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Добірка наукової літератури з теми "COMPOSITE ROTOR"

Автор: Grafiati

Опубліковано: 11 вересня 2023

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Статті в журналах з теми "COMPOSITE ROTOR"

1

Varatharajoo, Renuganth, Faizal Mustapha, Dayang Laila Abang Abdul Majid, Rizal Zahari, and Ralph Kahle. "Critical Speeds for Carbon/Epoxy Composite Rotors in Spacecraft Energy Storage Applications." Key Engineering Materials 471-472 (February 2011): 37–42. http://dx.doi.org/10.4028/www.scientific.net/kem.471-472.37.

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Анотація:

A numerical investigation to optimize the carbon/epoxy multi layer composite rotor is performed for the spacecraft energy storage application. A high-speed double and triple layer rotor design is proposed and different composite materials are tested to achieve the most suitable recipe. First, analytical rotor evaluation was performed in order to establish a reliable numerical composite rotor model. Subsequently, finite element analysis is employed in order to optimize the double and triple layer composite rotors. Then, the modal analysis was carried out to determine the rotor natural frequencies. The rotor stress distributions and the rotor mode shapes show that a safe operational regime below 46, 000 rotations per minute is achievable.

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2

Wang, Chuan Sheng, De Wei Zhang, and Hui Guang Bian. "Effects of Different Structure Rotors on Mixing Process and Quality of Short Fiber-Rubber Composite Material." Advanced Materials Research 87-88 (December 2009): 277–81. http://dx.doi.org/10.4028/www.scientific.net/amr.87-88.277.

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Анотація:

The structure of rotors is an important factor, which impacts the quality of the mixed rubber. For the short fiber-rubber composite material, the structure of the rotors is most important. Through the experiments study, the mixing performances of four-wing synchronous rotor, six-wing synchronous rotor and new type of six-wing synchronous varying clearance rotor have been studied. The experimental results indicated that the mixing performance of the new type rotor is much better than the four-wing and six-wing synchronous rotor for the mixing of short fiber-rubber composite materials.

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3

Guo, Song Yi, Chong Li, and Wen Yi Li. "Finite Element Analysis of Materials and Processing of Composite Flywheel Rotor." Applied Mechanics and Materials 529 (June 2014): 92–96. http://dx.doi.org/10.4028/www.scientific.net/amm.529.92.

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Анотація:

Flywheel rotor is the very important component in the flywheel energy storage system (FESS). The key factors of rotor, such as rotor materials, geometry and fabrication process, have directly influence on the performance of FESS. At present, press-assembling the rotor with shrink-fit is used usually to increase strength of composite flywheel rotors filament wound in the radial direction. This paper is concerned that the Von Mises equivalent stress distribution of the metal hub and the radial stress distribution of the composite rim at the speed of 20000rpm by the 3D finite element method. The materials and corresponding minimum value of interference fit of the flywheel rotor are determined based on the analysis results.

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4

Draghici, Sorin. "Structural evaluation of a composite centrifugal rotor." Scientific Bulletin of Naval Academy XXIII, no. 1 (July 15, 2020): 29–33. http://dx.doi.org/10.21279/1454-864x-20-i1-004.

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Анотація:

The steady increase in the use of composites has brought benefits in many areas. Polymer Matrix Composite (PMC) is a material consisting polymer (resin) matrix combined with a fibrous reinforcing dispersed phase. Polymer Matrix Composites are very popular due to their low cost and simple fabrication methods. This paper aims to validate thru finite element method the structural integrity of a composite gas turbine rotor and establish its benefits and disadvantages compared to a steel alternative. Composites provide the advantages of lower weight, greater strength and higher stiffness and the advantage of prepreg technology.

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5

Lo, Jason. "Designing a Composite Material for Use in Brake Applications." Materials Science Forum 475-479 (January 2005): 1109–12. http://dx.doi.org/10.4028/www.scientific.net/msf.475-479.1109.

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Traditionally, automotive brake rotors are made with cast iron. Besides having economical advantage, cast iron rotor provides many disadvantages due to its weight, such as reduction in fuel efficiency, increase in green house gas emission, and increase in noise, vibration and hardness. With the development of commercial aluminum composites, composite brake rotors are now manufactured. However, the present commercial composite materials are not specifically made for brake application and there are drawbacks. A major drawback is their poor elevated temperature property. In this paper, the unique properties offered by an aluminum composite for brake application is addressed, and an approach to compensate its properties for brake application is highlighted.

