Hi sir, I have got a lab assessment. firstly,I will submit it to you sample one which needs to be read carefully. Afterwards, I will submit the question. Pls let me know if you are accept it. Thanks
School of Engineering/Aerospace Engineering and Aviation May 2019 — AERO2566 Aerospace Materials Report Guide Design, manufacture and mechanical evaluation of fibre-reinforced polymer (FRP) composites Page 2 of 4 Executive summary of the practical assessment This assessment will ensure that you can apply the composites mechanics theory in estimating the mechanical properties of multi-directional fibre-reinforced polymer composite laminates. You are provided with tensile data for a unidirectional carbon fibre/epoxy laminate and you must use this data to estimate the in-plane tensile properties of a cross-ply [0/90/0/90/0] laminate. Upon completion of this assessment, you should: • have acquired hands-on experience in manufacturing fibre-reinforced polymer (FRP) composites from prepreg tape; • demonstrate an understanding of how the tensile properties of FRP composites are experimentally-measured; and, • be able to conduct a comparative analysis of theoretically-estimated and experimentally- measured tensile properties of multi-directional FRP composites. Manufacturing unidirectional composite laminates Unidirectional (UD) composite laminates measuring 300 mm × 300 mm were manufactured using carbon fibre-epoxy tape. Four prepreg plies were stacked upon each other with the fibres aligned in the 0° direction. The composite lay-up was de-bulked to remove any trapped air or gases. The de-bulked composite lay-up was vacuum bagged and autoclave-cured at 120°C for 1 hour under an externally-applied pressure of 90 psi. Tensile test specimens (180 mm × 25 mm) were then cut from the master laminate along varying angles (0°, 22.5°, 45°, 67.5° and 90°) relative to the fibre alignment. Manufacturing multi-directional [0/90/0/90/0] composite laminates Cross-ply (CP) composite laminates measuring 300 mm × 300 mm were manufactured using carbon fibre-epoxy tape. Prepreg plies were stacked upon each other to achieve the desired [0/90/0/90/0] configuration. The composite lay-up was de-bulked to remove any trapped air or gases. The de-bulked composite lay-up was vacuum bagged autoclave-cured at 120°C for 1 hour under an externally-applied pressure of 90 psi. Tensile test specimens (180 mm × 25 mm) were then cut from the master laminate along varying angles (0°, 30°, 45°, 60° and 90°) relative to the fibre alignment. Mechanical evaluation of the UD and CP composite laminates Tensile tests were conducted using the 100 kN MTS testing machine for both the UD and CP laminates. The dimensions (length, width, thickness) of each test coupon were recorded before testing. The specimens were placed in the grips to a depth of 25 mm at each end, leaving a gauge length of 130 mm. The specimens were loaded at a constant cross-head displacement rate of 2 mm/min until failure. Make reference to the ASTM tensile testing standard provided with this document to aid your preparation of the laboratory report. Page 3 of 4 You may consider following the outline below when putting together the laboratory report. However, please note that the information below is not exhaustive; this is just a guide, and the minimum expected. You must include additional analysis and commentary to achieve the maximum possible score for this assessment. 