Research Article
Aug 1965
Thermal-Shock Effects on a Space Vehicle
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VIEW THE REPLYAuthors: Lewis Li-Tang Au, F.ASCE, and Donald J. TrentAuthor Affiliations
Publication: Journal of the Engineering Mechanics Division
Volume 91, Issue 4
Abstract
The problem of thermal shock has implications in the microscopic scale, the macroscopic range, and in terms of the total structure. This paper studies these three areas of thermal-shock response of spacecraft structures. When encountering thermal-shock conditions, the spacecraft structure, comprising panels and shells, will react instantaneously. The response may involve vibration and melting of the structure in general, and drastic changes in material functions locally. The basic microscopic material characteristics that are involved in these processes are identified. Correlations between these characteristics and the more familiar macroscopic aspects of material behavior are included. Two significant phenomena of thermal shocks are investigated analytically: (1) The vaporization and blowing off of surface material that can result from sudden application of thermal energy to the surface of a vehicle; and (2) the vibration and response of vehicle panels and shells to such sudden application of thermal energy.
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Published In
Journal of the Engineering Mechanics Division
Volume 91 • Issue 4 • August 1965
Pages: 1 - 26
Copyright
© 1965 American Society of Civil Engineers.
History
Published in print: Aug 1965
Published online: Feb 3, 2021
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Affiliations
Lewis Li-Tang Au, F.ASCE
Senior Engr., Dynamic Sciences, Space and Information Systems Div., North American Aviation, Inc., Downey, Calif.
Donald J. Trent
Research Specialist, Dynamic Sciences, Space and Information Systems Div., North American Aviation, Inc., Downey, Calif.
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Terms of Use: ASCE Library Cards are for individual, personal use only. Reselling, republishing, or forwarding the materials to libraries or reading rooms is prohibited.
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