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6

Mwanyika, Hegespo H., Yusufu AC Jande, and Thomas Kivevele. "Design and Performance Analysis of Composite Airfoil Wind Turbine Blade." Tanzania Journal of Science 47, no. 5 (December 1, 2021): 1701–15. http://dx.doi.org/10.4314/tjs.v47i5.18.

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Abstract Small horizontal axis wind turbine rotors with composite airfoil rotor blades were designed and investigated in the present study in order to improve its performance in low wind speed and low Reynolds number (Re) conditions for standalone system. The geometrical and aerodynamic nature of a single airfoil small horizontal axis wind turbine blade curtails efficient energy harnessing of the rotor blade. The use of composite airfoil rotor blade improves energy production but imposes uncertainty in determining an optimal design angle of attack and the off design aerodynamic behaviour of the rotor. This research investigated the effects of two airfoils used at different sections in a composite blade and determined the blade’s optimal design angle of attack for maximum power generation. The wind turbine rotor blades were designed using blade element momentum (BEM) method and modelled by SolidWorks software. The SG6042 and SG6043 airfoils were used for the composite airfoil blades. Five wind turbines were designed with rotor blades of design angles of attack from 3° to 7°. The five wind turbine blades were simulated in computational fluid dynamics to determine the optimal design angle of attack. The composite airfoil wind turbine blade showed improved performance, whereas, the wind power generated ranged from 4966 W to 5258 W and rotor power coefficients ranged from 0.443 to 0.457. The blade with design angle of attack of 6° showed highest performance. Keywords: composite airfoil, lift-to-drag ratio, pressure coefficient, Reynolds number, design angle of attack.

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7

Li, Xing, Christian Mittelstedt, and Andreas Binder. "A review of critical issues in the design of lightweight flywheel rotors with composite materials." e & i Elektrotechnik und Informationstechnik 139, no. 2 (March 29, 2022): 204–21. http://dx.doi.org/10.1007/s00502-022-01005-4.

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Анотація:

AbstractComposite materials are widely used to build high-performance flywheels due to their high material strength and low mass density. The high degrees of freedom in material selection, design, and manufacturing techniques lead to a variety of rotor structures. This paper presents the characteristics of different composite rotors and the critical considerations in terms of designing, manufacturing, and testing them. The introduction starts with the limitations of a single filament-wound composite rim. Then, various rotor structures are presented as well as the critical issues regarding the composite rim design, rim-shaft connection, and rotor failure in order to make safe design recommendations. The aim is to summarize the current techniques and provide references for further developments.

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8

Firouz, Fatma, Atef Daoud, and Malak Abou El-Khair. "AlSi-SiC Composites for Automotive Brake Rotor." Key Engineering Materials 835 (March 2020): 178–85. http://dx.doi.org/10.4028/www.scientific.net/kem.835.178.

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Анотація:

This manuscript investigates the Fabrication and Microstructure of Automotive Brake Rotor Made of AlSi-SiC Composites. This work is oriented toward fabrication of automotive brake rotors from Al-9Si and Al-12Si reinforced with 10 and 20% SiC particles using stir-casting method. The brake rotors were subjected to heat treatment. Aging behavior showed that hardness increased with the addition of SiC reinforcements by 104%, comparing to solution treatment condition. Also, the addition of SiC particles accelerates formation of precipitates. Microstructure of brake rotors made of composite revealed uniform distribution of SiC particles, primary phase (⍺-Al) and modified eutectic Si. EDX analysis showed the presence of Al, Mg and O at the interface between matrix and SiC particles.

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9

Yang, J., S. Z. HE, and L. Q. Wang. "Dynamic Balancing of a Centrifuge: Application to a Dual-Rotor System with Very Little Speed Difference." Journal of Vibration and Control 10, no. 7 (July 2004): 1029–40. http://dx.doi.org/10.1177/1077546304035603.

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Анотація:

The conventional way of separating the vibration signals of the inner and outer rotors of a dual-rotor system is to separate the composite "beat" signal; however, this is not effective for a dual-rotor system with little speed difference. We propose a new method of separating the vibration signals of the inner and outer rotors of a system with veiy little speed difference. It is not necessary to separate the composite " beat" signal, as in the conventional method. The magnitude and phase values of the unbalanced weights are obtrined directly by sampling the vibration signal synchronized with a reference signal. The balancing process is completed by the reciprocity influence coefficients of the method of the inner and outer rotors. The results show the advantage of such a method for a dual-rotor system, compared with conventional balancing. The proposed new method has been successfully implemented in field dynamic balancing of the centrifuge with such dual-rotor systems in two rectifying planes with digital signal processing and virtual instrument technology.

