From GPS to Galileo: Evolution and Applications
- Paper number
IAC-04-IAA.6.15.P.03
- Author
Mr. Ignacio Arenas-Jimenez, Spain
- Year
2004
- Abstract
Carbon fiber reinforced plastics (CFRP) have been used in aerospace engineering because of its light weight, high strength and rigidity, design flexibility, etc. However, the impact resistance of CFRP is not strong enough for space structures facing the threat of debris collision. Thus we have examined to develop a low-cost molding method for thermoplastic resin composites. A CF/PC prepreg was manufactured by a hot press machine at a molding temperature (from 543 K to 583 K), pressure (from 2 MPa to 7 MPa), and pressurization time (from 10 minutes to 25 minutes), which were changed, respectively. The adequate molding conditions were determined by the surface observation of the CF/PC prepregs. Laminated composites were also fabricated by stacking CF/PC prepregs in the hot press machine. Specimens of laminated composite [0] 4 , [90] 4 , and [0 2 /90 2 ] S were prepared for static tensile and the low-velocity impact tests. Both of CF/PCs and CF/EPs had almost linear Stress-Strain curves until the test specimens were fractured. The tensile strength and failure strain of the CF/EPs were larger than those of the CF/PCs because the laminates of CF/PCs had initial voids and micro cracks after molding. The Young’s modulus of the laminates [0] 4 was calculated by the rule of mixture including influences of voids and stitching fibers. For the impact test, although the fracture progressed along the stitching fiber of the CF/EP laminates, the surface of CF/PC laminates was changed greatly in the large range. The absorbed energy and penetration limit of CF/PCs were larger than those of CF/EPs. As a result, it was found that CF/PCs are promising materials for high impact resistance structural materials and their mechanical properties can be increased by the improvement of the molding method in detail.
- Abstract document