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The prepreg should be removed from the freezer, thawed and allowed to reach room temperature before removal from the protective polythene bag.

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ACG MTM 46 INTERMEDIATE SERVICE TEMPERATURE VACUUM PROCESSABLE PREPREG Product Description MTM 46 is a flexible cure epoxy resin matrix developed for the manufacture of aerospace components using oven/vacuum
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ACG MTM 46 INTERMEDIATE SERVICE TEMPERATURE VACUUM PROCESSABLE PREPREG Product Description MTM 46 is a flexible cure epoxy resin matrix developed for the manufacture of aerospace components using oven/vacuum bag moulding processes. MTM46 can also be autoclave cured. MTM46 has been developed specifically for the production of high quality laminates using low pressure processing. Initial cure may be carried out at temperatures as low as 80 C (176 F), allowing the use of low cost tooling for prototypes and short production runs. However, it is recommended that the part is subjected to a minimum of a 1 hour cure or post-cure of 120 C (248 F) before any subsequent processing is carried out. MTM46 must be post-cured at 180 C (356 F) to attain full mechanical properties; it can achieve a dry Tg of 190 C (374 F) and a wet Tg of 130 C (266 F). MTM46 is an ideal candidate material for the low cost production of primary and secondary structures in FAR23 aircraft and unmanned air vehicles (UAVs). It is also suitable for secondary structure in civil aircraft and helicopters. Features 60 days out life. Tack and drape properties ideal for complex mouldings. 80 to 180 C (176 to 356 F) initial cure. Minimum wet Tg: 115 C (239 F) after 125 C (257 F) cure. Dry Tg: 190 C (374 F) after 180 C (356 F) post-cure. Wet Tg: 130 C (266 F) after 180 C (356 F) post-cure. Instructions for Use The prepreg should be removed from the freezer, thawed and allowed to reach room temperature before removal from the protective polythene bag. Prepreg should be cut to shape and laid up in accordance with design instructions. Care must be taken to ensure the prepreg conforms exactly to the tool shape, especially around internal corners. The lay-up should be vacuum debulked at regular intervals using a P3 (pin pricked) Halar release film on the prepreg surface, followed by the application of a lightweight breather. Depending on prepreg format, a vacuum of 980 mbar (29in Hg) should be applied for up to 30 minutes. Page 1 of 7 The level of tack increases with temperature; the material is designed to have optimum tack for layup between 18 and 24 C (64 and 75 F). Recommended Bagging Arrangement Bag Non-perforated Release Film [Halar or FEP to extend a minimum of 25mm (1in) beyond the laminate edge] Flash Tape to seal edge of release film to the tool surface Sealant Tape Breather (see note below) Dry Glass Tows (see note below) Laminate Lay-up Released Tool Surface Glass Tows Detail Placing dry glass tows at 0.5m (20in) intervals around the edge of the laminate will provide air paths under the release film and into the breather (depicted above). Release Film Detail The release film may be taped down to the tool surface with flash tape as required. Breather Detail Apply one ply of heavyweight breather 340gsm (10oz/yd²). The breather should connect directly to the vacuum ports, where two or three additional layers of breather should be applied locally. The highest available vacuum, typically 980mbar (29in Hg), must be achieved, It is essential that the laminate is fully exposed to the vacuum. This should be checked by placing a gauge at the opposite side of the laminate to the position of the vacuum port. A vacuum drop test should be performed prior to curing the part. The test must show a pressure drop of no more than 68mbar (2in Hg) within 10 minutes once the vacuum is removed. Exotherm MTM46 is a reactive formulation which can undergo severe exothermic heat build up during the