Relevant bibliographies by topics / Tailoring optimization

Academic literature on the topic 'Tailoring optimization'

Author: Grafiati
Published: 14 March 2023

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Contents

Consult the lists of relevant articles, books, theses, conference reports, and other scholarly sources on the topic 'Tailoring optimization.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Journal articles on the topic "Tailoring optimization"

1

Biegler, Lorenz T. "Tailoring optimization algorithms to process applications." Computers & Chemical Engineering 16 (May 1992): S81—S95. http://dx.doi.org/10.1016/s0098-1354(09)80011-2.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

Sadagopan, D., and R. Pitchumani. "A Combinatorial Optimization Approach to Composite Materials Tailoring." Journal of Mechanical Design 119, no. 4 (December 1, 1997): 494–503. http://dx.doi.org/10.1115/1.2826395.

Full text
Abstract:
Composite materials offer designers the advantage of tailoring structures and materials to meet a variety of property and performance requirements in changing and demanding environments. However, the wide variety of material combinations, reinforcement geometries and architectures to choose from poses a bewildering problem of selection. Thus an appropriate, and furthermore optimal, tailoring of composite materials for applications is a challenging design problem and forms the focus of the article. Specifically, the present work addresses the problem of selecting optimal combinations of matrix and reinforcement materials, and reinforcement morphology, architecture, and volume fraction so as to meet the specified property and performance requirements. The optimal tailoring problem is solved using the combinatorial optimization technique of simulated annealing which works in conjunction with a property model base consisting of analytical relationships between the composite properties and the microstructure. The matrix materials considered in the study span the material classes of polymers, metals and ceramics while reinforcement geometries of unidirectional fibers, particulates and two-dimensional woven fabrics are considered. The overall approach and key results of the study are presented and discussed.
APA, Harvard, Vancouver, ISO, and other styles
3

De Leon, D. M., C. E. de Souza, J. S. O. Fonseca, and R. G. A. da Silva. "Aeroelastic tailoring using fiber orientation and topology optimization." Structural and Multidisciplinary Optimization 46, no. 5 (April 3, 2012): 663–77. http://dx.doi.org/10.1007/s00158-012-0790-8.

Full text
APA, Harvard, Vancouver, ISO, and other styles
4

Chattopadhyay, Aditi, Charles E. Seeley, and Ratneshwar Jha. "Aeroelastic tailoring using piezoelectric actuation and hybrid optimization." Smart Materials and Structures 8, no. 1 (January 1, 1999): 83–91. http://dx.doi.org/10.1088/0964-1726/8/1/009.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

ALTIMARI, PIETRO, ERASMO MANCUSI, MARIO DI BERNARDO, LUCIA RUSSO, and SILVESTRO CRESCITELLI. "TAILORING THE BIFURCATION DIAGRAM OF NONLINEAR DYNAMICAL SYSTEMS: AN OPTIMIZATION BASED APPROACH." International Journal of Bifurcation and Chaos 20, no. 04 (April 2010): 1027–40. http://dx.doi.org/10.1142/s0218127410026290.

Full text
Abstract:
Bifurcation tailoring is a method developed to design control laws modifying the bifurcation diagram of a nonlinear dynamical system to a desired one. In its original formulation, this method does not account for the possible presence of constraints on state and/or manipulated inputs. In this paper, a novel formulation of the bifurcation tailoring method overcoming this limitation is presented. In accordance with the proposed approach, a feedforward control law generating an optimal bifurcation diagram is computed by constrained minimization of an objective functional. Then, a feedback control system enforcing stability of the computed equilibrium branch is designed. In this context, bifurcation analysis is exploited to select feedback controller parameters ensuring desired output behavior and, at the same time, preventing the occurrence of multistability. The method is numerically validated on the problem of tailoring the bifurcation diagram of an exothermic chemical reactor.
APA, Harvard, Vancouver, ISO, and other styles
6

ABELS, ARTUR, and MAARJA KRUUSMAA. "SHAPE CONTROL OF AN ANTHROPOMORPHIC TAILORING ROBOT MANNEQUIN." International Journal of Humanoid Robotics 10, no. 02 (June 2013): 1350002. http://dx.doi.org/10.1142/s0219843613500023.

