3960 PREPREG SYSTEM. Flexible Processing Prepreg can be suitably processed in either AFP or hand lay-up methodologies.
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1 396 PREPREG SYSTEM Toray s nextgeneration #396 prepreg system demonstrates the next leap in performance of aerospace materials. Complementary pairing of the #396 resin system with stateoftheart T11G carbon fiber provides the unparalleled properties expected of materials for the future. High toughness, exceptional tensile performance, and retention of hot/wet performance to 25 F (121 C) make the #396 system the clear choice for the future demands of the aerospace industry. High Heat Tolerance High Tg and hot/wet performance enable retention of critical properties like openhole compression to 121 C (25 F) without compromising material toughness. Resin Chemistry System features synergy with T11G, capturing fiber s full capability and maximizing translation of carbon fiber strand strength. Flexible Cure Methods Proven flexibility in curing and consistency in mechanical properties has been achieved by oven cure and autoclave, with or without an intermediate dwell. Flexible Processing Prepreg can be suitably processed in either AFP or hand layup methodologies. Laminate Toughness Toray s proven interlayer toughening technology sets the standard for laminate impact resistance and fracture toughness
2 396 AVAILABLE PRODUCT FORMATS PART NUMBER FIBER FORMAT FIBER TYPE/STYLE FAW (GSM) RC % WEIGHT ROLL WIDTH (IN) P173EBN19 Unidirectional T11G /39/36/12/6/.5/.25 FT62YER3EI Plain Weave T11G12K NEAT RESIN PHYSICAL PROPERTIES PROPERTY METHOD UNITS VALUE Density ASTM D595 g/cc Tg (Dry) DMA F ( C) 391 (199) Tg (Wet) DMA F ( C) 328 (165) Wet conditioning : 16 F/85% RH until equilibrium RESIN VISCOSITY CURVE VISCOSITY (P) sales@toraycma.com Updated November 8, 217
3 396 LAMINA/LAMINATE MECHANICAL PROPERTIES: UD T11G PROPERTY SYMBOL METHOD UNITS Tensile Strength F 1t ASTM D339 Ksi (MPa) AUTOCLAVE OVEN CTA RTA ETW CTA RTA ETW 551 (3797) 9 Tensile Strength F 2t ASTM D339 Ksi (MPa) Tensile Modulus E 1t ASTM D339 Msi (GPa) 25.1 (173) 9 Tensile Modulus E 2t ASTM D339 Msi (GPa) Compressive Strength F 1c ASTM D6641 Ksi (MPa) 9 Compressive Strength F 2c ASTM D6641 Ksi (MPa) Compressive Modulus E 1c ASTM D6641 Msi (GPa) 232 (1599) 37 (252) 21.9 (151) 9 Compressive Modulus E 2c ASTM D6641 Msi (GPa) InPlane Shear F 12 ASTM D5379 Ksi (MPa) InPlane Shear Modulus G 12 ASTM D5379 Msi (GPa) Short Beam Shear Strength SBS ASTM D2344 Ksi (MPa) Open Hole Tension Strength (25/5/25) OHT ASTM D5766 Ksi (MPa) Open Hole Compression Strength (25/5/25) OHC ASTM D6484 Ksi (MPa) Compression After Impact (25/5/25) Impact at 27inlbs (6.7J/mm) CAI ASTM D7137 Ksi (MPa) 23.1 (16) 9 (623) Laminate Density ρ g/cc Fiber Volume Fraction V f ASTM D792 % (93).7 (5.) 16.7 (115) 12 (72) 48 (331) 48 (331) 12 (71) 21.1 (146) 8.7 (6).5 (3.5) 36 (244) 511 (3523) 11.4 (78) 25.2 (174) 1.5 (1) 221 (1523) Cured Ply Thickness CPT Inch (mm).72 (.18).73 (.19) Tension and compression values are normalized to the indicated V f herein. 49 (34) 22.1 (153) 1.5 (11) 15.2 (15) 1.3 (9.) 23.9 (165) 9 (619) 56 (383) 534 (3682) 11.4 (79) 25. (172) 1.3 (9.3) 229 (1576) 38 (265) 22.3 (154) 1.4 (1) 12.1 (84).7 (5.) 17.2 (119) 95 (656) 49 (337) 45 (31) 37 (252) sales@toraycma.com Updated November 8, 217
