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Hybrid Composites for LH2 Fuel Tank StructureThe application of lightweight carbon fiber reinforced plastics (CFRP) as structure for cryogenic fuel tanks is critical to the success of the next generation of Reusable Launch Vehicles (RLV). The recent failure of the X-33 composite fuel tank occurred in part due to microcracking of the polymer matrix, which allowed cryogen to permeate through the inner skin to the honeycomb core. As part of an approach to solve these problems, NASA Langley Research Center (LaRC) and Marshall Space Flight Center (MSFC) are working to develop and investigate polymer films that will act as a barrier to the permeation of LH2 through the composite laminate. In this study two commercially available films and eleven novel LaRC films were tested in an existing cryogenics laboratory at MSFC to determine the permeance of argon at room temperature. Several of these films were introduced as a layer in the composite to form an interleaved, or hybrid, composite to determine the effects on permeability. In addition, the effects of the interleaved layer thickness, number, and location on the mechanical properties of the composite laminate were investigated. In this initial screening process, several of the films were found to exhibit lower permeability to argon than the composite panels tested.
Document ID
20040086019
Acquisition Source
Langley Research Center
Document Type
Other
Authors
Grimsley, Brian W. (NASA Langley Research Center Hampton, VA, United States)
Cano, Roberto J. (NASA Langley Research Center Hampton, VA, United States)
Johnston, Norman J. (NASA Langley Research Center Hampton, VA, United States)
Loos, Alfred C. (Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
McMahon, William M. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2001
Subject Category
Composite Materials
Distribution Limits
Public
Copyright
Public Use Permitted.

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