This is an open access article under the CC BY license: Al-Khwarizmi Engineering Journal Al-Khwarizmi Engineering Journal, Vol. 19, No. 1, March, (2023) P. P. 24- 35 Mechanical PropertiesInvestigation of Unidirectional Woven Carbon Fiber Reinforced Epoxy Matrix Composite Naznaz Jalal Awla* Younis Khalid Khdir** *,**Department of Mechanic and Energy Engineering/ College of Technical Engineering/ Erbil Polytechnic University/ Erbil, Kurdistan Region/ Iraq *Email: naznazshekhbzeny@yahoo.com **Email: younis.khdir@epu.edu.iq (Received 21 August 2022; accepted 12 December 2022) https://doi.org/10.22153/kej.2023.12.001 Abstract In this study, the mechanical properties of an epoxy and unidirectional woven carbon with fiberglass composite were experimentally investigated. When preparing the composite samples, American Society for Testing and Materials (ASTM)standard was used. Tensile, impact and flexural test were conducted to investigate the mechanical properties of the new produced epoxy Unidirectional Woven Carbon and Epoxy Fiberglass composites. The outcome showed that the strength of the produced samples increased with the increase in the number of unidirectional woven carbon layers added. Two methods were utilized: (1) woven carbon composite with glass fiber (2) woven carbon composite). The two methods of composite were compared with each other. The results explained that woven carbon composite had higher mechanical resistance. While in impact test the toughness of the sample increased with adding layers of mixture of Fiber glass with unidirectional woven carbon and epoxy. Keywords: UDWC, Epoxy, Fiber glass, Composite material, Mechanical properties. 1. Introduction Basic composite materials consists of two specific planned materials. The primary benefit of composite materials is that the cost of this kind of materials is low .Production of fabric and covered metal instruments heavily relies on various composites [1]. Polymer composite materials are the lightest and have the higher young’s modulus comparing with simple structure, even in some cases, the delamination reduces the mechanical properties of the known fiber reinforced compounds[2]. The latest wide-body twin-engine passenger aircraft now increasingly depend on composite materials, while smaller narrow-bodies (e.g. the Bombardier C Series/Airbus A220) are gaining traction. During the production of machine elements, drilling is still necessary for the assembly of sub-sections in the manufacturing of composite aircrafts utilizing mechanical fasteners [3].Carbon fiber composites are commonly used. That is due to simplicity of fabrication (even for components with complex shapes) and ease of orientation. The simplicity of fabrication and orientation allows designers to orient stiffness an d strength in desired directions. Due to these factors, woven fiber composites are often less expensive than other types of composites[4]. For the process of fabricating composite from epoxy resin with fibers, several manufacturing techniques are available. Manufacturing techniques such as: manual lay-up technique, distillation, pultrusion filament winding, vacuum bag forming, and resin transfer molding. The hand lay-up technique is preferred for this work, because this technique is simple and powerful[5]. Woven fabric composites have advantages mailto:naznazshekhbzeny@yahoo.com mailto:younis.khdir@epu.edu.iq https://doi.org/10.22153/kej.2023.12.001 Naznaz Jalal Awla Al-Khwarizmi Engineering Journal, Vol. 19, No. 1, P.P. 24- 35 (2023) 25 such as good integration, compatibility and balanced properties in the fabric plane. Although