TECHNICAL PAPERS
Jul 1, 1991

Axisymmetric Pressures and Thermal Gradients in Conical Missile Tips

Publication: Journal of Aerospace Engineering
Volume 4, Issue 3

Abstract

An iterative finite difference technique is presented for the analysis of axisymmetric conical shells with variable thickness. Temperature, surface pressure, and friction loadings due to supersonic flow are considered. The temperature loading is assumed to vary along the meridian and across the thickness of the shell. The variation of the material properties with temperature is taken into account. The applicability of classical thin shell theory is assumed in the analysis. The governing partial differential equation is presented in terms of the meridional and normal displacements. The proposed method of solution is applicable to short and long conical shells. Complete and truncated conical shells are treated, and results are presented and compared with those of existing solutions.

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Published In

Go to Journal of Aerospace Engineering
Journal of Aerospace Engineering
Volume 4Issue 3July 1991
Pages: 237 - 255

History

Published online: Jul 1, 1991
Published in print: Jul 1991

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Authors

Affiliations

Pei Jianping
Sr. Design Engr., Ningxia Arch. Design Inst., Yinchuan, People's Republic of China. Visiting Scholar at the Dept. of Civ. Engrg., Univ. of Kentucky, Lexington, KY 40506‐0046
Issam E. Harik, Member, ASCE
Assoc. Prof., Dept. of Civ. Engrg., Univ. of Kentucky, Lexington, KY 40506‐0046

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