Evaluation Of Microcracking In Two Carbon-fiber/epoxy-matrix Composite Cryogenic Tanks
by Nasa Technical Reports Server (ntrs)
2021-01-13 20:34:20
Evaluation Of Microcracking In Two Carbon-fiber/epoxy-matrix Composite Cryogenic Tanks
by Nasa Technical Reports Server (ntrs)
2021-01-13 20:34:20
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...
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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.
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