layers of glass woven fabric are preferred in practice, additional layers are required to achieve the desired design strength. This happens in a larger nominal size, which increases the weight of the component/structure. Also, the additional layers make the structure commonly known in structural applications e.g. vehicles, aircraft, yachts, and civil structures [6]. Bhargav, et, al., (2021) prepared a composite by epoxy in addition with hardner, jute fiber (0/90 oriented) with 760 GSM and titanium dioxide TiO2 filler particles [7]also woven jute mat, Araldite LY556 epoxy resin and HY951 hardener based on Triethylenetetramine Ltd (TETA) by using hand lay-up technique and this method was adopted by 10:1 epoxy for curing. For an ASTM D3039-79 they performed tensile testing on a UTM with a dumbbell-shaped specimen and a crossover speed of 2 mm/min. For ASTM D790 bend test was adopted with 1.5mm/min. S2-glass-woven/reinforced epoxy, woven IM7-graphite/reinforced epoxy, and woven S2-glass-IM7-graphite fiber/epoxy were used for researching purposes by [8]. Vacuum Assisted Resin Transfer Molding (VARTM) technology was used to stack plain-woven fill- warp fabrics together and the composite was manufactured and designed by EDO Fiber Innovations into (101.6 x 101.6) mm sheets, the specimens were cured at 177 °C. A 0.3 mm thickness E-glass fabrics as reinforcement was used by [9] and epoxy with its hardener R101 and H101 as a matrix was used respectively. A rectangular volume was produced for conducting tensile tests using ASTM D638 (165x19x4mm) and ASTM D790 (130x12x4mm) for conducting flexural testing. That is to optimize the glass fibers weight fractions. The epoxy resin type (WSR618) as the matrix was used by [10] with benzene dimethylamine as the resin-curing agent and butyl phthalate as the hardener. The layer-by- layer manual stacking process using room temperature vacuum technology and negative pressure curing was used to prevent delamination and cracks between layers. E-glass and carbon fibers were used as reinforcements and epoxy as matrix material by [11]. Epoxy resin and Tri Ethylene Tetra Amine (TETA) hardener were supplied by Atul Ltd. The production of composites Glass/Carbon fiber/Epoxy based hybrid composites were made by using vacuum bag process trough changing both the reinforcements in terms of weight percentage of 15%, 30%, 45% and 60% fiberglass and carbon fiber in 40% epoxy matrix. The study outcome showed that the mechanical properties of carbon fibers were improved as the fibers reinforcement content increased in the matrix material. [12]used Twill -glass fiber, aramid twill fiber, monocoque carbon fiber, unidirectional glass and unidirectional carbon fiber. An epoxy resin (MGS L285) was mixed with a solid (HGS L285) in a volume ratio of 50/100. The compound was made by a manual laying process. The composites were cured at 75°C in an oven after curing at room temperature for 24 h. The steel plates were stacked on the edges of some samples to prevent breakage. The carbon fiber reinforced epoxy compound had better performance than the glass fiber reinforced epoxy compound. That is due to the unidirectional fibers reinforcing the epoxy composite. Bhargav and Babu, 2021 produced LY556 and HY591 epoxy resin matrix [7], 0.4mm thick bidirectional jute fiber reinforced and S- glass fiber in weaving. The fabricating technique was applied by hand. ASTM-D3039 standard was used for tensile test. For impact test, Izod was conducted according to ASTM- D256 standard and three-point bend test according to ASTM-D790 standard the sample size (80X8X3) mm. The results of this research explained that high strength, toughness and stiffness with the combination of two different levels of fibers play a critical role in automotive and some aerospace application components. In this study, composite materials which consists of epoxy, Unidirectional woven carbon and fiber glass are produced by using hand-lay-up technique. Also, the mechanical properties are determined by testing the specimens. Tests are Tensile, Impact and Flexural. 