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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