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10

Medovar, L., G. Polishko, G. Stovpchenko, V. Kostin, A. Tunik, and A. Sybir. "Electroslag refining with liquid metal for composite rotor manufacturing." Archives of Materials Science and Engineering 2, no. 91 (June 1, 2018): 49–55. http://dx.doi.org/10.5604/01.3001.0012.5489.

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Purpose: To develop novel ESR based process for composite ingot with shallow transition zone between layers in order to produce efficient heavy-weight rotors for steam turbines. Design/methodology/approach: The nowadays heavy-weight rotors for steam turbines for power plants are monoblock or two or more layer in length composite part facilitating operation in different zones withstanding various loads and working medium. However, the joining of various steel in composite rotors by welding has low productivity. The ESR now is recognised as the best available technology for the big-diameter and mass forgings for power generating machines, including rotor ones. The ESR affords the most favourable conditions of solidification resulting in homogenous low-segregation ingot with smooth surface and high-quality structure. The step ahead is the ESR for composite. Findings: The two-layer model ingot had produced from steel grades 12Cr13 and 35NiCrMoV12-5 were manufactured using the electroslag process with the liquid metal (ESR LM) in the CSM of 180 mm in diameter with ingot withdrawing. The transition zone in two-layer ingot had have the shallow shape and low depth with the even macrostructure without defects of the same type as both joined steels. The metal of the transition zone fully satisfies standard requirements for properties of both steel grades in the heat treated and as-cast conditions. Research limitations/implications: The ESR LM can provide both the monobloc heavy ingots with uniform structure and composites with low-stress connection between metal layers for heavyweight rotors and other critical products manufacturing.

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Дисертації з теми "COMPOSITE ROTOR"

1

Soykasap, Omer. "Aeroelastic optimization of a composite tilt rotor." Diss., Georgia Institute of Technology, 1999. http://hdl.handle.net/1853/11823.

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2

Ozbay, Serkan. "Extension-Twist Coupling Optimization in Composite Rotor Blades." Diss., Georgia Institute of Technology, 2005. http://hdl.handle.net/1853/10422.

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Анотація:

For optimal rotor performance in a tiltrotor aircraft the difference in the inflow and the rotor speeds between the hover and cruise flight modes suggests different blade twist and chord distributions. The blade twist rates in current tiltrotor applications are defined based upon a compromise between the figure of merit in hover and propeller efficiency in airplane mode. However, when each operation mode is considered separately the optimum blade distributions are found to be considerably different. Passive blade twist control, which uses the inherent variation in centrifugal forces on a rotor blade to achieve optimum blade twist distributions in each flight mode through the use of extension-twist coupled composite rotor blades, has been considered for performance improvement of tiltrotor aircraft over the last two decades. The challenge for this concept is to achieve the desired twisting deformations in the rotor blade without altering the aeroelastic characteristics of the vehicle. A concept referred to as the sliding mass concept is proposed in this work in order to increase the twist change with rotor speed for a closed-cell composite rotor blade cross-section to practical levels for performance improvement in a tiltrotor aircraft. The concept is based on load path changes for the centrifugal forces by utilizing non-structural masses readily available on a conventional blade, such as the leading edge balancing mass. A multilevel optimization technique based on the simulated annealing method is applied to improve the performance of the XV15 tiltrotor aircraft. A cross-sectional analysis tool, VABS together with a multibody dynamics code, DYMORE are integrated into the optimization process. The optimization results revealed significant improvements in the power requirement in hover while preserving cruise efficiency. It is also shown that about 21% of the improvement is provided through the sliding mass concept pointing to the additional flexibility the concept provides for tailoring of the structure without any additional weight penalty on the system.

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3

Turnock, Wingyan Wong. "Impact response of composite helicopter rotor blades." Thesis, Cranfield University, 2004. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.422188.

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4

Pawar, Prashant M. "Structural Health Monitoring Of Composite Helicopter Rotor Blades." Thesis, Indian Institute of Science, 2006. https://etd.iisc.ac.in/handle/2005/273.