2. Experimental Study 2.1 Materials In this study, the mechanical properties of carbon/fiberglass unidirectional woven epoxy are experimentally investigated. The Naznaz Jalal Awla Al-Khwarizmi Engineering Journal, Vol. 19, No. 1, P.P. 24- 35 (2023) 26 characteristics of each material used are found. 2.1.1 Epoxy In this investigation for preparation of the specimens, a type of "Master Protect 180"epoxy is used (a high build epoxy resin). This type of epoxy consists of two-component part A is as base and part B is as hardener. Mixing the two components is very critical by a thin stick for 2-3 minute. Table 1 shows the main characteristics of this epoxy resin. Table 1, chemical and physical properties of Master Protect180 epoxy Parameter Epoxy Unit Mixing ratio 3:1 % Mixing density 1:5 g/cm3 Initial cure 24 at 25 Hours at℃ Final curing 7 at 25 days at℃ Working life 40 Minute 2.1.2. Unidirectional woven carbon (UDWC) SikaWrap-230 C is a unidirectional woven carbon (UDWC) fiber fabric with mid-range strengths is used. SikaWrap-230 C is designed for installation using the dry application process. See Table 2 for more information about this type of carbon and Figure 1(a). Table 2, Mechanical and physical properties of unidirectional woven carbon parameter UDWC Unit Fiber density 1.82 g/cm3 Filament diameter 21-22 μm Tensile strength(MPa) 4 GPa Tensile modulus (MPa) 230 GPa Faber orientation 0 rad Limit temperature 5-35 ℃ (a) (b) Fig. 1. (a) Unidirectional carbon fiber (b) Fiber glass. 2.1.3. Fiber glass 360 Direct Roving is a saline compatible with unsaturated polyester, vinyl ester and epoxy resin. 360 Direct Roving is designed for wire wrap, drip, and weave applications. 360 Direct Roving is suitable for use in pipes, pressure vessels, grates, profiles and roving woven diverters. Also, 360 Direct Roving is used in boats and chemical storage tanks. See Table 3 and Figure 1(b). Table 3, mechanical and physical properties of fiber glass. Parameter Fiber glass Unit Density 2.62 g/cm3 Filament diameter 21-22 μm Tensile strength 2673 MPa Tensile modulus 81126 MPa Shear strength 70 MPa Limit temperature 15-35 ℃ 2.2. Fabrication of composite layers Molds are needed. Molds are built by 3mm thickness plate has an internal rectangular hole 200mm by 100mm see Figure 2. For each test AutoCad2023is used for the purpose of designing the specimen with different standards, see figure3. A Computer Numerical Control (CNC) machine is employed for cutting the prepared composite specimens. To know the amount needed of epoxy, the mold is filled with epoxy and the percentage of the UDWC with fiber glass are calculated . For Tensile Sample Volume = Area x thickness …(1) V=2509 x 3 = 7.527 cm 3 Wight of sample = Density of epoxy x Volume …(2) =1.5 x 7.527 =11.2905 gm Volume= 11.2905 1.5 = 7.527 cm 3 5% of UDWC = 0.3763cm 3 10% of UDWC = 0.7527 cm 3 15% of UDWC = 1.1290cm 3 3% of UDWC +3% OF FIBER GLASS = 0.2258 + 0.2258 = 0.4516cm 3 1.5% of UDWC = 0.1129cm 3 Naznaz Jalal Awla Al-Khwarizmi Engineering Journal, Vol. 19, No. 1, P.P. 24- 35 (2023) 27 Impact Sample Volume =16.10 x 0.3=4.83 cm 2 Wight of sample = 1.5 x 4.83 = 7.245 