Full text
Abstract:
In this paper, we describe a new type of humanoid robot designed for made-to-measure garment industry — a shape-changing robotic mannequin. This mannequin is designed to imitate body shapes of different people. The main emphasis of this paper is on modeling and shape-optimization algorithm used to adjust mannequins shape to resemble the shape of any given person. We represent the whole procedure of adjusting the mannequin to the body shapes of real people. Finally, we provide the estimate of the mannequin's model precision and suitability of the proposed solutions for made-to-measure tailoring application. The results show that the mannequin and the optimization methods are sufficiently precise for the requirements in tailoring industry.
APA, Harvard, Vancouver, ISO, and other styles
7

Kapoor, PoonamM, Rohan Magoon, Arindam Choudhury, and Ameya Karanjkar. "An individualized hemodynamic optimization: Tailoring the targets of therapy." Journal of Anaesthesiology Clinical Pharmacology 36, no. 2 (2020): 274. http://dx.doi.org/10.4103/joacp.joacp_299_19.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

Cheng, Wen Yuan, De Gang Cui, Yan Chang, and Xiang Hui Xie. "Composite Structure Optimization Design System Based on Grid Technology." Key Engineering Materials 334-335 (March 2007): 453–56. http://dx.doi.org/10.4028/www.scientific.net/kem.334-335.453.

Full text
Abstract:
In the traditional iterative design process for composite structures, it is difficult to achieve an optimal solution even though a great effort is made. A genetic optimization system based on grid technology offers an automatic and efficient approach for composite structure redesign and optimization. A genetic algorithm system, which integrates Genetic Algorithm Optimization (GAO) software and a Finite Element Analysis (FEA) based commercial package, has been developed as a tool for composite structure design and analysis. The GAO is capable of tailoring large number of composite design variables and taking the time-consuming FEA results to calculate objective function value and conduct optimization in high accuracy. By operating the system employing the Grid technology and Artificial Neural Network (ANN) method, significant time saving in numerical analysis can be achieved. A user friendly interface has also been built in the system. In the paper, aeroelastic tailoring of a composite wing has been taken as a numerical example to demonstrate the optimization approach. The numerical results show that an optimal design has been achieved to meet the design requirement.
APA, Harvard, Vancouver, ISO, and other styles
9

Rongrong, Xue, Ye Zhengyin, Ye Kun, and Wang Gang. "Composite material structure optimization design and aeroelastic analysis on forward swept wing." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 13 (November 2, 2018): 4679–95. http://dx.doi.org/10.1177/0954410018807810.

Full text
Abstract:
The static aeroelastic torsion divergence problem is the main obstacle to bring forward swept wing into massive applications. The aeroelastic tailoring technique-based radial basis function neural networks (RBFNNs) and genetic algorithm (GA) optimization in MATLAB considering the material orientation, thickness, and lay-up are elucidated in the present work. RBFNNs are used to build a surrogate model between the composite parameters and structure displacement, which is proved robust and accurate. Then an optimal structure is obtained by GA global search based on RBFNNs model with the weight constrain. The displacements of the forward swept wing caused by an approximate aerodynamic load are decreased 32.5% through finite element method (FEM) static structural analysis. The modal analysis illustrates that the first mode frequency increases by 33.0% and the second mode increases by 37.9%. A computational aeroelasticity approach is developed by in-house Hybrid Unstructured Reynolds-Averaged Navier-Stokes solver associating an open source FEM code – Calculix. The results of coupling calculations show effectiveness of aeroelastic tailoring optimization of composite forward swept wing without weight penalty. The results obtained demonstrate that for the forward swept wing, the most violent situation appears around Mach Number 1.0 where the aeroelastic tailoring optimization could decrease the torsion angle by nearly 70.0%. The torsion of forward swept wing will increase at subsonic and decrease at supersonic with the increase of velocity.
APA, Harvard, Vancouver, ISO, and other styles
10

Abdullah, Nur Azam, and Erwin Sulaeman. "Aeroelastic Tailoring of Oscillating Supersonic Wing with External Stores." Applied Mechanics and Materials 464 (November 2013): 110–15. http://dx.doi.org/10.4028/www.scientific.net/amm.464.110.

