Impact of Thermal Cycling on Carbon Fiber Reinforced Glass Epoxy Laminates PDF Download
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Author: L Subhadra Burugula
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages :
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Book Description
Wind Turbine blade icing is a serious problem in cold climates, which leads to production losses, failure of the blade, ice throw etc. To eliminate production downtime associated with icing of wind turbine blades, a structurally integrated, carbon fiber based wind turbine blade heating system has been proposed. The de-icing of the blades, where the carbon fiber element is heated which results in a temperature gradient across the blade which may compromise the structural properties of the material. This is explained by the uneven thermal expansion of the different components in the composite (blade) material. Due to the micro-cracking in the composite material it leads to deterioration of the material which further leads to failure. There is a need to investigate the effects of thermal cycling on the structural properties of the composite material. The two main parts of this thesis include the thermal cycling of the CF reinforced glass epoxy laminate samples and Flexural testing on the thermal cycled samples. Thermal cycling is performed on CF reinforced glass epoxy laminate samples with a range of -18 °C to 4 °C with a hold time of 10 minutes for each heating/cooling cycle. A set of 6 samples were taken for each thermal cycle and ran 0, 50, 100, 200 thermal cycles. Temperatures of the samples were recorded using the computer program as well as pictures were taken using a thermal camera; from this data it shows that there is a considerable temperature difference between the carbon fiber and side thermocouples. To study the effects of this temperature gradient on the flexural properties of the laminate, on all the samples three point bending tests (following ASTM standards) are performed and examined for any change in the properties with the increase in the number of thermal cycles. Test results showed that there is very little decrease in the ultimate stress when numbers of thermal cycles were increased from 0 to 200; this decrease is not significant to affect or degrade the material properties of the sample. There might be an effect on material properties when thermal cycling is done in higher levels with more thermal cycling temperature range.
Author: L Subhadra Burugula
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages :
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Book Description
Wind Turbine blade icing is a serious problem in cold climates, which leads to production losses, failure of the blade, ice throw etc. To eliminate production downtime associated with icing of wind turbine blades, a structurally integrated, carbon fiber based wind turbine blade heating system has been proposed. The de-icing of the blades, where the carbon fiber element is heated which results in a temperature gradient across the blade which may compromise the structural properties of the material. This is explained by the uneven thermal expansion of the different components in the composite (blade) material. Due to the micro-cracking in the composite material it leads to deterioration of the material which further leads to failure. There is a need to investigate the effects of thermal cycling on the structural properties of the composite material. The two main parts of this thesis include the thermal cycling of the CF reinforced glass epoxy laminate samples and Flexural testing on the thermal cycled samples. Thermal cycling is performed on CF reinforced glass epoxy laminate samples with a range of -18 °C to 4 °C with a hold time of 10 minutes for each heating/cooling cycle. A set of 6 samples were taken for each thermal cycle and ran 0, 50, 100, 200 thermal cycles. Temperatures of the samples were recorded using the computer program as well as pictures were taken using a thermal camera; from this data it shows that there is a considerable temperature difference between the carbon fiber and side thermocouples. To study the effects of this temperature gradient on the flexural properties of the laminate, on all the samples three point bending tests (following ASTM standards) are performed and examined for any change in the properties with the increase in the number of thermal cycles. Test results showed that there is very little decrease in the ultimate stress when numbers of thermal cycles were increased from 0 to 200; this decrease is not significant to affect or degrade the material properties of the sample. There might be an effect on material properties when thermal cycling is done in higher levels with more thermal cycling temperature range.
Author: Brian J. Knouff
Publisher:
ISBN:
Category :
Languages : en
Pages : 238
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Book Description
Author: Mitch Alan Okeson
Publisher:
ISBN:
Category : Composite materials
Languages : en
Pages : 198
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Book Description
Author: Ad Vlot
Publisher: Springer Science & Business Media
ISBN: 030648398X
Category : Technology & Engineering
Languages : en
Pages : 224
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Book Description
Glare is the name given to a new material for aircraft structures developed at Delft University in the Netherlands. It consists of thin aluminium layers bonded together by adhesive containing embedded fibres and is very resistant to fatigue. This book gives the inside story of how the development of Glare took place. It took more than two decades from the first tests in Delft to the major breakthrough following the decision of Airbus to apply the material on the A380 super-jumbo. This success was achieved by a small group of people inspired by professor Boud Vogelesang, people who kept believing in the material and fought against all obstacles during the years. This book tells the story of the ups and downs and the final success of their efforts.
