RM-2005 350 o F Cure Toughened Epoxy Prepreg FOR HIGH PERFORMANCE AEROSPACE APPLICATIONS
RM-2005 350 o F Cure Toughened Epoxy Prepreg Renegade Materials RM-2005 is a 350 F Curing Toughened Epoxy Prepreg system. In response to widespread aerospace market demand for an alternative to industry-standard toughened epoxies, Renegade Materials has developed the NEXT generation Toughened Epoxy Prepreg, optimized for both hand-lay-up and automated fiber placement (AFP) processing. RM-2005 is supported by an extensive mechanical property database on both carbon tape and fabric. Excellent mechanical performance and damage tolerance makes RM-2005 a superior choice for military or commercial structural applications. RM-2005 is readily available with no minimum order quantities and the fastest lead times in the industry. Straightforward 350 F Cure. Typical RM-XXXX Resin Properties Designed for demanding aerospace structural applications. Developed for optimized tack and handle ability. Delivers an excellent balance of properties for service up to 300 o F. Available in woven, unidirectional and slit-tape product forms using all fibers including carbon, quartz and glass. Nano-enhancements for tailored laminate properties and multi-functional performance available. RM-2005 Resin Properties Cured Resin Density 1.26 g/cc Resin Flex Strength 25 ksi Resin Flex Modulus 526 Msi Resin Flex Strain to Failure 5.0 % 3363 South Tech Boulevard Miamisburg, OH 45342 Tel: 937-350-5274 Page 1
Typical Cured Mechanical Properties for RM-2005 / Intermediate Modulus Carbon Uni-Directional Tape (All Normalized to 60% Fiber Volume Except for In-Plane and Short Beam Shear Properties.) Property Test Method Test Condition Test Result 0 o Tensile Strength ASTM D 3039 RT Dry 390 0 o Tensile Modulus (Msi) ASTM D 3039 RT Dry 23.9 0 o Compression Strength ASTM D 3410 RT Dry 240 0 o Compression Modulus (Msi) ASTM D 3410 RT Dry 20.9 Flexural Strength ASTM D 790 RT Dry 272 Flexural Modulus (Msi) ASTM D 790 RT Dry 20.7 Interlaminar Shear Strength Interlaminar Shear Strength ASTM D 2344 RT Dry 17.0 ASTM D 2344 200 F Dry 13.0 In-Plane Shear Strength ASTM D 3518 RT Dry 18.4 In-Plane Shear Modulus (Msi) ASTM D 3518 RT Dry 0.6 Open Hole Compression SACMA SRM-3 RT Dry 52.0 Open Hole Compression SACMA SRM-5 RT Dry 58.0 3363 South Tech Boulevard Miamisburg, OH 45342 Tel: 937-350-5274 Page 2
Typical Cured Mechanical Properties for RM-2005 / Standard Modulus Carbon Unidirectional Tape (Continued) (All Data Normalized to 57% Fiber Volume Except for Shear Properties.) RM-2005-HTS45-12K-E23-Unitape (130 gsm) Property Test Method Test Condition* Test Result -75 o F Dry 281 RT Dry 335 0 o Tensile Strength ASTM D 3039 RT Wet 322 250 o F Dry 301 250 o F Wet 325-75 o F Dry 12.6 90 o Tensile Strength ASTM D 3039 RT Dry 14.1 250 o F Wet 3.9-75 o F Dry 19.0 RT Dry 19.6 0 o Tensile Modulus (Msi) ASTM D 3039 RT Wet 18.9 250 o F Dry 18.8 250 o F Wet 20.7-75 o F Dry 1.53 90 o Tensile Modulus (Msi) ASTM D 3039 RT Dry 1.37 250 o F Wet 0.97-75 o F Dry 226 RT Dry 234 0 o Compression Strength SRM-1R-94 RT Wet 222 250 o F Dry 215 250 o F Wet 168-75 o F Dry 18.0 RT Dry 17.8 0 o Compression Modulus SRM-1R-94 RT Wet 17.6 (Msi) 250 o F Dry 20.0 250 o F Wet 19.2-75 o F Dry 18.6 In-Plane Shear Strength ASTM D 3518 RT Dry 17.8 250 o F Wet 11.8-75 o F Dry 0.85 In-Plane Shear Modulus (Msi) ASTM D 3518 RT Dry 0.73 250 o F Wet 0.43 3363 South Tech Boulevard Miamisburg, OH 45342 Tel: 937-350-5274 Page 3
