RM o F Cure Toughened Epoxy Prepreg FOR HIGH PERFORMANCE AEROSPACE APPLICATIONS

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1 RM o F Cure Toughened Epoxy Prepreg FOR HIGH PERFORMANCE AEROSPACE APPLICATIONS

2 RM 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 Tel: Page 1

3 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 o Tensile Modulus (Msi) ASTM D 3039 RT Dry o Compression Strength ASTM D 3410 RT Dry 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 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 South Tech Boulevard Miamisburg, OH Tel: Page 2

4 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 o Tensile Strength ASTM D 3039 RT Wet o F Dry o F Wet o F Dry o Tensile Strength ASTM D 3039 RT Dry o F Wet o F Dry 19.0 RT Dry o Tensile Modulus (Msi) ASTM D 3039 RT Wet o F Dry o F Wet o F Dry o Tensile Modulus (Msi) ASTM D 3039 RT Dry o F Wet o F Dry 226 RT Dry o Compression Strength SRM-1R-94 RT Wet o F Dry o F Wet o F Dry 18.0 RT Dry o Compression Modulus SRM-1R-94 RT Wet 17.6 (Msi) 250 o F Dry o F Wet o F Dry 18.6 In-Plane Shear Strength ASTM D 3518 RT Dry o F Wet o F Dry 0.85 In-Plane Shear Modulus (Msi) ASTM D 3518 RT Dry o F Wet South Tech Boulevard Miamisburg, OH Tel: Page 3

5 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 o F Wet 7.4 ASTM D 5528 RT Dry 1.47 ASTM D o F Dry 47.7 RT Dry 51.9 Open Hole Tensile Modulus (Msi) Open Hole Compression Strength ASTM D 5766 ASTM D o F Dry 7.6 RT Dry 7.3 RT Dry 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 o F Wet 6.6 SRM-2R-94 RT Dry 24.0 ASTM E 1640 Dry 396 Wet 320 *Wet Conditioning F with 85% Relative Humidity to Saturation; Avg. Pick-up % By Weight -HTS45 is a standard modulus 12K carbon fiber South Tech Boulevard Miamisburg, OH Tel: Page 4

6 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 o Tensile Strength ASTM D o Tensile Modulus (Msi) ASTM D o Tensile Modulus (Msi) ASTM D 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 o F Dry o F Wet o F Dry 111 RT Dry o F Dry o F Wet o F Dry 9.6 RT Dry 9.4 RT Wet o F Dry o F Wet o F Dry 9.4 RT Dry o F Dry o F Wet o F Dry 144 RT Dry 144 RT Wet o F Dry o F Wet 74 RT MEK Soak o F MEK Soak o F Dry 9.2 RT Dry 8.9 RT Wet o F Dry o F Wet 9.0 RT MEK Soak o F MEK Soak South Tech Boulevard Miamisburg, OH Tel: Page 5

7 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 o F Wet 10.5 RT MEK Soak o F MEK Soak o F Dry 0.82 RT Dry 0.74 In-Plane Shear Modulus (Msi) ASTM D o F Wet 0.43 RT MEK Soak o F MEK Soak 0.52 RT Dry 12.6 Interlaminar Shear Strength ASTM D o F Dry 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 o F Dry 44 RT Dry o F Dry 7.0 RT Dry 6.8 RT Dry o F Wet 30 RT Dry o F Wet 6.1 SRM-2R-94 RT Dry 34 ASTM E 1640 Dry 404 Wet 297 *Wet Conditioning F with 85% Relative Humidity to Saturation; Avg. Pick-up % By Weight -HTS40 3K is a standard modulus carbon fiber South Tech Boulevard Miamisburg, OH Tel: Page 6

8 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 o F Dry o Tensile Modulus (Msi) ASTM D o Compression Strength SRM-1R-94 RT Dry o F Dry 9.4 RT Dry o F Dry o Compression Modulus SRM-1R-94 RT Dry o F Dry 9.3 Glass Transition Temperature, Tg Onset at G ( o F) ASTM E 1640 Dry 399 Wet 311 *Wet Conditioning F with 85% Relative Humidity to Saturation; Avg. Pick-up % By Weight -HTS40 3K is a standard modulus carbon fiber South Tech Boulevard Miamisburg, OH Tel: Page 7

9 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) F Cure 350 F Cure 360 F Cure Glass Transition Temperature of RM-2005 Epoxy Carbon Plain Weave Cured at the Lower, Nominal, and Upper Cure Cycle Temperature Ranges (G Rollover) South Tech Boulevard Miamisburg, OH Tel: Page 8

10 RM-2005 Typical Viscosity Profile Example RDA Curve for RM-2005 Prepreg South Tech Boulevard Miamisburg, OH Tel: Page 9

11 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 /-0 minutes. Step 5. Cool at 1 10 F/ min, when temperature is below 150 F release pressure South Tech Boulevard Miamisburg, OH Tel: Page 10

12 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 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 Tel: Page 11