gm Volume= 4.83 cm 3 5% of UDWC = 0.2415 cm 3 10% of UDWC = 0.483 cm 3 15% of UDWC = 0.7245 cm 3 3% of UDWC +3% OF FIBER GLASS = 0.1449 + 0.1449 = 0.2898 cm 3 1.5 % of UDWC = 0.0725 cm 3 Flexural Sample Volume=16.51 x 0.3=4.953cm 2 Wight of sample =1.5 x 4.953 =7.2495gm Volume = 4.833 cm 3 5% of UDWC = 0.2416 cm 3 10% of UDWC= 0.4833 cm 3 15% of UDWC= 0.7249 cm 3 3% of UDWC +3% OF FIBER GLASS = 0.14499 + 0.14499 = 0.2899 cm 3 1.5 % of UDWC = 0.0724 cm 3 Fig. 2. The plate mold. (a) (b) (c) Fig. 3 AutoCAD drawing a) tensile test sample b) impact test sample c) flexural test sample Note, all dimensions are in mm. Naznaz Jalal Awla Al-Khwarizmi Engineering Journal, Vol. 19, No. 1, P.P. 24- 35 (2023) 28 Hand lay-up technique is used, layer by layer, for fabricating the new proposed composite materials (epoxy UDWC and fiber glass)in each sample a different layer from the others is conducted. The first step to start conducting compound material is to prepare the mold, by using on backside a limpid paper and adopting a stick for all sides. Then in the second step the front of the mold is cased inside for ease emerging. Later on sticks is used for adopting, while in the third step, a layer of epoxy resin is used. After that in the fourth step the second layer which is unidirectional woven carbon is used. These steps are picked out in figure4. These steps are repeated for each composite specimen to produce all the specimens with the same components. One time for each percentage. That is because all the samples are from the same plate. a. First step b. Second step. c. Third step d. Fourth step Fig. 4 steps of fabricating composite materials. For the purpose of investigating mechanical properties of samples, three mechanical tests are conducted . The tests are: (1) tensile test (2) impact test (3) flexural test. In the next section the details of the mechanical investigations are explained in details. 3. Mechanical Tests and Results The specimen is labeled. For the mechanical tests, three group of specimens are prepared. Group (A1-0, A1-1, A1-2, A1-3, A1- 4, A1-5, and A1-6) for tensile tests, group (B1- 0, B1-1, B1-2, B1-3, B1-4, B1-5, and B2-6) for impact tests and group (C1-0, C1-1, C1-2, C1- 3, C1-4, C1-5, and C1-6) for flexural tests, as indicated in Table 4. Naznaz Jalal Awla Al-Khwarizmi Engineering Journal, Vol. 19, No. 1, P.P. 24- 35 (2023) 29 Table 4, Labeling each specimen for the mechanical tests Code of composite Carbon % Fiber glass % Layers of composite A1-0, B1-0, C1-0 0 0 Epoxy A1-1, B1-1, C1-1 5 0 Ep*-C**-Ep A1-2, B1-2, C1-2 10 0 Ep-C-Ep-C-Ep A1-3, B1-3, C1-3 15 0 Ep-C-Ep-Ep-C-Ep A1-4, B1-4, C1-4 3 3 Ep-C-Ep-F.g***-Ep A1-5, B1-5, C1-5 3 1.5 Ep-C-Ep-F.g-Ep A1-6, B1-6, C1-6 1.5 3 Ep-C-Ep-F.g-Ep Noting that * Ep refers of Epoxy, ** C refers to Carbon, *** F.g refers to Fiber glass 3.1. Tensile test In this test, ASTM D638 standard is utilized. A machine type of XHC-50 ring stiffness tester is employed to test samples. The machine has a software that shows all details about the test. The cross head is 5mm/min, worked with a 100KN load cell with advanced load control. Figure 5 shows two samples before testing. Fig. 5. Specimens tested in tensile. 3.2 Impact test In this test, ASTM D256 is used see figure 6. A machine XJJD-50Seriesis used to conduct impact test. Charpy impact test is conducted for both metal and plastic. In summary, the details of load and energy are determined. Fig. 6. Samples tested in impact. 