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Анотація:

Helicopter rotor system operates in a highly dynamic and unsteady aerodynamic environment leading to severe vibratory loads on the rotor system. Repeated exposure to these severe loading conditions can induce damage in the composite rotor blade which may lead to a catastrophic failure. Therefore, an interest in the structural health monitoring (SHM) of the composite rotor blades has grown markedly in recent years. Two important issues are addressed in this thesis; (1) structural modeling and aeroelastic analysis of the damaged rotor blade and (2) development of a model based rotor health monitoring system. The effect of matrix cracking, the first failure mode in composites, is studied in detail for a circular section beam, box-beam and two-cell airfoil section beam. Later, the effects of further progressive damages such as debonding/delamination and fiber breakage are considered for a two-cell airfoil section beam representing a stiff-inplane helicopter rotor blade. It is found that the stiffness decreases rapidly in the initial phase of matrix cracking but becomes almost constant later as matrix crack saturation is reached. Due to matrix cracking, the bending and torsion stiffness losses at the point of matrix crack saturation are about 6-12 percent and about 25-30 percent, respectively. Due to debonding/delamination, the bending and torsion stiffness losses are about 6-8 percent and about 40-45 percent after matrix crack saturation, respectively. The stiffness loss due to fiber breakage is very rapid and leads to the final failure of the blade. An aeroelastic analysis is performed for the damaged composite rotor in forward flight and the numerically simulated results are used to develop an online health monitoring system. For fault detection, the variations in rotating frequencies, tip bending and torsion response, blade root loads and strains along the blade due to damage are investigated. It is found that peak-to-peak values of blade response and loads provide a good global damage indicator and result in considerable data reduction. Also, the shear strain is a useful indicator to predict local damage. The structural health monitoring system is developed using the physics based models to detect and locate damage from simulated noisy rotor system data. A genetic fuzzy system (GFS) developed for solving the inverse problem of detecting damage from noise contaminated measurements by hybridizing the best features of fuzzy logic and genetic algorithms. Using the changes in structural measurements between the damaged and undamaged blade, a fuzzy system is generated and the rule-base and membership functions optimized by genetic algorithm. The GFS is demonstrated using frequency and mode shape based measurements for various beam type structures such as uniform cantilever beam, tapered beam and non-rotating helicopter blade. The GFS is further demonstrated for predicting the internal state of the composite structures using an example of a composite hollow circular beam with matrix cracking damage mode. Finally, the GFS is applied for online SHM of a rotor in forward flight. It is found that the GFS shows excellent robustness with noisy data, missing measurements and degrades gradually in the presence of faulty sensors/measurements. Furthermore, the GFS can be developed in an automated manner resulting in an optimal solution to the inverse problem of SHM. Finally, the stiffness degradation of the composite rotor blade is correlated to the life consumption of the rotor blade and issues related to damage prognosis are addressed.

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5

Pawar, Prashant M. "Structural Health Monitoring Of Composite Helicopter Rotor Blades." Thesis, Indian Institute of Science, 2006. http://hdl.handle.net/2005/273.

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Анотація:

Helicopter rotor system operates in a highly dynamic and unsteady aerodynamic environment leading to severe vibratory loads on the rotor system. Repeated exposure to these severe loading conditions can induce damage in the composite rotor blade which may lead to a catastrophic failure. Therefore, an interest in the structural health monitoring (SHM) of the composite rotor blades has grown markedly in recent years. Two important issues are addressed in this thesis; (1) structural modeling and aeroelastic analysis of the damaged rotor blade and (2) development of a model based rotor health monitoring system. The effect of matrix cracking, the first failure mode in composites, is studied in detail for a circular section beam, box-beam and two-cell airfoil section beam. Later, the effects of further progressive damages such as debonding/delamination and fiber breakage are considered for a two-cell airfoil section beam representing a stiff-inplane helicopter rotor blade. It is found that the stiffness decreases rapidly in the initial phase of matrix cracking but becomes almost constant later as matrix crack saturation is reached. Due to matrix cracking, the bending and torsion stiffness losses at the point of matrix crack saturation are about 6-12 percent and about 25-30 percent, respectively. Due to debonding/delamination, the bending and torsion stiffness losses are about 6-8 percent and about 40-45 percent after matrix crack saturation, respectively. The stiffness loss due to fiber breakage is very rapid and leads to the final failure of the blade. An aeroelastic analysis is performed for the damaged composite rotor in forward flight and the numerically simulated results are used to develop an online health monitoring system. For fault detection, the variations in rotating frequencies, tip bending and torsion response, blade root loads and strains along the blade due to damage are investigated. It is found that peak-to-peak values of blade response and loads provide a good global damage indicator and result in considerable data reduction. Also, the shear strain is a useful indicator to predict local damage. The structural health monitoring system is developed using the physics based models to detect and locate damage from simulated noisy rotor system data. A genetic fuzzy system (GFS) developed for solving the inverse problem of detecting damage from noise contaminated measurements by hybridizing the best features of fuzzy logic and genetic algorithms. Using the changes in structural measurements between the damaged and undamaged blade, a fuzzy system is generated and the rule-base and membership functions optimized by genetic algorithm. The GFS is demonstrated using frequency and mode shape based measurements for various beam type structures such as uniform cantilever beam, tapered beam and non-rotating helicopter blade. The GFS is further demonstrated for predicting the internal state of the composite structures using an example of a composite hollow circular beam with matrix cracking damage mode. Finally, the GFS is applied for online SHM of a rotor in forward flight. It is found that the GFS shows excellent robustness with noisy data, missing measurements and degrades gradually in the presence of faulty sensors/measurements. Furthermore, the GFS can be developed in an automated manner resulting in an optimal solution to the inverse problem of SHM. Finally, the stiffness degradation of the composite rotor blade is correlated to the life consumption of the rotor blade and issues related to damage prognosis are addressed.