Full text
Abstract:
This paper presents aeroelastic tailoring optimization of a swept back supersonic wing with external stores using composite structure material for the wing skin. The analysis has been conducted to calculate the flutter speeds at several altitudes ranging from a negative altitude of-7,943 ft until 30000 ft. MSC Nastran software is used to determine the flutter speed. The objective is to get the lowest possible wing weight by varying the wing skin composite fly angle and thickness as the optimization variables and by considering flutter speed as the optimization constraint. The constraint is imposed such that the flutter speed should be similar or higher than flutter speed of a previously investigated supersonic wing having similar planform but using aluminum as wing skin. The use of composite suggested that each composite layer thickness and fiber angle can be manipulated to achieve the target. The present results indicate that the weight of the composite wing skin can be reduced by 70 % compared to the aluminum wing skin while retaining similar or better flutter speed boundary envelope.
APA, Harvard, Vancouver, ISO, and other styles
More sources

Dissertations / Theses on the topic "Tailoring optimization"

1

Autio, M. (Maija). "Studies on tailoring of thermomechanical properties of composites." Doctoral thesis, Oulun yliopisto, 1999. http://urn.fi/urn:isbn:9514254473.

Full text
Abstract:
Abstract Layered composite materials consisting of thin orthotropic layers offer for a designer many possibilities to tailor the structure: the behaviour and properties of the structure can be influenced not only by varying the geometry and thicknesses of the structure but also by varying the lay-up of the laminate. As new orthotropic materials having high specific strength and stiffness are used in structures, the tailoring is essential to utilize all the benefits of these materials. In this thesis tailoring and optimization of thermomechanical properties of layered composite structures are considered. The tailoring problemis formulated and solved as a constrained nonlinear optimization problem. Different types of global thermomechanical properties, such as stiffnesses, coefficients of thermal expansion and natural frequencies and buckling loads of composite plates, as well as layer-wise properties, such as stresses and strains in a certain lamina, are considered. Also, coupled thermalstructural problems are studied. When lay-up parameters, i.e. number of layers, and their orientations and thicknesses, are employed as design variables, global as well as layer-wise properties of the laminate can be considered. As relations between thermomechanical properties and lay-up parameters are highly nonlinear, optimization may suffer from various local optima. However, in tailoring the global minima or maxima are not the points of interest but rather the points of design space, where appropriate values for considered properties are achieved. In the thesis optimization of global thermomechanical properties is presented also by applying so-called lamination parameters as design variables. The lamination parameters are defined as integrals of the functions, which consist of sines and cosines of the lay-up angles of different layers multiplied by the powers of the thickness co-ordinate z, through the thickness of the laminate. Thus, information of the lay-up of the laminate can be compressed into these parameters and only twelve lamination parameters are needed to describe the behaviour of a common laminate. The use of these parameters as design variables is advantageous, because the number of parameters needed is small and often formulating a convex optimization problem is possible. After finding optimal lamination parameters, a procedure is needed to generate a lay-up corresponding to these parameters. Explicit equations are derived for generating lay-ups having optimal bending lamination parameters. For creating a laminate having both optimal in-plane and bending lamination parameters, a new optimization problem searching laminates having lamination parameters as close as possible to the optimal ones is formulated. In that problem, also layer-wise properties and restrictions of manufacturing are taken into account. Agenetic algorithmsearch is employed for solving that later problem as the value of the objective function can be computed efficiently. Also, often the thicknesses and orientations of different layers can have only discrete values, which can be handled easily in the GA search, where all design variables are discrete in character.
APA, Harvard, Vancouver, ISO, and other styles
2

Canfield, Robert A. "Integrated structural design, vibration control, and aeroelastic tailoring by multiobjective optimization." Diss., This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-07282008-134827/.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

Walker, William Paul. "Optimization of Harmonically Deforming Thin Airfoils and Membrane Wings for Optimum Thrust and Efficiency." Diss., Virginia Tech, 2012. http://hdl.handle.net/10919/27748.

