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Information Journal Paper

Title

THERMAL BUCKLING ANALYSIS OF MODERATELY THICK COMPOSITE CYLINDRICAL SHELLS UNDER AXISYMMETRIC THERMAL LOADING

Pages

  99-107

Abstract

 In this paper, a semi-analytical [mite element method is presented to study the thermal buckling behavior of moderate-thick cylindrical shells. The theory is formulated based on first shear deformation assumptions. Simplified Sanders theory and non simplified theory are employed for calculation of geometrical stiffness matrix. The results obtained from these two theories are compared which shows that the critical thermal buckling temperature based on non-simplified theory is higher than that of the simplified Sanders theory. The material is high strength carbon and the boundary condition is clamped-clamped. The influence of fiber angle orientations is also studied.

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    APA: Copy

    DARVIZEH, M., DARVIZEH, A., SHATER ZADEH, A.R., & ANSARI, R.. (2007). THERMAL BUCKLING ANALYSIS OF MODERATELY THICK COMPOSITE CYLINDRICAL SHELLS UNDER AXISYMMETRIC THERMAL LOADING. AEROSPACE MECHANICS JOURNAL, 3(2), 99-107. SID. https://sid.ir/paper/101980/en

    Vancouver: Copy

    DARVIZEH M., DARVIZEH A., SHATER ZADEH A.R., ANSARI R.. THERMAL BUCKLING ANALYSIS OF MODERATELY THICK COMPOSITE CYLINDRICAL SHELLS UNDER AXISYMMETRIC THERMAL LOADING. AEROSPACE MECHANICS JOURNAL[Internet]. 2007;3(2):99-107. Available from: https://sid.ir/paper/101980/en

    IEEE: Copy

    M. DARVIZEH, A. DARVIZEH, A.R. SHATER ZADEH, and R. ANSARI, “THERMAL BUCKLING ANALYSIS OF MODERATELY THICK COMPOSITE CYLINDRICAL SHELLS UNDER AXISYMMETRIC THERMAL LOADING,” AEROSPACE MECHANICS JOURNAL, vol. 3, no. 2, pp. 99–107, 2007, [Online]. Available: https://sid.ir/paper/101980/en

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