1.0 Table of contents 2.0 Introduction 3.0 Methodology 4.0 Results and discussion (experimental and analytical modelling) 5.0 Conclusions 6.0 References Critical aspects of the report • Plot the stress-strain data for all the loading angles of the UD laminates in one graph. There are three stress-strain curves for each angle, however, select only one representative profile for each loading angle (e.g., your graph must have five curves for angles 0°, 22.5°, 45°, 67.5° and 90°). Label the points or regions that represent the modulus of elasticity, the ultimate failure strength and the strain-at-failure. Label the axes and provide appropriate units. • Determine the ultimate tensile strength, the modulus of elasticity and the strain-at-failure for each loading angle of the UD laminates. Make reference to the Tensile Chord Modulus of Elasticity method in section 13.3.1 (Table 3) of the ASTM standard. Determine the average and standard deviation values using the three data sets for each loading angle. • Plot the ultimate tensile strength and the modulus of elasticity against the loading angle presenting the average values and the standard deviation (e.g. show error bars). Describe the effect of the loading direction on the modulus of elasticity, the ultimate failure strength and the strain-at-failure. Explain why the tensile properties of a UD laminate vary in the way they do as the loading angle is changed from 0° to 90°. • Plot the stress-strain data for all the loading angles of the [0/90/0/90/0] laminates in one graph. There are three stress-strain curves for each angle, however, select only one representative profile for each loading angle (e.g., your graph must have five curves for angles 0°, 30°, 45°, 60° and 90°). Label the axes and provide appropriate units. • Determine the ultimate tensile strength, the modulus of elasticity and the strain-at-failure for each loading angle of the [0/90/0/90/0] laminate. Make reference to the Tensile Chord Modulus of Elasticity method in section 13.3.1 (Table 3) of the ASTM standard. Determine the average and standard deviation values using the three data sets for each loading angle. Page 4 of 4 • Plot the ultimate tensile strength and the modulus of elasticity against the loading angle presenting the average values and the standard deviation (e.g. show error bars). Explain why the tensile properties of a [0/90/0/90/0] laminate vary in the way they do as the loading angle is changed from 0° to 90°. • Exploit the micromechanics or macromechanics modelling equations discussed in class and estimate the theoretical modulus of elasticity of the [0/90/0/90/0] laminate at different loading angles. Remember that you already have the tensile properties measured for the UD laminate at various angles. • Present the theoretical estimates of the modulus of elasticity together with the experimentally-measured data (including error bars) for the [0/90/0/90/0] laminate and comment on the discrepancies. • Add any other relevant information to your report as you see fit. • You must use no more than ten (10) A4-size pages excluding the Coversheet. 0 Experiment A cross-ply [0/90/0/90/0] carbon fabric/epoxy laminate was manufactured by laying five cross-ply prepreg plies. Three of the plies were aligned in the 0° direction and two were aligned in the 90° direction. The cured laminated was loaded in the 100 kN MTS testing machine and subjected to tensile loading in the displacement control (2 mm/min) until failure. The test specimen had a rectangular block geometry and the respective dimensions are given below. The gauge length is the distance between the grips (original length) at the start of the tensile test. The force (N) and extension (mm) data was electronically recorded and is provided below. MaterialPristinePristinePristine Specimen123 Gauge Length (mm)130130130 Thickness (mm)1.9522.07 Width (mm)18.620.3519.29 Failured at the:GripsGripsGrips ExtensionForceExtensionForceExtensionForce (mm)(N)(mm)(N)(mm)(N) 000000 0.015628.635680.015483.910370.016311.73032 0.0343516491270.14890.03226176963.930240.01623854629.72253 0.0664584391883.64930.065176191445.17570.034233178942.47253 0.1002944992529.03030.097446891915.23110.0501453881247.5566 0.1338630893141.13160.132187462403.34960.0671461181563.2368 0.1675493993751.21920.16592222877.66410.0830203281864.0925 0.1997984994342.21970.198785963345.30760.0997438982162.9185 0.2342581794940.71630.232175743809.62960.1172974682472.3643 