CYCOM 919 Epoxy Prepreg
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1 T E C H N I C A L D A T A S H E E T CYCOM 919 EPOXY PREPREG CYCOM 919 Epoxy Prepreg DESCRIPTION CYCOM 919 is a modified epoxy resin supplied on graphite, glass and aramid reinforcing fibers. This resin system offers controlled flow and high elongation permitting direct lamination to honeycomb without the use of additional adhesive. These properties make lightweight sandwich structures possible where impact resistance or a thinner-skin is an important design consideration. Examples include radomes subject to rain erosion and aircraft interiors subject to physical abuse. Other applications are secondary aircraft structure and recreation products. CYCOM 919 composites are serviceable over a temperature range of -67 f to 200 F (-55 C to 93 C) and can be fully cured at 235 F to 260 F (113 C to 127 C) in 60 minutes. FEATURES & BENEFITS Excellent structural properties in solid laminates of moderate thickness Exceptional toughness Controlled flow and high elongation Flame retardant; fire-resistant under FAA-453 Serviceable to 200 F (93 C) No post cure required Curing pressures range from 12 psi (0.084 MPa) vacuum to 100 psi (0.70 MPa) positive pressure 20 day out time at room temperature SUGGESTED APPLICATIONS Radomes Aircraft interiors Aircraft secondary structure
2 CHARACTERISTICS Table 1 Product Description Fiber Finish Resin content, % by weight Flow, % at 250 F (121 C), 50 psi (0.35 MPa) Gel time, minutes at 250 F (121 C) Volatile content, max % Shelf life Recommended storage
3 PROPERTIES Table 2 CYCOM 919 Glass Prepreg Mechanical Performance 1 Product Description Number of plies Cure pressure, psi (MPa) Cure temperature Cure time (cool under pressure) Cure rate per minute Physical Properties Resin content, % by weight Mechanical Properties Tensile strength, ksi (MPa) Tensile modulus, msi (GPa) Compressive strength, ksi (MPa) Compressive modulus, Msi (GPa) Flexural strength, ksi (MPa) Flexural modulus, msi (GPa) Interlaminar shear, ksi, (MPa) 1 Where testing options for either warp or fill apply, warp conditions are assumed unless otherwise indicated 2 Wet: 2 hour water boil
4 Table 3 CYCOM 919 Glass Prepreg Mechanical Performance (continued) 1 Product Description Number of plies Cure pressure, psi (MPa) Cure temperature Cure time (cool under pressure) Cure rate per minute Physical Properties Resin content, % by weight 3-ply Skin Sandwich Properties 2 Sandwich peel, in-lb/3 in. (Nm/m) Flatwise tensile, psi (MPa) Flexural strength, psi (MPa) (tested in warp direction) Flexural strength, psi (MPa) (tested in the fill direction) 1 Where testing options for either warp or fill apply, warp conditions are assumed unless otherwise indicated 2 Honeycomb core: 3/ NP 5052 ½ thick 4.76 mm mm NP 5052, 12.7 mm thick
5 Table 4 CYCOM 919 Kevlar and Carbon Fiber Prepreg Mechanical Performance 1 Product Description Orientation Number of plies Cure pressure, psi (MPa) Cure temperature Bleeder Cure time (cool under pressure) Cure rate per minute Physical Properties Cured ply thickness, in (mm) Specific gravity, g/cc Resin content, % by weight Water absorption, % Mechanical Properties Tensile strength, ksi (MPa) Tensile modulus, msi (GPa) Compressive strength, ksi (MPa) Compressive modulus, msi (GPa) Flexural strength, ksi (MPa) Flexural modulus, Msi (GPa) 1 Where testing options for either warp or fill apply, warp conditions are assumed unless otherwise indicated 2 Wet: 2 hour water boil
6 Table 5 CYCOM 919 Graphite Fiber Prepreg Mechanical Performance 1 Product Description Number of plies Average ply thickness, inch (mm) Cure pressure Cure temperature Cure time (cool under pressure) Cure rate per minute Mechanical Properties Tensile strength, ksi (MPa) Tensile modulus, msi (GPa) Compressive strength, ksi (MPa) Compressive modulus, msi (GPa) Interlaminar shear, ksi (MPa) Short beam shear, ksi (MPa) 1 Where testing options for either warp or fill apply, warp conditions are assumed unless otherwise indicated 2 Wet: 2 hour water boil