initial curing process if incorrect curing procedures are followed. Great care must be taken to ensure that safe heating rates; dwell temperatures and layup/bagging procedures are adhered to, especially when moulding solid laminates in excess of 10mm (0.4in) thickness. The risk of exotherm increases with lay-up thickness and increasing temperature. It is strongly recommended that the user carries out representative trials of all the relevant circumstances to allow a safe cure cycle to be specified. It is also important to recognise that the model or tool material and its thermal mass, combined with the insulating effect of breather/bagging materials can affect the risk of exotherm in particular cases. Page 2 of 7 All statements, technical information and recommendations contained in this data sheet are given in good faith and are based on tests believed to be reliable, but their accuracy and completeness are not guaranteed. They do not constitute an offer to any person and shall not be deemed to form the basis of any subsequent contract, nor to constitute any warranty or representation as to quality, merchantability or fitness for purpose. All products are sold subject to the seller s Standard Terms and conditions of Sale. Accordingly, the user shall determine the suitability of the products for their intended use prior to purchase and shall assume all risk and liability in connection therewith. It is the responsibility of those wishing to sell items made from or embodying the products to inform the user of the properties of the products and the purposes for which they may be suitable, together with all precautionary measures required in handling those products. The information contained herein is under constant review and liable to be modified from time to time. Copyright 2009 All rights reserved worldwide. All trademarks or registered trademarks are the property of their respective owners. If in doubt, contact the Advanced Composites Group technical support staff for advice on modified cure cycles for thick laminates, especially those greater than 10mm (0.4in). Cure Vacuum Bag Processing Autoclave Processing Ramp Rate 2 C (3.6 F)/minute 2 C (3.6 F)/minute Pressure N/A 90psi (6.2 bar) Vacuum Pressure 980mbar (29in Hg ) 980mbar (29in Hg ) Cure Time 1 hour at 120 C (248 F) 1 hour at 120 C (248 F) 3 C (5 F)/minute maintain vacuum 3 C (5 F)/minute maintain vacuum Cooling Cycle pressure, vent when the temperature pressure, vent when the temperature has has reached 50 C (90 F) below the reached 50 C (90 F) below the cure cure temperature. temperature. Alternative Cure Options Time Glass Transition Temperature C ( F) DMA Temperature C ( F) (Hours) Onset 5 80 (176) 76 (169) (212) 109 (228) (248) 122 (251) (266) 140 (284) (356) 190 (374) Post-Cure Components must be post-cured to develop the maximum Tg and mechanical properties. It is recommended that parts are subjected to a minimum cure or post-cure of 120 C (248 F) before further processing operations are carried out. However, the material will still be in a relatively low state of cure. To develop full mechanical performance, it is necessary to post-cure parts to 180 C (356 F). Parts may be loaded into a pre-heated oven or heated at 3 C (5 F)/minute to the initial cure temperature. Continue heating at a rate of 0.3 C (0.54 F)/minute to post-cure temperature. Maintain at post-cure temperature for 1 hour -0/+30 minutes. Cool at a rate of 3 C (5 F)/minute to 70 C (158 F). Note: Large components should be adequately supported to avoid distortion. Page 3 of 7 Post-Cure Temperature C ( F) Glass Transition Temperature C ( F) DMA Onset 120 (248) 122 (251) 130 (266) 140 (284) 180 (356) 190 (374) Technical Data Matrix Resin Properties Cured Resin Property Cured resin density at 21 C (70 F) g/cm Prepreg Volatile content % 1 Prepreg Work Life at 21 C (70 F) Days 60 DMA Tg onset after 14days water immersion at 70 C (158 F): 1 hour at 120 C (248 F) cure/no post-cure 90 minutes at 130 C (266 F)/no