3.3 Flexural test This test is done by XWW-5KN by software all details are known using ASTM D790 see Figure7. The value of the bending units is determined. Seven samples are generated to perform this test and the average quality is calculated; the speed of the crosshead used is 5 mm/min with an extension length of 80 mm. Naznaz Jalal Awla Al-Khwarizmi Engineering Journal, Vol. 19, No. 1, P.P. 24- 35 (2023) 30 Fig. 7. Samples tested in flexural. 4. Results and discussion 4.1. Tensile test As shown in Table 5 and the results of the samples for the tensile test are illustrated in figure8, the highest value of ultimate tensile stress is (168 MPa). That is reached in sample A1-4, which contains a mixture of fiberglass and UDWC. On the other hand, adding mor e layers of UDWC to the sample, the tensile strength also increases. This indicates that the difference in stacking sequence has little effect on the tensile strength. In addition, the table shows the modulus of elasticity for each sample and the highest one is A1-4 which contains tertiary epoxy, UDWC and fiberglass. This is another indication that shows that the rigid bond between this triple mixture is very high that leads to have the highest modulus of elasticity. Figure8 shows the relation between stress and strain, and figure 9 shows samples after testing. From[13] Modulus of elasticity can be found as bellow: ϭmax=Pmax/(Cross section area) …(3) where: ϭ = tensile stress, MPa Pmax = maximum load prior to failure, N A = average cross-sectional area, m 2 Є =∆L/L …(4) Where; Є = strain, unit less ∆L = change in length (mm) L = original length (mm) Young’s Modulus od elasticity (E) = σ/ Є …(5) Where E is in MPa. Modulus of elasticity will be found by equation 5, all parameters are known from equation 3& 4 subsequently. Table 5, Tensile test results Composite Code Load (N) Stress (MPa) Strain (mm) Elongation (%) E (MPa) A1-0 415 10.05 18.02 7.5 0.55 A1-1 3460 74 5.8 0.83 12 A1-2 4260 107 13 1.23 8.2 A1-3 4620 121 23 1.18 5.2 A1-4 7670 168 5 11.77 33 A1-5 1130 23 3.8 9.6 6.05 A1-6 1380 32 2.9 7.89 11.03 Fig. 8. Stress-Strain curves for experimental tensile tests of (A1-0, A1-1, A1-2, A1-3, A1-4, A1-5, and A1-6) 0 25 50 75 100 125 150 175 0 2 4 6 8 10 12 14 16 18 20 22 St re ss ( M P a ) Strain Є A1-0 A1-1 A1-2 A1-3 A1-4 A1-5 A1-6 Naznaz Jalal Awla Al-Khwarizmi Engineering Journal, Vol. 19, No. 1, P.P. 24- 35 (2023) 31 Fig. 9. Sample tested in tensile results. 4.2. Impact test results Table 6 shows the impact testing results of unidirectional woven carbon fiber reinforced epoxy composites, as well as the fiber glass strength. As its seen from the tables the layers of UDWC increases the kinematic energy inside the composite samples increases too because of the rigid bond between the epoxy and UDWC fibers, samples after testing as shown in figure 10, and the results are shown in the Figure 11. The most extreme impact strength is 6.387 j because of having he most layer on it and having the highest toughness compared to others and surely because of having UDWC, that gives more ductility to the sample, and the fracture area is less. Moreover, both samples B1-2 and B1-4 gives approximately the results of strength. The results show that even adding a layer of fiber glass, can improve the toughness about 3% of the sample. This is a point that can be noted which has a good effect for increasing the toughness of the sample by this small range of fiber glass layers. Table 6, Impact testing results of unidirectional woven carbon fiber reinforced epoxy composites Composite Code Energy (Joule) B1-0 0.103 B1-1 1.488 B1-2 2.757 B1-3 6.387 B1-4 2.059 B1-5 1.578 B1-6 0.867 Fig. 10. Impact testing samples. Naznaz Jalal Awla Al-Khwarizmi Engineering Journal, Vol. 19, No. 1, P.P. 24- 35 (2023) 32 Fig. 11. Impact toughness for (B1-0, B1-1, B1-2, B1-3, B1-4, B1-5, and B1-6). 