Typical Cured Mechanical Properties for RM-2005 / Standard Modulus Carbon Unidirectional Tape (Continued) (All Data Normalized to 57% Fiber Volume Except for Shear, G IC and Tg Properties) Property Interlaminar Shear Strength G IC Fracture Toughness (in-lb/in 2 ) Open Hole Tensile Strength RM-2005-HTS45-12K-E23-Unitape (130 gsm) Test Method ASTM D 2344 Test Condition* Test Result RT Dry 16.2 250 o F Wet 7.4 ASTM D 5528 RT Dry 1.47 ASTM D 5766-75 o F Dry 47.7 RT Dry 51.9 Open Hole Tensile Modulus (Msi) Open Hole Compression Strength ASTM D 5766 ASTM D 6484-75 o F Dry 7.6 RT Dry 7.3 RT Dry 50 250 o F Wet 38 Open Hole Compression Modulus (Msi) Compression After Impact Glass Transition Temperature, Tg Onset at G ( o F) ASTM D 6484 RT Dry 6.9 250 o F Wet 6.6 SRM-2R-94 RT Dry 24.0 ASTM E 1640 Dry 396 Wet 320 *Wet Conditioning - 160 F with 85% Relative Humidity to Saturation; Avg. Pick-up 1.2-1.3% By Weight -HTS45 is a standard modulus 12K carbon fiber. 3363 South Tech Boulevard Miamisburg, OH 45342 Tel: 937-350-5274 Page 4
Typical Cured Mechanical Properties for RM-2005 / Standard Modulus Carbon Plain Weave Property (All Data Normalized to 54.5% Fiber Volume) RM-2005-HTS40-3K-E13-PW Fabric (195 gsm) Test Method 0 o Tensile Strength ASTM D 3039 90 o Tensile Strength ASTM D 3039 0 o Tensile Modulus (Msi) ASTM D 3039 90 o Tensile Modulus (Msi) ASTM D 3039 0 o Compression Strength SRM-1R-94 0 o Compression Modulus (Msi) SRM-1R-94 Test Condition* Test Result -75 o F Dry 117 RT Dry 127 RT Wet 126 250 o F Dry 143 250 o F Wet 138-75 o F Dry 111 RT Dry 115 250 o F Dry 126 250 o F Wet 124-75 o F Dry 9.6 RT Dry 9.4 RT Wet 9.7 250 o F Dry 8.9 250 o F Wet 9.4-75 o F Dry 9.4 RT Dry 9.1 250 o F Dry 10.1 250 o F Wet 9.0-75 o F Dry 144 RT Dry 144 RT Wet 117 250 o F Dry 125 250 o F Wet 74 RT MEK Soak 144 250 o F MEK Soak 100-75 o F Dry 9.2 RT Dry 8.9 RT Wet 9.0 250 o F Dry 9.0 250 o F Wet 9.0 RT MEK Soak 9.1 250 o F MEK Soak 9.9 3363 South Tech Boulevard Miamisburg, OH 45342 Tel: 937-350-5274 Page 5
Typical Cured Mechanical Properties for RM-2005 / Standard Modulus Carbon Plain Weave (Continued) (Data Normalized to 54.5% Fiber Volume Except for Shear, G IC and Tg Properties) RM-2005-HTS40-3K-E13-PW Fabric (195 gsm) Property Test Method Test Condition* Test Result -75 o F Dry 19.0 RT Dry 18.5 In-Plane Shear Strength ASTM D 3518 250 o F Wet 10.5 RT MEK Soak 18.0 250 o F MEK Soak 13.9-75 o F Dry 0.82 RT Dry 0.74 In-Plane Shear Modulus (Msi) ASTM D 3518 250 o F Wet 0.43 RT MEK Soak 0.67 250 o F MEK Soak 0.52 RT Dry 12.6 Interlaminar Shear Strength ASTM D 2344 250 o F Dry 9.4 250 o F Wet 6.0 G IC Fracture Toughness (in-lb/in 2 ) ASTM D 5528 RT Dry 2.36 Open Hole Tensile Strength Open Hole Tensile Modulus (Msi) Open Hole Compression Strength Open Hole Compression Modulus (Msi) Compression After Impact Glass Transition Temperature, Tg Onset at G ( o F) ASTM D 5766 ASTM D 5766 ASTM D 6484 ASTM D 6484-75 o F Dry 44 RT Dry 46.6-75 o F Dry 7.0 RT Dry 6.8 RT Dry 47 250 o F Wet 30 RT Dry 6.2 250 o F Wet 6.1 SRM-2R-94 RT Dry 34 ASTM E 1640 Dry 404 Wet 297 *Wet Conditioning - 160 F with 85% Relative Humidity to Saturation; Avg. Pick-up 1.2-1.3% By Weight -HTS40 3K is a standard modulus carbon fiber. 3363 South Tech Boulevard Miamisburg, OH 45342 Tel: 937-350-5274 Page 6
