Abstract
Thermal control of spacecraft tubular composites is discussed. The equations used to calculate orbital temperatures are presented with a description of the design techniques which limit temperature excursions and associated distortions. Laminate fiber orientation is related to heat transfer characteristics, and it is shown that orientations selected to yield high axial strength and least thermal deformations will generally lead to excessive fin effect heat losses. A perforation procedure is proposed to eliminate in plane deflections in a space environment independently of laminate construction. The lamination sequence may then he optimized to meet strength and heat loss requirements.
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© 1983 Applied Science Publishers Ltd
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Karam, R.D. (1983). Thermal Control of Tubular Composite Structures in Space Environment. In: Marshall, I.H. (eds) Composite Structures 2. Springer, Dordrecht. https://doi.org/10.1007/978-94-009-6640-6_17
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DOI: https://doi.org/10.1007/978-94-009-6640-6_17
Publisher Name: Springer, Dordrecht
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