Axisymmetric Pressures and Thermal Gradients in Conical Missile Tips

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 thic...

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Bibliographic Details
Published in:Journal of aerospace engineering 1991-07, Vol.4 (3), p.237-255
Main Authors: Jianping, Pei, Harik, Issam E
Format: Article
Language:English
Subjects:
aerodynamics
conical shells
missiles
pressure
supersonic flow
TECHNICAL PAPERS
thermodynamics
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Summary: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.
ISSN:0893-1321
1943-5525
DOI:10.1061/(ASCE)0893-1321(1991)4:3(237)