7 LAMINATING AND CURING TECHNIQUE The following procedure is one frequently used in preparing autoclave or vacuum cured laminates: 1. Place the lay-up on a tool or caul sheet which has been treated with a release agent or film. Insert a thermocouple into the lay-up near the center ply of the thickest edge section, outside the net trim line. 2. Cover entirely with a release film. Normally no edge resin bleeder system is used. In those cases where vertical resin bleeder system is specified, permeable Armalon fluorocarbon coated fabric may be used. The amount of resin bled away is controlled by the number of dry plies of resin bleeder cloth placed over the perforated release sheet. 3. Install a vacuum bag by standard techniques. Insert at least two vacuum ports through the bag connecting one to the vacuum source and the other, at a point on the part furthest from the source, to a calibrated vacuum gauge. Position part in the oven or autoclave and draw vacuum to check for bag or system leaks. 4. To cure, draw vacuum, usually 20 to 21 inches Hg (0.68 atmospheres) and apply the desired positive air pressure if an autoclave is being used. 5. Commence the heat-up cycle, typically about 3.5 F (1.9 C)/minute, to 250 F (121 C). Hold for 60 minutes at 250 F (121 C). All temperatures are measured by the previously installed thermocouple. 6. Upon completion of the cure, turn off heat and cool under pressure until part temperature has fallen below 150 F (66 C). When fully cooled, the part may be debagged, trimmed and machined as necessary. A post cure is not required. Laminating Materials CYCOM Laminating Material CYCOM Laminating Material FPW Percent FPW Percent Percent Resin Content Percent Resin Content Percent flow versus resin content in relation to various bonding pressures 50 psi 30 psi 0.35 MPa 0.21 MPa 15 psi 0.10 MPa
8 PRODUCT HANDLING AND SAFETY Cytec Engineered Materials recommends wearing clean, impervious gloves when working with epoxy resin systems to reduce skin contact and to avoid contamination of the product. Materials Safety Data Sheets (MSDS) and product labels are available upon request and can be obtained from any Cytec Engineered Materials Office. DISPOSAL OF SCRAP MATERIAL Disposal of scrap material should be in accordance with local, state, and federal regulations. CONTACT INFORMATION GLOBAL HEADQUARTERS for AEROSPACE MATERIALS Tempe, Arizona tel fax NORTH AMERICA Anaheim, California tel fax Orange, California tel fax Cytec Carbon Fiber Piedmont, South Carolina tel fax Greenville, Texas tel fax Winona, Minnesota tel fax Havre de Grace, Maryland tel fax D Aircraft Products Anaheim, California tel fax EUROPE Wrexham, United Kingdom tel fax Östringen, Germany tel fax ASIA Shanghai, China tel fax DISCLAIMER: The data and information provided in this document have been obtained from carefully controlled samples and are considered to be representative of the product described. Cytec Engineered Materials (Cytec) does not express or imply any guarantee or warranty of any kind including, but not limited to, the accuracy, the completeness or the relevance of the data and information set out herein. Because the properties of this product can be significantly affected by the fabrication and testing techniques employed, and since Cytec does not control the conditions under which its products are tested and used, Cytec cannot guarantee the properties provided will be obtained with other processes and equipment. No guarantee or warranty is provided that the product is adapted for a specific use or purpose. Cytec declines any liability with respect to the use made by any third party of the data and information contained herein. Cytec has the right to change any data or information when deemed appropriate. All trademarks are the property of their respective owners. PAT-269-A 4/13
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