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6

Atilgan, Ali Rana. "Towards a unified analysis methodology for composite rotor blades." Diss., Georgia Institute of Technology, 1989. http://hdl.handle.net/1853/15403.

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7

Ku, Jieun. "A Hybrid Optimization Scheme for Helicopters with Composite Rotor Blades." Diss., Georgia Institute of Technology, 2007. http://hdl.handle.net/1853/16268.

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Анотація:

Rotorcraft optimization is a challenging problem due to its conflicting requirements among many disciplines and highly coupled design variables affecting the overall design. Also, the design process for a composite rotor blade is often ambiguous because of its design space. Furthermore, analytical tools do not produce acceptable results compared with flight test when it comes to aerodynamics and aeroelasticity unless realistic models are used, which leads to excessive computer time per iteration. To comply these requirements, computationally efficient yet realistic tools for rotorcraft analysis, such as VABS and DYMORE were used as analysis tools. These tools decompose a three-dimensional problem into a two-dimensional cross-sectional and a one-dimensional beam analysis. Also, to eliminate the human interaction between iterations, a previously VABS-ANSYS macro was modified and automated. The automated tool shortened the computer time needed to generate the VABS input file for each analysis from hours to seconds. MATLAB was used as the wrapper tool to integrate VABS, DYMORE and the VABS-ANSYS macro into the methodology. This methodology uses Genetic Algorithm and gradient-based methods as optimization schemes. The baseline model is the rotor system of generic Georgia Tech Helicopter (GTH), which is a three-bladed, soft-in-plane, bearingless rotor system. The resulting methodology is a two-level optimization, global and local. Previous studies showed that when stiffnesses are used as design variables in optimization, these values act as if they are independent and produce design requirements that cannot be achieved by local-level optimization. To force design variables at the global level to stay within the feasible design space of the local level, a surrogate model was adapted into the methodology. For the surrogate model, different ``design of experiments" (DOE) methods were tested to find the most computationally efficient DOE method. The response surface method (RSM) and Kriging were tested for the optimization problem. The results show that using the surrogate model speeds up the optimization process and the Kriging model shows superior performance over RSM models. As a result, the global-level optimizer produces requirements that the local optimizer can achieve.

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8

Macedo, Moura Geraldo A. "An approach for design and analysis of composite rotor blades." Thesis, Monterey, California. Naval Postgraduate School, 1989. http://hdl.handle.net/10945/25698.

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9

SHARMA, ANUJ. "DEVELOPMENT, CHARACTERIZATION AND DYNAMIC ANALYSIS OF METAL MATRIX COMPOSITE ROTOR." Thesis, DELHI TECHNOLOGICAL UNIVERSITY, 2021. http://dspace.dtu.ac.in:8080/jspui/handle/repository/18893.