4 396 LAMINA/LAMINATE MECHANICAL PROPERTIES: PW T11G12K PROPERTY SYMBOL METHOD UNITS OVEN CTA RTA ETW Tensile Strength F 1t ASTM D339 Ksi (MPa) 216 (1489) 22 (1519) 9 Tensile Strength F 2t ASTM D339 Ksi (MPa) 28 (1435) 218 (151) Tensile Modulus E 1t ASTM D339 Msi (GPa) 12.4 (86) 12. (83) 9 Tensile Modulus E 2t ASTM D339 Msi (GPa) 12.2 (84) 12.7 (87) Compressive Strength F 1c ASTM D6641 Ksi (MPa) 125 (863) 128 (88) 9 Compressive Strength F 2c ASTM D6641 Ksi (MPa) 132 (98) 129 (889) Compressive Modulus E 1c ASTM D6641 Msi (GPa) 11.9 (82) 1.7 (74) 9 Compressive Modulus E 2c ASTM D6641 Msi (GPa) 1.7 (74) 11. (76) Short Beam Shear Strength SBS ASTM D2344 Ksi (MPa) 14.1 (97) 12.9 (89) Open Hole Tension Strength (25/5/25) OHT ASTM D5766 Ksi (MPa) 79 (545) 82 (563) Open Hole Compression Strength (25/5/25) OHC ASTM D6484 Ksi (MPa) 51 (351) 46 (318) 36 (245) Compression After Impact (25/5/25) Impact at 27inlbs (6.7J/mm) CAI ASTM D7137 Ksi (MPa) 45 (313) Laminate Density ρ g/cc Fiber Volume Fraction V f ASTM D792 % 52.8 Cured Ply Thickness CPT Inch (mm).79 (.2) Tension and compression values are normalized to the indicated V f herein. Note: CTA: 75 F (6 C), Ambient RTA: 72 F (22 C), Ambient ETW: 25 F (121 C) Ambient, Conditioned at 16 F/85% RH until equilibrium sales@toraycma.com Updated November 8, 217
5 396 BAGGING PROCEDURE STORAGE LIFE Out Life F Freezer Life 2 <1 F CURE CYCLE AUTOCLAVE 1. Apply vacuum of 22 inhg (56 mmhg) minimum. 2. Apply 85 +1/ psi ( / bar) of pressure to the laminate. 3. Vent the vacuum bag to atmospheric pressure once the pressure reaches 2 psi (1.4 bar). 4. Heat the part temperature to 355 ±1 F (18 ±5 C) at a ramp rate of 1. to 5. F/min (.5 to 2.7 C/min). 5. Hold for 12 +3/ minutes at 355 ±1 F (18 ±5 C). 6. Under pressure, cool to 15 F (65 C) or lower at a maximum ramp rate of 5 F/min (2.7 C/min). CURE CYCLE OVEN 1. Apply vacuum of 28 inhg (71 mmhg) minimum, and maintain for at least three hours prior to beginning cure cycle. 2. Heat the part temperature to 25 ±1 F (12 ±5 C) at a ramp rate of 1. to 5. F/min (.5 to 2.7 C/min). 3. Hold for 24 +3/ minutes at 25 ±1 F (12 ±5 C). 4. Heat the part temperature to 355 ±1 F (18 ±5 C) at a ramp rate of 1. to 5. F/min (.5 to 2.7 C/min). 5. Hold for 12 +3/ minutes at 355 ±1 F (18 ±5 C). 6. Cool to 15 F (65 C) or lower at a maximum ramp rate of 5 F/min (2.7 C/min). OVEN CURE PROCESS 2 12 AUTOCLAVE CURE PROCESS TIME (MIN) Temperature Pressure PRESSURE (BAR) Temperature ( C) Vacuum (kpa) TIME (MINUTES) 1 VACUUM (kpa) sales@toraycma.com Updated November 8, 217
3900 PREPREG SYSTEM. Mechanically Stable Mechanical working life of product is over 40 days, allowing for lay-up of large parts.
PREPREG SYSTEM -series prepregs are highly-toughened 350 F (177 C) cure systems. It is available in a variety of configurations, including unidirectional tape for manual or automated tape laying applications,
2510 PREPREG SYSTEM. Industry Database FAA approved design allowable values (AGATE methodology), results in a low cost one-batch equivalency.
PREPREG SYSTEM The 251 prepreg system is specifically formulated for out-of-autoclave (OOA) processing of aerospace primary structures. This prepreg system has excellent all-around structural properties
3900 PREPREG SYSTEM. Mechanically Stable Mechanical working life of product is over 40 days, allowing for lay-up of large parts.
PREPREG SYSTEM 3900-series prepregs are highly-toughened 350 F (177 C) cure systems. It is available in a variety of configurations, including unidirectional tape for manual or automated tape laying applications,
2510 PREPREG SYSTEM. Industry Database FAA approved design allowable values (AGATE methodology), results in a low cost one-batch equivalency.
PREPREG SYSTEM The 251 prepreg system is specifically formulated for out-of-autoclave (OOA) processing of aerospace primary structures. This prepreg system has excellent all-around structural properties
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