Author: I.H. Marshall
Publisher: Springer
ISBN:
Category : Technology & Engineering
Languages : en
Pages : 872
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Book Description
The papers contained herein were presented at the Sixth International Conference on Composite Structures (ICCS/6) held at Paisley College, Scotland in September 1991. The Conference was organised and sponsored by Paisley College. It was co-sponsored by Scottish Enterprise, the National Engineering Laboratory, the US Army Research, Development and Standardisation Group-UK, Strathclyde Regional Council and Renfrew District Council. It forms a natural and ongoing progression from the highly successful ICCS/1/2/3/4 and 5 held at Paisley in 1981, 1983, 1985, 1987 and 1989 respectively. As we enter the final decade of this century many organisations throughout the world are adopting a prophetic role by attempting to forecast future scientific advances and their associated impact on mankind. Although some would argue that to do so is folly, without such futuristic visionaries the world would be that much poorer. IntelJigent speculation based on research trends and historical advances, rather than fanciful theories, breathes a healthy air of enthusiasm into the scientific community. Surely this is the very oxygen necessary to ignite the fir~s of innovation and invention amongst pioneers of research.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702
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Author: Gordon H. Stevens
Publisher:
ISBN:
Category :
Languages : en
Pages : 11
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The paper presents the modulus of elasticity and strength values of four reinforced plastic laminates in tension and compression at room temperature and at 500F. Prior to evaluation at these temperatures, the test specimens were exposed to thermal-shock cycling. Three of the laminates evaluated in this study were reinforced with 181-A1100 glass fabric and represented three resin systems: a phenolic resin (CTL 37-9X), an epoxy resin (ERSB-0111), and a phenyl-silane (Narmco 534). The fourth was a phenolic-asbestos laminate made of R/M Pyrotex felt style 41-RPD. The effects of thermalshock cycling on properties vary with the type of resin and reinforcement. In general, thermal-shock cycling had less effect on modulus of elasticity than on strength. Properties at room temperature tended to decrease after exposure to cycling, while the properties of most laminates evaluated at 500F. were not seriously affected. (Author).
Author: Soheila Mahdavi
Publisher:
ISBN:
Category :
Languages : en
Pages : 95
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Book Description
Carbon fiber reinforced polymer composites have been widely used in space industries for manufacturing of spacecraft structures, satellite‐panels and antennas. Composite materials in space undergo harsh environmental conditions. One of the most environmental effects during the life of a satellite antenna is thermal cycling during which the composite endures a large temperature difference between −196°C and +180°C, depending on operational condition. On the other hand, composite structures for space applications are often cured in an autoclave to achieve the required space grade quality which is limited and expensive. Therefore, fabrication of large structures using out‐of‐autoclave (OOA) with the same performance as autoclave with lower costs is of interest of many industries. Composite parts cured inside an oven have higher void content than the ones cured in the autoclave. This thesis aims to study the effect of thermal cycling on the mechanical and thermal properties of flat laminates made of unidirectional (UD) and woven fabric OOA materials as well as a sandwich panel. A toughened epoxy prepreg reinforced by carbon fibers was used to manufacture flat laminates by the hand layup and cured inside the oven. Coupon samples were cut and subjected to different number of thermal cycles (30, 60, 100, 150, 200, 350) by dipping into the liquid nitrogen (−196°C) and then transferring to the oven (+140°C). Afterwards, different material properties were measured including: interlaminar shear strength (ILSS) in three-point bending, viscoelastic properties (loss and storage modulus and tan e) and glass transition temperature (Tg) in DMA, and coefficient of thermal expansion (CTE) in TMA. Besides, optical microscope was utilized to identify damages within the resin. It was identified that the thermal cycling can affect the examined properties by two competing factors: (i) excessive cross-linking in polymer chain due to post-curing at high temperature; (ii) micro-cracks formation due to the induced thermal stresses as a result of matrix/fiber CTE mismatch. It was found that the thermal cycling can cause microcrack formation and propagation around the voids in the laminate and affect its properties.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Book Description
Author: J. P. Komorowski
Publisher: National Research Council Canada = Conseil national de recherches Canada
ISBN:
Category : Aeronautics
Languages : en
Pages : 72
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Book Description