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Анотація:

Industrial development is one of the pioneer enablers of the economic and social prosperity of any nation. High efficiency, low cost and reliable system are the most critical factors that are focussed by industries. New developments in this direction are observed in the past few decades. Researchers thrive for new inventions and technologies by which high-quality output can be attained with effective and robust systems. Materials play an essential role in achieving high efficiency by providing an outcome-based response to any process. With the advent of composite materials, industries have started focusing on using lighter weight materials with the same mechanical properties. Metal matrix composites have the edge over the parent metals for rotor applications as it has a higher specific modulus and specific modulus is the critical material factor for vibration responses. Aluminium /alumina MMCs have shown prominent growth in the composite material market because of their compatibility with the rotor systems. Several types of research are available for the development of aluminium based metal matrix composites for industrial applications. The main focus of this research is to propose a method of development of metal matrix composite for specific rotary applications. This work focuses on the development, characterization and dynamic analysis of the metal matrix rotor. The rotors are developed through a cost-effective, flexible, and readily available method called the stir casting process. The physical properties of the composites depend primarily on the homogeneity and the fraction of reinforcement in the matrix. The uniformity and the concentration have been enhanced by optimizing process parameters in various researches. However, these vii researches are based on the qualitative analysis (visual observation) of the microstructure of composites. These qualitative methods do not assist in providing numerical and objective-oriented results. Therefore, these methods lack a objective judgment that is crucial for comparing the dispersion of reinforcements consistently. Therefore, quantitative measurement of dispersion is essential for optimizing the process parameters in order to attain better results. There are several techniques for the quantitative measurement of particle dispersion in the matrix. The mean free path has been calculated by dividing micrograph images into multiple grid lines and was utilized for quantifying particle dispersions. The quantitative distribution index and area fraction may be beneficial in optimizing the process parameters and providing more authentic and reliable results than the qualitative analysis. There are various methods used for parametric optimization having multivariant parameters. Box- Behnken designs (BBD) are rotatable or nearly rotatable second-order designs based on three-level incomplete factorial designs. BBD is one of the main types of response surface design, the other being central composite design. The BBD design requires a smaller number of runs as compared to the central composite design. The Box-Behnken design operates within the range of parameters and does not generate experimentation points beyond the range of parameters like the central composite design. BBD is suitable for designs where the range of operations are constrained by manufacturing conditions. In this work, a novel technique has been adopted where newly developed quantitatively assessed responses are used for process optimization instead of conventional qualitative analysis and thus, it provides a profound methodology for optimization of process parameters. viii A novel characterization approach has been adopted in this work, which determines the effect of reinforcements on the dynamic properties and residual stress of the Al 6061/Al2O3 shafts. Long and slender shafts were fabricated through a stir casting process. Grain structure has been obtained through optical microscopy, and morphological evaluation of the composites was performed through Scanning Electron Microscopy (SEM). In addition to that, an X-ray diffraction pattern (XRD) were analyzed, and residual stress was calculated by X-ray residual stress measurement system μ-X360 Ver. 2. 3. 0. 1. Tensile strength and microhardness were also determined in this analysis for various compositions of the composite material. For composite materials, the system response changes abruptly with a change in the properties of the material. Therefore, attaining significant knowledge about the effect of material composition on material properties is crucial. The researchers are looking for new computational methods which can predict these alterations so that the effort in experimental testing can be reduced. In this direction, this paper presents a robust and novel methodology of validating the estimation of the composite's effective properties through a multi-scale approach by a set of standardized experimentation. These effective properties are estimated through the mean-field homogenization technique, whose parameters are driven from the image analysis of Scanning Electron Microscopy (SEM) images. The predicted results are validated with the results obtained by the experimentation as per ASTM E1876 standard. This research work has adopted a novel approach of providing a dedicated methodology for determining the calibrated internal damping factor for bond graph dynamic analysis, which has been used in various literature for transient and stable ix responses. The investigation has been performed on long and slender shafts of the metal matrix composites. An insight into the change in dynamic response with the difference in the composition of composite shafts is provided in this work. Many valuable insights and findings were obtained in this work related to the development and response of different compositions of metal matrix composite shafts. The optimization of the stir casting parameters using a quantitative distribution index and area fraction resulted in uniformly distributed composite shafts. The mechanical properties such as tensile strength, microhardness, specific modulus increased with the addition of reinforcement in the composite up to a particular limit. Above that limit, the agglomeration and porosity become prominent factors and further depletes the properties of a composite. The natural frequency of the composite shaft increased, and the amplitude of vibration was reduced for the composites with a high volume fraction of reinforcements. The values of Young's modulus of different compositions determined through computation were congruent with the experimental results. The dynamic response was simulated using bond graph analysis, and it was observed that the amplitude of orbits was also reduced for the composites with a high volume fraction of reinforcements.

