NASA/TM-211194, Hodge, A.J., Evaluation of Microcracking in Two Carbon-Fiber/Epoxy-Matrix Composite Cryogenic Tanks , George C. Marshall Space Flight Center Marshall Space Flight Center, Alabama 35812, National Aeronautics and Space Administration Washington, DC 20546-0001, Prepared for Materials Processes and Manufacturing Department, Engineering Directorate, August 2001, pp. 20, Format(s): PDF 1137k |
Two graphite/epoxy cryogenic pressure vessels were evaluated for microcracking. The X-33 LH2 tank lobe skins were extensively examined for microcracks. Specimens were removed from the inner skin of the X-33 tank for tensile testing. The data obtained from these tests were used to model expected microcrack density as a function of stress. Additionally, the laminate used in the Marshall Space Flight Center (MSFC) Composite Conformal, Cryogenic, Common Bulkhead, Aerogel-Insulated Tank (CBAT) was evaluated. Testing was performed in an attempt to predict potential microcracking during testing of the CBAT
| Keywords: | composite, microcrack, cryogenic tank, tensile testing |
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| Subjects: | Chemistry and Materials: Composite Materials: Composite Materials |
| ID Code: | 573 |
| Deposited On: | 01 August 2002 |