post-cure 90 minutes at 130 C (266 F)/1 hour at 180 C (356 F) post-cure C ( F) 118 (244) 125 (257) 133 (271) Mechanical Data Material Details: MTM46/HTS(12K) %RW Unidirectional HTS-5631 carbon prepreg 1 hour at 120 C (250 F), 6bar (90psi) autoclave pressure Cure Details: No post-cure Zero bleed process achieving 57% Fibre Volume All results (except shear) normalised to 60% Fibre volume Test Conditions for Data Property Test 20 C (68F ) Method Dry Tensile Modulus D 3039 GPa (msi) (18.6) Compressive Modulus D 3410 GPa (msi) (17.2) Trans. Tensile Modulus D 3039 GPa (msi) 9 (1.3) Trans. Comp. Modulus D 3410 GPa (msi) 10.3 (1.5) Tensile Strength D 3039 MPa (ksi) 2278 (330.3) Compressive Strength D 3410 MPa (ksi) 1352 (196) Trans. Tensile Strength D 3039 MPa (ksi) 33.9 (4.9) Trans. Comp. Strength D 3410 MPa (ksi) 210 (30.4) Tensile Strain to Failure D 3039 % 1.79 Comp. Strain to Failure D 3410 % 1.12 Trans. Tensile Strain D 3039 % 0.40 Trans. Comp. Strain D 3410 % 2.12 In-Plane Shear Modulus D 3518 GPa (msi) 3.95 (0.57) In-Plane Shear Strength D 3518 MPa (ksi) 98.1 (14.2) Maj. Tensile Poissons Ratio D Maj. Comp. Poissons Ratio D Min. Tensile Poissons Ratio D Min. Comp Poissons Ratio D Flexural Modulus CRAG 200 GPa (msi) (16.5) Flexural Strength CRAG 200 MPa (ksi) 2262 (328) ILSS D 2344 MPa (ksi) 99.9 (14.5) Page 4 of 7 All statements, technical information and recommendations contained in this data sheet are given in good faith and are based on tests believed to be reliable, but their accuracy and completeness are not guaranteed. They do not constitute an offer to any person and shall not be deemed to form the basis of any subsequent contract, nor to constitute any warranty or representation as to quality, merchantability or fitness for purpose. All products are sold subject to the seller s Standard Terms and conditions of Sale. Accordingly, the user shall determine the suitability of the products for their intended use prior to purchase and shall assume all risk and liability in connection therewith. It is the responsibility of those wishing to sell items made from or embodying the products to inform the user of the properties of the products and the purposes for which they may be suitable, together with all precautionary measures required in handling those products. The information contained herein is under constant review and liable to be modified from time to time. Copyright 2009 All rights reserved worldwide. All trademarks or registered trademarks are the property of their respective owners. Material Details: MTM46/CF % RW FT300(3k) -199gsm 2 x 2 Twill Carbon Prepreg 1 hour at 120 C (250 F), 6bar (90psi) autoclave pressure Cure Details No post-cure Zero bleed process achieving 49% fibre volume Test Conditions for Data Property Test 20 C (68F ) +71 C +82 C Method Dry (160 F) Wet (180 F) Wet Tensile Modulus D 3039 GPa (msi) 55.8 (8.1) Compressive Modulus D 3410 GPa (msi) 53.3 (7.8) Trans. Tensile Modulus D 3039 GPa (msi) 56.4 (8.2) Trans. Comp. Modulus D 3410 GPa (msi) 51.9 (7.5) Tensile Strength D 3039 MPa (ksi) 497 (72) Compressive Strength D 3410 MPa (ksi) 698 (101.2) Trans. Tensile Strength D 3039 MPa (ksi) 513 (74.4) Trans. Comp. Strength D 3410 MPa (ksi) 706 (102.4) 567 (82.2) 529 (76.7) Tensile Strain to Failure D 3039 % 0.90 Comp. Strain to Failure D 3410 % 1.30 Trans. Tensile Strain D 3039 % 0.92 Trans. Comp. Strain D 3410 % 1.37 In-Plane Shear Modulus D 3518 GPa (msi) 3.51 (0.5) 3.25 (0.47) In-Plane Shear Strength D 3518 MPa (ksi) (16.4) 87.3 (12.6) Maj. Tensile Poissons Ratio D Maj. Comp. Poissons Ratio D Min. Tensile Poissons Ratio D Min. Comp Poissons Ratio D Flexural Modulus CRAG 200 GPa (msi) Flexural Strength CRAG 200 MPa (ksi) ILSS (WARP) D 2344 MPa (ksi) 71.8 (10.4) 54.4 (7.9) 49.1 (7.1) Page 5 of 7 Material Details: MTM46/GF % RW Eglass-300gsm-8HS (7781 style) epoxy silane finish 1 hour at 120 C (250 F), 6bar (90psi) autoclave pressure Cure Details: No post-cure Zero bleed process achieving 44% fibre volume Test