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10

Bailey, Brent. "Investigation of a composite hingeless helicopter rotor blade with integral actuators." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 2000. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape4/PQDD_0024/MQ52385.pdf.

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Книги з теми "COMPOSITE ROTOR"

1

Piatak, David J. Stiffness characteristics of composite rotor blades with elastic couplings. Washington, D.C: National Aeronautics and Space Administration, 1997.

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2

W, Nixon Mark, Kosmatka J. B, and Langley Research Center, eds. Stiffness characteristics of composite rotor blades with elastic couplings. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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3

Moura, Geraldo A. Macedo. An approach for design and analysis of composite rotor blades. Monterey, Calif: Naval Postgraduate School, 1989.

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4

United States. National Aeronautics and Space Administration. Scientific and Technical Information Office., ed. Preliminary structural design of composite main rotor blades for minimum weight. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

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5

W, Nixon Mark, Rehfield Lawrence W, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Comparison of composite rotor blade models: A coupled-beam analysis and an MSC/NASTRAN finite-element model. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

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6

United States. National Aeronautics and Space Administration., ed. Aeroelastic response and stability of tiltrotors with elastically-coupled composite rotor blades. [Washington, DC: National Aeronautics and Space Administration, 1993.

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7

Center, Langley Research, ed. Aeroelasticity and structural optimization of composite helicopter rotor blades with swept tips. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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8

United States. National Aeronautics and Space Administration., ed. Aeroelastic response and stability of tiltrotors with elastically-coupled composite rotor blades. [Washington, DC: National Aeronautics and Space Administration, 1993.

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9

Lake, Renee C. Experimental and analytical investigation of dynamic characteristics of extension-twist-coupled composite tubular spars. Hampton, Va: Langley Research Center, 1993.

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10

C, Park K., and Langley Research Center, eds. An aeroelastic analysis of helicopter rotor blades incorporating piezoelectric fiber composite twist actuation. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1996.

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Більше джерел

Частини книг з теми "COMPOSITE ROTOR"

1

Rand, Omri. "Analysis of composite rotor blades." In Numerical Analysis and Modelling of Composite Materials, 1–26. Dordrecht: Springer Netherlands, 1996. http://dx.doi.org/10.1007/978-94-011-0603-0_1.

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2

Gupta, K. "Composite Shaft Rotor Dynamics: An Overview." In Mechanisms and Machine Science, 79–94. Cham: Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-09918-7_6.

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3

Ganguli, Ranjan. "Life Prediction of Composite Rotor Blade." In Structural Health Monitoring Technologies and Next-Generation Smart Composite Structures, 369–94. Taylor & Francis Group, 6000 Broken Sound Parkway NW, Suite 300, Boca Raton, FL 33487-2742: CRC Press, 2016. http://dx.doi.org/10.1201/9781315373492-11.

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4

Güemes, J. A., and F. Avia. "Design, Manufacturing and Tests of Large Wind Turbine Rotor Blades." In Composite Structures 4, 206–11. Dordrecht: Springer Netherlands, 1987. http://dx.doi.org/10.1007/978-94-009-3455-9_15.

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5

Pawar, Prashant M., and Ranjan Ganguli. "Structural Health Monitoring of Composite Helicopter Rotor." In Structural Health Monitoring Using Genetic Fuzzy Systems, 85–125. London: Springer London, 2011. http://dx.doi.org/10.1007/978-0-85729-907-9_5.

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6

Jacquet-Richardet, G., E. Chatelet, and T. Nouri-Baranger. "Rotating Internal Damping in the Case of Composite Shafts." In IUTAM Symposium on Emerging Trends in Rotor Dynamics, 125–34. Dordrecht: Springer Netherlands, 2010. http://dx.doi.org/10.1007/978-94-007-0020-8_11.

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7

Kensche, C., and H. Seifert. "Wind Turbine Rotor Blades under Fatigue Loads." In Developments in the Science and Technology of Composite Materials, 173–80. Dordrecht: Springer Netherlands, 1990. http://dx.doi.org/10.1007/978-94-009-0787-4_21.

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8

Gupta, K., S. P. Singh, V. Tiwari, Savi Takkar, Rahul Dev, and Anant Rai. "Vibration Analysis of Fiber Reinforced Composite Discs." In Proceedings of the 9th IFToMM International Conference on Rotor Dynamics, 1665–75. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-06590-8_137.