Typical Cured Mechanical Properties for RM-2005 / Standard Modulus Carbon Eight-Harness Satin Weave (Data Normalized to 54.3% Fiber Volume; Except Shear and Tg Properties) Property RM-2005-HTS40-3K-E13-8HS Fabric (370 gsm) Test Method 0 o Tensile Strength ASTM D 3039 Test Condition* Test Result RT Dry 129 250 o F Dry 138 0 o Tensile Modulus (Msi) ASTM D 3039 0 o Compression Strength SRM-1R-94 RT Dry 9.1 250 o F Dry 9.4 RT Dry 129 250 o F Dry 103 0 o Compression Modulus SRM-1R-94 RT Dry 9.1 250 o F Dry 9.3 Glass Transition Temperature, Tg Onset at G ( o F) ASTM E 1640 Dry 399 Wet 311 *Wet Conditioning - 160 F with 85% Relative Humidity to Saturation; Avg. Pick-up 1.2-1.3% By Weight -HTS40 3K is a standard modulus carbon fiber. 3363 South Tech Boulevard Miamisburg, OH 45342 Tel: 937-350-5274 Page 7
Glass Transition Temperature (G' Rollover, F) RM-2005 Glass Transition Temperature Data Glass Transition Temperature, Dry and Wet, of the RM-2005 Epoxy on the Three Reinforcements (G Rollover). 450 400 350 300 250 200 150 340 F Cure 350 F Cure 360 F Cure 100 50 0 Glass Transition Temperature of RM-2005 Epoxy Carbon Plain Weave Cured at the Lower, Nominal, and Upper Cure Cycle Temperature Ranges (G Rollover). 3363 South Tech Boulevard Miamisburg, OH 45342 Tel: 937-350-5274 Page 8
RM-2005 Typical Viscosity Profile Example RDA Curve for RM-2005 Prepreg. 3363 South Tech Boulevard Miamisburg, OH 45342 Tel: 937-350-5274 Page 9
Recommended Bagging Scheme for RM-2005 Recommended Cure Cycle for RM-2005 All temperatures and times are based upon the lagging thermocouple unless otherwise specified. Step 1. Vacuum hold for 60 minutes at room temperature Step 2. Heat 1 10 F/ minute to 350±10 F apply 30±5 psig pressure until temperature reaches 225± 5 F Step 3. Apply 85±5 psig autoclave pressure and vent to atmosphere. Step 4 Hold temperature at 350±10 F for 120 +15/-0 minutes. Step 5. Cool at 1 10 F/ min, when temperature is below 150 F release pressure. 3363 South Tech Boulevard Miamisburg, OH 45342 Tel: 937-350-5274 Page 10
Renegade Materials Corporation is a global leader in manufacturing composite materials for aerospace applications. We deliver light-weight, highly-engineered prepregs, adhesives and hybrid composite systems to enable maximum fuel efficiency in commercial and military aircraft structures. For pricing or additional information on Renegade Material s products, please visit our website at www.renegadematerials.com This document and any pricing provided on this product, are considered proprietary, confidential and competition-sensitive and are not to be disclosed to any third parties without express written consent of Renegade Materials. Revision Date: 12-OCT-2013 KOA 3363 South Tech Boulevard Miamisburg, OH 45342 Tel: 937-350-5274 Page 11