0.2678312395535.41210.265599794272.86080.1327633882772.0393 0.3008775396118.99170.298043344734.13820.1489758483067.3577 0.3348804996692.83110.331954665189.22270.1672066783370.4402 0.3676734897271.5020.365325815635.19380.1834526683680.2102 0.4009403297845.78470.399707266091.53130.2006694683972.1211 0.4344083398416.2930.43142146544.52440.2176783984267.8955 0.4673510498971.21290.465439266993.21830.2343483284561.418 0.5008630499531.96580.498667367445.20170.2504408384852.2837 0.53388473910084.7230.532527277895.22750.2673305585141.5942 0.56803974910643.0340.565350068345.27250.2832964085422.5601 0.60038640911191.6630.599306838794.01270.3008216585706.1455 0.63466283911735.5330.631621489239.11910.3175273585992.3604 0.66817774912266.1920.666238379679.26460.3345400086286.2358 0.70139243912799.0060.6985813410120.4230.3503188486562.7271 0.73456617913324.0480.7320791510559.0240.3669351386845.144 0.76745447913846.3270.765208910989.2560.3832600987130.1279 0.80093893914365.6620.7995434411443.9880.4004776487410.415 0.83462074914881.3610.8323624811872.6570.4175126587701.6553 0.86766108915388.440.8659623312312.1780.4343048087976.1021 0.90016647915898.1740.8990615912737.8110.4515476488261.582 0.93417914916408.160.9329258913169.920.4677698288540.1182 0.96749814916906.6090.9667514913590.0460.4841275488800.1377 1.00062714917393.10.9995832914013.6250.5000576689080.3301 1.03310864917873.5471.0327338914425.6570.5183704189372.6484 1.06750214918353.0121.0661132914852.4790.5328700289639.792 1.10044704918822.5741.0987519915260.6090.5510941489916.584 1.13453494919303.2421.1325410915661.4590.56689157810189.83 1.16868544919776.8931.1659025916084.1940.58368894810450.61 1.20086154920245.5451.1989667916496.1450.59980526810714.73 1.23451644920703.8731.2326523916911.0510.61648484810987.604 1.26763504921157.9671.2660048917332.9180.63317116811256.865 1.30061584921613.8031.2991577917740.9650.65081342811526.123 1.33491834922057.5351.3327076918147.5960.66743942811795.971 1.36818814922497.4381.3659686918568.1660.68341645812051.297 1.40133124922919.5391.3990029918987.5570.70027562812326.414 1.43436044923334.9941.4335282919371.0610.71775093812586.357 1.46796334923606.4411.4657631919762.020.73363706812844.439 1.467963349200001.4997593920176.1410.75065788813104.781 1.5320152920588.1250.76733383813369.069 1.5664726921006.4690.78378244813627.08 1.5994779921420.1740.79928931813882.3 1.6324557921825.6350.81757977814137.344 1.6657582922233.7480.83355679814402.211 1.6990556922636.8090.84897872814658.116 1.7324395923031.4610.86622389814918.566 1.7661482923431.9080.88466480815172.986 1.76614829200000.90070739815424.413 0.91624709815676.564 0.93373650815938.013 0.95045720816196.377 0.96616370816421.07 0.98371950816693.033 1.00077680816947.244 1.01654300817190.797 1.03319440817437.67 1.05053640817678.84 1.06686350817939.387 1.08363480818179.756 1.09993070818408.561 1.11682710818659.934 1.13327060818907.35 1.15053580819156.83 1.16645620819377.859 1.18264920819627.809 1.20028780819871.771 1.21828090820110.502 1.23322600820347.609 1.24994510820581.869 1.26693700820808.334 1.28357630821032.174 1.29991170821246.957 1.31740130821468.598 1.33417330821691.324 1.35041550821895.633 1.36695270822105.072 1.38377100822288.773 1.38377100820000 30 Experiment A cross-ply [0/90/0/90/0] carbon fabric/epoxy laminate was manufactured by laying five cross-ply prepreg plies. Three of the plies were aligned in the 0° direction and two were aligned in the 90° direction. The cured laminated was loaded in the 100 kN MTS testing machine and subjected to tensile loading in the displacement control (2 mm/min) until failure. The test specimen had a rectangular block geometry and the respective dimensions are given below. The gauge length is the distance between the grips (original length) at the start of the tensile test. The force (N) and extension (mm) data was electronically recorded and is provided below. MaterialPristinePristinePristine Specimen123 Gauge Length (mm)130130130 Thickness (mm)2.112.031