The form, fit, and function of glass fiber composites is well accepted in the aerospace community. The need for reduced weight in airline service materials is addressed through evaluation of S-2 Glass hollow fiber 250 F cure epoxy systems within existing composite components. A 15-20 % weight reduction with minimal loss of performance and function is demonstrated in initial baseline testing. Static, fatigue, impact, and flight cycling properties are included in the assessment of woven materials. Unidirectional lamina data is also presented for comparison with solid fiber materials. Compressive, shear, and flexural strengths are comparable. Tensile strength and all moduli appear to follow rules-of-mixture behavior with the removal of bulk glass. The apparent density of the S-2 Glass hollow fiber is 1.8 g/cc or about 0.3 hollow void fraction.
S-2 Glass hollow fiber epoxy composites in commercial aircraft
Verbundwerkstoffe aus S-2 Hohlglasfasern/Epoxid in kommerziellen Flugzeugen
1992
15 Seiten, 7 Bilder, 4 Tabellen, 3 Quellen
Conference paper
English
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