4.3 Flexural test results The variance of the flexural strength with the percentage of UDWC and fiberglass is shown in Table 7. The flexure stress increased by this additional percentage, as well as the maximum (100 MPa) in the load (207 N) containing three layers of UDWC. The flexural behavior of the composite was increased by the interfacial bond between the UDWC and the matrix. And the combination of fiberglass and UDWC has an intermediate value of results which is (135N) with (65MPa). Also, about modulus of flexure sample C1-1 Has the highest value the reason is the bond of rigid strength between UDWC and the epoxy resin. Fig. 12. Samples tested in flexural From [13] flexural modulus will be found by: EF = 𝐿3 𝑚 4 𝑏ℎ3 (6) Were; Ef = Flexural modulus (MPa), L = Span length (mm) b = Width of the sample (mm) h = Thickness of the sample (mm) m= Slope (N/mm) 0.103 1.488 2.757 6.387 2.059 1.578 0.867 0 1 2 3 4 5 6 7 B1-0 B1-1 B1-2 B1-3 B1-4 B1-5 B1-6 T o u g h n e ss ( J/ m ) Naznaz Jalal Awla Al-Khwarizmi Engineering Journal, Vol. 19, No. 1, P.P. 24- 35 (2023) 33 Table 4, Flexural testing results Composi te Code Load (N) Flexure Stress (MPa) Flexure Strain Flexural Extension Flexural Modulus (MPa) C1-0 43 20.9 0.064 15 32752 C1-1 118 57 0.054 10 349291 C1-2 141 68 0.033 8.3 252285 C1-3 207 100 0.0292 7 192992 C1-4 135 65 0.062 15 112467 C1-5 29.8 27.37 0.07 20.77 627 C1-6 25.0 22.99 0.06 15.89 3520 Fig. 13. Stress-Strain curves for flexures experimental tests of (C1-0, C1-1, C1-2, C1-3, C1-4, C1-5, and C1-6) 4. Conclusion In this study, the mechanical properties of unidirectional woven carbon, fiber glass/ epoxy composite at different rate of layers were studied. The compression between flexural modulus and modulus of elasticity were theoretically found and clearly discussed. The following points can be concluded: 1- Adding more UDWC layers may increase mechanical properties such as tensile stress. 2- Tensile stress of all specimens varied (decreased) when fiber glass was added to the composite specimens, this variation happened in samples A1-4, A1-5 and A1-6 showed the maximum value when 3% UDWC and fiber glass in A1-4 sample when mixed together with epoxy resin. 3- The maximum value of Young’s Modulus of elasticity were achieved within A1-4 specimen the reason is due to multiple layers and having much more composite material on in such as UDWC. 4- From impact test the sample B1-3 has the highest toughness energy, this increase in toughness because more layers of UDWC exists 5- The flexural modulus indicates the tendency of the samples. High value of flexural modulus was found with C1-1 sample in which it has the low weight and it has 10% of UDWC layers inside. 6- The achievement results from the triple mechanical tests shows that as much as the layers of UDWC added, the mechanical properties will be increased. 5. References [1] Callister, W.D. and D.G. Rethwisch, Materials science and engineering: an introduction. Vol. 9. 2018: Wiley New York. [2] 2. Mohanta, N. and S. Acharya, Fiber surface treatment: Its effect on structural, thermal, and mechanical properties of Luffa cylindrica fiber and its composite. Journal of composite materials, 2016. 50(22): p. 3117- 3131. [3] Liu, H., B.G. Falzon, and J.P.J.I.J.o.M.S. Dear, An experimental and numerical study on the crush behaviour of hybrid unidirectional/woven carbon-fibre reinforced 0 20 40 60 80 100 120 0.00 0.02 0.04 0.06 0.08 0.10 0.12 S tr e ss ( M P a ) Strain Є C1-0 C1-1 C1-2 C1-3 C1-4 C1-5 C1-6 Naznaz Jalal Awla Al-Khwarizmi Engineering Journal, Vol. 19, No. 1, P.P. 24- 35 (2023) 34 composite laminates. 