Thermo-mechanical evaluation of carbon-carbon primary structure for SSTO vehicles

Details Thermo-mechanical evaluation of carbon-carbon primary structure for SSTO vehicles Thermo-mechanical evaluation of carbon-carbon primary structure for SSTO vehicles

Jan 1998

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1998aipc..420.1020c&link_type=abstract

Space technology and applications international forum - 1998. AIP Conference Proceedings, Volume 420, pp. 1020-1026 (1998).

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Spaceborne And Space Research Instruments, Apparatus, And Components

Scientific paper

An advanced development program to demonstrate carbon-carbon composite structure for use as primary load carrying structure has entered the experimental validation phase. The component being evaluated is a wing torque box section for a single-stage-to-orbit (SSTO) vehicle. The validation or demonstration component features an advanced carbon-carbon design incorporating 3D woven graphite preforms, integral spars, oxidation inhibited matrix, chemical vapor deposited (CVD) oxidation protection coating, and ceramic matrix composite fasteners. The validation component represents the culmination of a four phase design and fabrication development effort. Extensive developmental testing was performed to verify material properties and integrity of basic design features before committing to fabrication of the full scale box. The wing box component is now being set up for testing in the Air Force Research Laboratory Structural Test Facility at Wright-Patterson Air Force Base, Ohio. One of the important developmental tests performed in support of the design and planned testing of the full scale box was the fabrication and test of a skin/spar trial subcomponent. The trial subcomponent incorporated critical features of the full scale wing box design. This paper discusses the results of the trial subcomponent test which served as a pathfinder for the upcoming full scale box test.

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