-compression ratios of 0.25, 0.50, and 0.75) achieved maximum reduction of 31.7%. This reduction is obtained by introducing elliptical defense holes along the principal stress direction. Finite element analysis is used to optimize the size and location for defense hole system. The effect of the stacking sequence, the fiber orientation, and the stiffness of both the fiber and the matrix are investigated.

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