Conditions for Data Property Test 20 C (68F ) +71 C +82 C (180 F) Method Dry (160 F) Wet Wet Tensile Modulus D 3039 GPa (msi) 23.5 (3.4) Compressive Modulus D 3410 GPa (msi) 24.5 (3.5) Trans. Tensile Modulus D 3039 GPa (msi) 22.1 (3.2) Trans. Comp. Modulus D 3410 GPa (msi) 23.9 (2.5) Tensile Strength D 3039 MPa (ksi) 425 (61.6) Compressive Strength D 3410 MPa (ksi) 545 (79) Trans. Tensile Strength D 3039 MPa (ksi) 335 (48.6) Trans. Comp. Strength D 3410 MPa (ksi) 369 (53.5) 254 (36.8) 235 (34) Tensile Strain to Failure D 3039 % 1.81 Comp. Strain to Failure D 3410 % 2.27 Trans. Tensile Strain D 3039 % 1.52 Trans. Comp. Strain D 3410 % 1.59 In-Plane Shear Modulus D 3518 GPa (msi) 4.39 (0.64) 2.92 (0.42) In-Plane Shear Strength D 3518 MPa (ksi) (16.3) 68.4 (9.9) Maj. Tensile Poissons Ratio D Maj. Comp. Poissons Ratio D Min. Tensile Poissons Ratio D Min. Comp Poissons Ratio D Flexural Modulus CRAG 200 GPa (msi) Flexural Strength CRAG 200 MPa (ksi) ILSS (WARP) D 2344 MPa (ksi) 72.9 (10.6) 39 (5.6) 35.2 (5.1) Availability MTM46 prepreg is available on a wide variety of reinforcing fabrics and unidirectional tapes. Not all prepreg formats and reinforcement combinations are suitable for oven/vacuum bag curing. For full recommendations on the optimum material format to suit a particular application and process condition, please contact Advanced Composites Group technical support staff. For vacuum bag processing, it is recommended that E-Glass, S2 Glass and Quartz prepregs, and tightly-woven carbon fabrics are used in their partially-impregnated formats. This ensures minimum laminate porosity by facilitating air removal. Out Life and Storage Storage at -18 C (0 F) Out Life at 21 C (70 F) 12 months 60 days MTM46 should be stored in a freezer at all times. On removal from the freezer, the roll should be allowed to thaw before the polyethylene bag is opened. A full 20 linear metre roll, taken from -18 C (0 F) storage will take between 4 and 6 hours to reach room temperature (21 C [70 F]). If material is Page 6 of 7 All statements, technical information and recommendations contained in this data sheet are given in good faith and are based on tests believed to be reliable, but their accuracy and completeness are not guaranteed. They do not constitute an offer to any person and shall not be deemed to form the basis of any subsequent contract, nor to constitute any warranty or representation as to quality, merchantability or fitness for purpose. All products are sold subject to the seller s Standard Terms and conditions of Sale. Accordingly, the user shall determine the suitability of the products for their intended use prior to purchase and shall assume all risk and liability in connection therewith. It is the responsibility of those wishing to sell items made from or embodying the products to inform the user of the properties of the products and the purposes for which they may be suitable, together with all precautionary measures required in handling those products. The information contained herein is under constant review and liable to be modified from time to time. Copyright 2009 All rights reserved worldwide. All trademarks or registered trademarks are the property of their respective owners. not allowed to full thaw prior to use, condensation may form on the surface, thereby presenting a condition that can be detrimental to the final laminate properties. When materials are returned to the freezer they must be resealed to prevent the ingress of moisture. Health and Safety MTM46 contains an epoxy resin which can cause allergic reaction on prolonged or repeated skin contact. Gloves and protective clothing must be worn. Wash skin thoroughly with soap and water or resin-removing cream after handling. Do not use solvents for cleaning the skin. Use mechanical exhaust ventilation when heat curing the resin system. For further information consult ACG (Material) Safety Data Sheet: (M)SDS 436 Page 7 of 7
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