Full text
Abstract:
This dissertation presents both analytical and numerical approaches to optimizing thrust and thrust efficiency of harmonically deforming thin airfoils and membrane wings. A frequency domain unsteady aerodynamic theory for deformable thin airfoils, with Chebychev polynomials as the basis functions is presented. Stroke-averaged thrust and thrust efficiency expressions are presented in a quadratic matrix form. The motion and deformation of the airfoil is optimized for maximum thrust and efficiency. Pareto fronts are generated showing optimum deformation conditions (magnitude and phase) for various reduced frequencies and constraints. It is shown that prescribing the airfoil to deform in a linear combination of basis functions with optimal magnitude and phase results in a larger thrust as compared to rigid plunging, especially at low reduced frequencies. It is further shown that the problem can be constrained significantly such that thrust is due entirely to pressure with no leading edge suction, and associated leading edge separation. The complete aeroelastic system for a membrane wing is also optimized. The aerodynamic theory for deformable thin airfoils is used as the forcing in a membrane vibration problem. Due to the nature of the two dimensional theory, the membrane vibration problem is reduced to two dimensions via the Galerkin method and nondimensionalized such that the only terms are nondimesional tension, mass ratio and reduced frequency. The maximum thrust for the membrane wing is calculated by optimizing the tension in the membrane so that the the aeroelastic deformation due to wing motion leads to optimal thrust and/or efficiency. A function which describes the optimal variation of spanwise tension along the chord is calculated. It is shown that one can always find a range of membrane tension for which the flexible membrane wings performs better than the rigid wing. These results can be used in preliminary flapping wing MAV design.
Ph. D.
APA, Harvard, Vancouver, ISO, and other styles
4

Nordgren, Eleonora. "A study of tailoring acoustic porous material properties when designing lightweight multilayered vehicle panels." Phd thesis, Conservatoire national des arts et metiers - CNAM, 2012. http://tel.archives-ouvertes.fr/tel-00780756.

Full text
Abstract:
The present work explores the possibilities of adapting poro-elastic lightweight acoustic materials to specific applications. More explicitly, a design approach is presented where finite element based numerical simulations are combined with optimization techniques to improve the dynamic and acoustic properties of lightweight multilayered panels containing poro-elastic acoustic materials.The numerical models are based on Biot theory which uses equivalent fluid/solid models with macroscopic space averaged material properties to describe the physical behaviour of poro-elastic materials. To systematically identify and compare specific beneficial or unfavourable material properties, the numerical model is connected to a gradient based optimizer. As the macroscopic material parameters used in Biot theory are interrelated, they are not suitable to be used as independent design variables. Instead scaling laws are applied to connect macroscopic material properties to the underlying microscopic geometrical properties that may be altered independently.The design approach is also combined with a structural sandwich panel mass optimization, to examine possible ways to handle the, sometimes contradicting, structural and acoustic demands. By carefully balancing structural and acoustic components, synergetic rather than contradictive effects could be achieved, resulting in multifunctional panels; hopefully making additional acoustic treatment, which may otherwise undo major parts of the weight reduction, redundant.The results indicate a significant potential to improve the dynamic and acoustic properties of multilayered panels with a minimum of added weight and volume. The developed modelling techniques could also be implemented in future computer based design tools for lightweight vehicle panels. This would possibly enable efficient mass reduction while limiting or, perhaps, totally avoiding the negative impact on sound and vibration properties that is, otherwise, a common side effect of reducing weight, thus helping to achieve lighter and more energy efficient vehicles in the future.
APA, Harvard, Vancouver, ISO, and other styles
5

Lind, Nordgren Eleonora. "A study of tailoring acoustic porous material properties when designing lightweight multilayered vehicle panels." Doctoral thesis, KTH, MWL Marcus Wallenberg Laboratoriet, 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-100701.

Full text
Abstract:
The present work explores the possibilities of adapting poro-elastic lightweight acoustic materials to specific applications. More explicitly, a design approach is presented where finite element based numerical simulations are combined with optimization techniques to improve the dynamic and acoustic properties of lightweight multilayered panels containing poro-elastic acoustic materials. The numerical models are based on Biot theory which uses equivalent fluid/solid models with macroscopic space averaged material properties to describe the physical behaviour of poro-elastic materials. To systematically identify and compare specific beneficial or unfavourable material properties, the numerical model is connected to a gradient based optimizer. As the macroscopic material parameters used in Biot theory are interrelated, they are not suitable to be used as independent design variables. Instead scaling laws are applied to connect macroscopic material properties to the underlying microscopic geometrical properties that may be altered independently. The design approach is also combined with a structural sandwich panel mass optimization, to examine possible ways to handle the, sometimes contradicting, structural and acoustic demands. By carefully balancing structural and acoustic components, synergetic rather than contradictive effects could be achieved, resulting in multifunctional panels; hopefully making additional acoustic treatment, which may otherwise undo major parts of the weight reduction, redundant. The results indicate a significant potential to improve the dynamic and acoustic properties of multilayered panels with a minimum of added weight and volume. The developed modelling techniques could also be implemented in future computer based design tools for lightweight vehicle panels. This would possibly enable efficient mass reduction while limiting or, perhaps, totally avoiding the negative impact on sound and vibration properties that is, otherwise, a common side effect of reducing weight, thus helping to achieve lighter and more energy efficient vehicles in the future.

