Core crush problem in manufacturing of composite sandwich structures: Mechanisms and solutions

AIAA Journal

Volumn 44, Issue 4, 2006, Pages 901-907

  Hsiao, H M ^a,b,c   Lee, S M ^a,d   Buyny, R A ^a,b  

^a HEXCEL CORPORATION   (United States)

^b Research and Technology   (United States)

^c BOSTON SCIENTIFIC CORPORATION   (United States)

^d LOCKHEED MARTIN   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

COMPOSITE HONEYCOMB SANDWICH STRUCTURES; CORE CRUSH; PREPREG FRACTIONAL RESISTANCE; ROUNDER FIBER TOW;

AIRCRAFT ENGINE MANUFACTURE; AUTOCLAVES; CURING; HONEYCOMB STRUCTURES; MANUFACTURING DATA PROCESSING; RESINS;

COMPOSITE STRUCTURES;

EID: 33646385106     PISSN: 00011452     EISSN: None     Source Type: Journal    
DOI: 10.2514/1.18067     Document Type: Article

References (10)

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2. Martin, C. J., Seferis, J. C., and Wilhelm, M. A., "Factional Resistance of Thermoset Prepregs and Its Influences on Honeycomb Composite Processing," Composites Part A, Vol. 27A, No. 10, 1996, pp. 943-951.
3. Buehler, F. U., Seferis, J. C., and Zeng, S., "Consistency Evaluation of a Qualified Glass Fiber Prepreg System," Journal of Advanced Materials, Vol. 33, No. 2, 2001, pp. 41-50.
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7. Martin, C. J., and Seferis, J. C., "Effect of Prepreg Resin Composition on Honeycomb Core Crush," Proceedings of the 43rd International SAMPE Symposium and Exhibition, Society for the Advancement of Material and Process Engineering, Covina, CA, 1998, pp. 366-375.
8. Hsiao, H. M., Lee, S. M., Buyny, R. A., and Martin, C. J., "Core-Crush Resistant Fabric and Prepreg for Fiber Reinforced Composite Sandwich Structures," U.S. Patent 6,261,675, U.S. Patent and Trademark Office, Washington, DC, 17 July 2001.
9. Hsiao, H. M., Lee, S. M., Buyny, R. A., and Martin, C. J., "Development of Core Crush Resistant Prepreg for Composite Sandwich Structures," Proceedings of the 33rd International SAMPE Technical Conference, Society for the Advancement of Material and Process Engineering, Covina, CA, 2001, pp. 440-451.
10. "Boeing Material Specification: Epoxy Preimpregnated Carbon Fiber Tapes and Woven Fabrics - 350°F Cure," The Boeing Co., Rept. BMS 8-256, Seattle, WA, 1999.