2019. 164: p. 105160. [4] Kaka, D., et al. Dynamic mechanical properties of woven carbon fibre reinforced thermoplastic composite. in Proceedings of the 20th International Conference on Composite Materials. 2015. ICCM. [5] Thirumalai, R., et al., Experimental investigation of mechanical properties of epoxy based composites. Materials Research Express, 2019. 6(7): p. 075309. [6] Yoo, S.H., et al., Facile method to fabricate carbon fibers from textile-grade polyacrylonitrile fibers based on electron- beam irradiation and its effect on the subsequent thermal stabilization process. Carbon, 2017. 118: p. 106-113. [7] Bhargav, M. and V.S. Babu, Experimental investigation of fiber orientation effect on mechanical and erosive wear performance of TiO2 filled woven jute fiber based epoxy composites. Materials Today: Proceedings, 2021. 44: p. 2617-2622. [8] Wang, C., et al., Low-velocity impact response of 3D woven hybrid epoxy composites with carbon and heterocyclic aramid fibres. Polymer Testing, 2021. 101: p. 107314. [9] Singh, S. and P. SK Jain, An experimental and numerical investigation of mechanical properties of glass fiber reinforced epoxy composites. Advanced Materials Letters, 2013. 4(7): p. 567-572. [10] Zhou, G., et al., Experimental investigation on mechanical properties of unidirectional and woven fabric glass/epoxy composites under off-axis tensile loading. Polymer Testing, 2017. 58: p. 142-152. [11] Jagannatha, T. and G. Harish, Mechanical properties of carbon/glass fiber reinforced epoxy hybrid polymer composites. International Journal of Mechanical Engineering and Robotics Research, 2015. 4(2): p. 131-137. [12] Ekşı, S. and K. Genel, Comparison of mechanical properties of unidirectional and woven carbon, glass and aramid fiber reinforced epoxy composites. composites, 2017. 132(3): p. 879-882. [13] Hosford, W.F., Mechanical behavior of materials. 2010: Cambridge university press. (2023) 24-35، صفحة 1، العدد19مجلة الخوارزمي الهندسية المجلد نازناز جالل عوال 35 إيبوكسي معززة بألياف الكربون أحادية االتجاهدراسة الخواص الميكانيكية لمركب ر**دنازناز جالل عوال* يونس خالد خ أربيل*،**الكلية التقنية الهندسية/ naznazshekhbzeny@yahoo.com *البريد االلكتروني: younis.khdir@epu.edu.iq**البريد االلكتروني: الخالصة تحضير في هذه الدراسة تم دراسة الخواص الميكانيكية للكربون المنسوج االيبوكسي أحادي االتجاه مع مركب األلياف الزجاجية بشكل تجريبي. عند للتحقق من الخواص واالنحناء(. تم إجراء اختبار الشد والصدمة ASTMيتم استخدام معيار الجمعية األمريكية لالختبار والمواد ) المركبة،العينات اف مركبات اإليبوكسي أحادية االتجاه المنسوجة المصنوعة من الكربون واأللي لواإليبوكسيمع المنسوج أحادي االتجاه الجديد الكربونمنتج للالميكانيكية كب مع بعضهما الزجاجية. لوحظ أن قوة العينات المنتجة تزداد مع زيادة عدد طبقات الكربون المنسوجة أحادية االتجاه المضافة. إذا قارنت طريقتا المر ومة ميكانيكية فقد لوحظ أن مركب الكربون المنسوج يتمتع بمقا (،مركب الكربون المنسوج الزجاجية،البعض )مركب الكربون المنسوج مع األلياف تزداد صالبة العينة مع إضافة طبقات من خليط األلياف الزجاجية مع الكربون المنسوج بالعكس،وبالتالي في اختبار التأثير يكون العكس بكثير،أعلى أحادي االتجاه واإليبوكسي. mailto:naznazshekhbzeny@yahoo.com mailto:younis.khdir@epu.edu.iq Abstract 1. Introduction 2. Experimental Study 2.1 Materials 2.1.1 Epoxy 2.1.2. Unidirectional woven carbon (UDWC) 2.1.3. Fiber glass 2.2. Fabrication of composite layers (a) (b) (c) 3. Mechanical Tests and Results Table 4, Labeling each specimen for the mechanical tests 3.1. Tensile test 3.2 Impact test 4. Results and discussion 4.1. Tensile test Table 5, Tensile test results 5. References