| タイトル | Process Optimization of Bismaleimide (BMI) Resin Infused Carbon Fiber Composite |
| 本文（外部サイト） | http://hdl.handle.net/2060/20130011578 |
| 著者（英） | Cox, Sarah B.; Tate, LaNetra C.; Caraccio, Anne J.; Wright, M. Clara; Sampson, Jeffery W.; Taylor, Brian J.; Ehrlich, Joshua W. |
| 著者所属（英） | NASA Kennedy Space Center |
| 発行日 | 2013-01-01 |
| 言語 | eng |
| 内容記述 | Bismaleimide (BMI) resins are an attractive new addition to world-wide composite applications. This type of thermosetting polyimide provides several unique characteristics such as excellent physical property retention at elevated temperatures and in wet environments, constant electrical properties over a vast array of temperature settings, and nonflammability properties as well. This makes BMI a popular choice in advance composites and electronics applications [I]. Bismaleimide-2 (BMI-2) resin was used to infuse intermediate modulus 7 (IM7) based carbon fiber. Two panel configurations consisting of 4 plies with [+45deg, 90deg]2 and [0deg]4 orientations were fabricated. For tensile testing, a [90deg]4 configuration was tested by rotating the [0deg]4 configirration to lie orthogonal with the load direction of the test fixture. Curing of the BMI-2/IM7 system utilized an optimal infusion process which focused on the integration of the manufacturer-recommended ramp rates,. hold times, and cure temperatures. Completion of the cure cycle for the BMI-2/IM7 composite yielded a product with multiple surface voids determined through visual and metallographic observation. Although the curing cycle was the same for the three panellayups, the surface voids that remained within the material post-cure were different in abundance, shape, and size. For tensile testing, the [0deg]4 layup had a 19.9% and 21.7% greater average tensile strain performance compared to the [90deg]4 and [+45deg, 90deg, 90deg,-45degg] layups, respectively, at failure. For tensile stress performance, the [0deg]4 layup had a 5.8% and 34.0% greater average performance% than the [90deg]4 and [+45deg, 90deg, 90deg,-45deg] layups. |
| NASA分類 | Composite Materials |
| レポートNO | KSC-2013-013R
KSC-2013-013 |
| 権利 | No Copyright |
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