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9

Wierach, Peter, Johannes Riemenschneider, Steffen Opitz, and Frauke Hoffmann. "Experimental Investigation of an Active Twist Model Rotor Blade Under Centrifugal Loads." In Adaptive, tolerant and efficient composite structures, 391–407. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-29190-6_32.

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10

Zhu, Chang Sheng. "The Response Time of a Magnetorheological Fluid Squeeze Film Damper Rotor System." In Advances in Composite Materials and Structures, 1085–88. Stafa: Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-427-8.1085.

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Тези доповідей конференцій з теми "COMPOSITE ROTOR"

1

Volovoi, Vitali, Sangpil Yoon, Chang-Young Lee, and Dewey Hodges. "Structural Optimization of Composite Rotor Blades." In 45th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics & Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-1837.

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2

Corbin, C. K., J. M. Ganley, and S. W. Tsai. "Composite Flywheel Rotor Technology Development Overview." In Ninth Biennial Conference on Engineering, Construction, and Operations in Challenging Environments. Reston, VA: American Society of Civil Engineers, 2004. http://dx.doi.org/10.1061/40722(153)122.

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3

GANGULI, RANJAN, and INDERJIT CHOPRA. "Aeroelastic optimization of a composite helicopter rotor." In 4th Symposium on Multidisciplinary Analysis and Optimization. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-4780.

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4

HODGES, DEWEY. "A review of composite rotor blade modeling." In 29th Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-2249.

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5

Soykasap, Omer, and Dewey Hodges. "Aeroelastic optimization of a composite tilt rotor." In 39th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-1919.

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6

Chellil, A., A. T. Settet, S. Lecheb, A. Nour, A. Yahiaoui, and H. Kebir. "Aeroelastic stability analysis of composite rotor blade." In 2013 5th International Conference on Modeling, Simulation and Applied Optimization (ICMSAO 2013). IEEE, 2013. http://dx.doi.org/10.1109/icmsao.2013.6552604.

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7

Wolmarans, J. J., M. van der Geest, H. Polinder, J. A. Ferreira, and D. Zeilstra. "Composite materials for low loss rotor construction." In Drives Conference (IEMDC). IEEE, 2011. http://dx.doi.org/10.1109/iemdc.2011.5994862.

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8

Li, Leihong, Vitali Volovoi, and Dewey Hodges. "Probabilistic Design Optimization of Composite Rotor Blades." In 49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
16th AIAA/ASME/AHS Adaptive Structures Conference
10t. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-2260.

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9

Ha, Sung K., Dong-Gun Lee, and Dong-Jin Kim. "Optimization of Hybrid Composite Rotor in Flywheel Battery." In Future Transportation Technology Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1998. http://dx.doi.org/10.4271/981899.

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10

Shang, Xiaoyang, and Dewey Hodges. "Aeroelastic stability of composite rotor blades in hover." In 36th Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-1453.

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Звіти організацій з теми "COMPOSITE ROTOR"

1

Engblom, John J., and Ozden O. Ochoa. Nonlinear Dynamic Responses of Composite Rotor Blades. Fort Belvoir, VA: Defense Technical Information Center, August 1988. http://dx.doi.org/10.21236/ada200145.

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2

Kass, M. D., J. W. McKeever, M. A. Akerman, P. L. Goranson, P. S. Litherland, and D. U. O`Kain. Evaluation of Demo 1C composite flywheel rotor burst test and containment design. Office of Scientific and Technical Information (OSTI), July 1998. http://dx.doi.org/10.2172/656848.

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3

Griffin, D. A. WindPACT Turbine Design Scaling Studies Technical Area 1-Composite Blades for 80- to 120-Meter Rotor. Office of Scientific and Technical Information (OSTI), April 2001. http://dx.doi.org/10.2172/783406.

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4

Hughes, S. Preliminary Structural Design Conceptualization for Composite Rotor for Verdant Power Water Current: Cooperative Research and Development Final Report, CRADA Number CRD-08-296. Office of Scientific and Technical Information (OSTI), February 2011. http://dx.doi.org/10.2172/1008203.

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5

Bir, G., and P. Migliore. Preliminary Structural Design of Composite Blades for Two- and Three-Blade Rotors. Office of Scientific and Technical Information (OSTI), September 2004. http://dx.doi.org/10.2172/15009673.

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