RESEARCH IN THE FIELD OF FIBERGLASSREINFORCED SANDWICH STRUCTURE FOR AIRFRAME USE
Final rept. for 10 Jun 1963-29 Feb 1964
OKLAHOMA UNIV RESEARCH INST NORMAN
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The research covered in this report involves investigation of the effects of raw materials usage and fabrication process variables on the final strength properties of fiberglass-reinforced plastic FRP sandwich structure suitable for use as a primary airframe structural material. The program encompassed the two types of sandwich fabrication used industrially, the one- step process method and the method whereby pre-laminated facings are bonded to the core in a separate step. The materials chosen for study were the promising Volan A finished 181 fiberglass fabric and EPON 828 epoxy resin activated by curing agent Z. Thin, 3-ply facings of these materials used in conjunction with honeycomb cores were the basic elements of the structural sandwich. The results of the research program include the isolation of the optimum conditions of fabrication the expected strength values for these optimum fabrication conditions the best lay-up method and the performance of several adhesive system-core material combinations with optimum conditions of cure for each. Among the many by-products of the research effort is a multi-ply coating machine which is capable of impregnating several layers of fabric simultaneously.