An improved higher order model for analysis of composite laminated cylindrical shell under thermal and electromechanical loads /
Modern aerospace structures are smart composite structures which are made from combination of composite and piezoelectric materials. These composite structures during their service life are exposed to severe environmental conditions such as high temperature and moisture effect that are detrimental t...
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| Main Author: | |
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| Format: | Thesis |
| Language: | English |
| Published: |
Kuala Lumpur :
Kulliyyah of Engineering, International Islamic University Malaysia,
2019
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| Subjects: | |
| Online Access: | http://studentrepo.iium.edu.my/handle/123456789/5159 |
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| LEADER | 034940000a22003010004500 | ||
|---|---|---|---|
| 008 | 191031s2019 my a f m 000 0 eng d | ||
| 040 | |a UIAM |b eng |e rda | ||
| 041 | |a eng | ||
| 043 | |a a-my--- | ||
| 050 | 0 | 0 | |a TA418.9.L3 |
| 100 | 0 | |a Muhammad Rahman Adedi, |e author | |
| 245 | 1 | 3 | |a An improved higher order model for analysis of composite laminated cylindrical shell under thermal and electromechanical loads / |c by Muhammad Rahman Adedi |
| 264 | 1 | |a Kuala Lumpur : |b Kulliyyah of Engineering, International Islamic University Malaysia, |c 2019 | |
| 300 | |a xv, 95 leaves : |b illustrations ; |c 30cm. | ||
| 336 | |2 rdacontent |a text | ||
| 347 | |2 rdaft |a text file |b PDF | ||
| 502 | |a Thesis (MSME)--International Islamic University Malaysia, 2019. | ||
| 504 | |a Includes bibliographical references (leaves 77-80). | ||
| 520 | |a Modern aerospace structures are smart composite structures which are made from combination of composite and piezoelectric materials. These composite structures during their service life are exposed to severe environmental conditions such as high temperature and moisture effect that are detrimental to the strength and stiffness of the composite structures. Moreover, with the combination of piezoelectric material in the smart composite structures, the effect of electric load lead to additional stresses. Based on the realistic variation of displacements from the elasticity approach a new 13 terms higher order shear deformation theory HSDT13 is proposed to accurately investigate the effect of thermal and electromechanical loads on the bending behavior of such smart composite laminate cylindrical shells. The HSDT13 model incorporates Murakami zigzag function in in-plane displacements and higher order terms in transverse displacement. To evaluate the accuracy of the theory, angle-ply and cross-ply cylindrical shells subjected to thermal and electromechanical load for the case of generalized plane strain deformations in the axial direction is considered. Equilibrium equations are derived through principle of virtual displacements and Navier type analytical solutions are obtained. Numerical results are presented for various layups in graphical and tabular form and validated against established elasticity solutions. Based on the results it can be concluded that HSDT13 model performs better with high accuracy even for thick shells compared to other commonly used shell theories such as Classical shell theory by Kirchoff, first order theory and higher order theory by J N Reddy. Moreover, results for transverse shear stresses are evaluated from constitutive equations and elasticity equations are also presented. Finally, parametric study on the effect of material properties and applied voltage on the accuracy of the theory for bending behavior of the laminate are conducted. | ||
| 596 | |a 1 | ||
| 655 | 7 | |a Theses, IIUM local | |
| 690 | |a Dissertations, Academic |x Department of Mechanical Engineering |z IIUM | ||
| 710 | 2 | |a International Islamic University Malaysia. |b Department of Mechanical Engineering | |
| 856 | 4 | |u http://studentrepo.iium.edu.my/handle/123456789/5159 | |
| 900 | |a sz-aaz | ||
| 999 | |c 440165 |d 471393 | ||
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| 952 | |0 0 |6 TS CDF TA 418.9 L3 M9522I 2019 |7 0 |8 THESES |9 858770 |a IIUM |b IIUM |c MULTIMEDIA |g 0.00 |o ts cdf TA 418.9 L3 M9522I 2019 |p 11100408172 |r 2020-08-06 |t 1 |v 0.00 |y THESISDIG | ||