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On the thermo-structural response of a composite closeout in a regeneratively cooled thrust chamber

Composite materials could be very useful when applied to structural rocket engine components since they can allow significant weight savings thanks to their high specific strength and high specific stiffness. In the present work, a carbon fiber reinforced composite has been adopted to replace the typical heavy metallic closeout structure of a regeneratively cooled thrust chamber of a liquid rocket engine. The composite structure has been considered wrapped over the inner liner of the thrust chamber, made of copper alloys, and provides hoop strength for withstanding the fuel/coolant pressure in the cooling channels.

» Author: M. Ferraiuolo, W. Petrillo, A. Riccio

» Reference: Aerospace Science and Technology, Volume 71

» Publication Date: 01/12/2017

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This project has received funding from the European Union Seventh Framework Programme (FP7/2007-2013) under grant agreement n° [609203].

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