QC 20120815

APA, Harvard, Vancouver, ISO, and other styles
6

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

Full text
Abstract:
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.
APA, Harvard, Vancouver, ISO, and other styles
7

Carlsson, Martin. "Design and Testing of Flexible Aircraft Structures." Doctoral thesis, KTH, Aeronautical and Vehicle Engineering, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3761.

Full text
Abstract:

Methods for structural design, control, and testing offlexible aircraft structures are considered. Focus is onnonconventional aircraft con- figurations and control concepts.The interaction between analysis and testing is a central topicand all studies include validation testing and comparisonbetween computational and experimental results.

The first part of the thesis is concerned with the designand testing of an aeroelastic wind-tunnel model representing aBlended Wing Body (BWB) aircraft. The investigations show thata somewhat simplified wind-tunnel model design concept isuseful and efficient for the type of investigations considered.Also, the studies indicate that well established numericaltools are capable of predicting the aeroelastic behavior of theBWB aircraft with reasonable accuracy. Accurate prediction ofthe control surface aerodynamics is however found to bedifficult.

A new aerodynamic boundary element method for aeroelastictimedomain simulations and its experimental validation arepresented. The properties of the method are compared totraditional methods as well as to experimental results. Thestudy indicates that the method is capable of efficient andaccurate aeroelastic simulations.

Next, a method for tailoring a structure with respect to itsaeroelastic behavior is presented. The method is based onnumerical optimization techniques and developed for efficientdesign of aeroelastic wind-tunnel models with prescribed staticand dynamic aeroelastic properties. Experimental validationshows that the design method is useful in practice and that itprovides a more efficient handling of the dynamic aeroelasticproperties compared to previous methods.

Finally, the use of multiple control surfaces andaeroelastic effects for efficient roll maneuvering isconsidered. The idea is to design a controller that takesadvantage of the elasticity of the structure for performancebenefits. By use of optimization methods in combination with afairly simple control system, good maneuvering performance isobtained with minimal control effort. Validation testing usinga flexible wind-tunnel model and a real-time control systemshows that the control strategy is successful in practice.Keywords: aeroelasticity, active aeroelastic structures,aeroelastic tailoring, control, structural optimization,wind-tunnel testing.

APA, Harvard, Vancouver, ISO, and other styles
8

Zhao, Wei. "Optimal Design and Analysis of Bio-inspired, Curvilinearly Stiffened Composite Flexible Wings." Diss., Virginia Tech, 2017. http://hdl.handle.net/10919/79143.

Full text
Abstract:
Large-aspect-ratio wings and composite structures both have been considered for the next-generation civil transport aircraft to achieve improved aerodynamic efficiency and to save aircraft structural weight. The use of the large-aspect-ratio and the light-weight composite wing can lead to an enhanced flexibility of the aircraft wing, which may cause many aeroelastic problems such as large deflections, increased drag, onset of flutter, loss of control authority, etc. Aeroelastic tailoring, internal structural layout design and aerodynamic wing shape morphing are all considered to address these aeroelastic problems through multidisciplinary design, analysis and optimization (MDAO) studies in this work. Performance Adaptive Aeroelastic Wing (PAAW) program was initiated by NASA to leverage the flexibility associated with the use of the large-aspect-ratio wings and light-weight composite structures in a beneficial way for civil transport aircraft wing design. The biologically inspired SpaRibs concept is used for aircraft wing box internal structural layout design to achieve the optimal stiffness distribution to improve the aircraft performance. Along with the use of the active aeroelastic wing concept through morphing wing shape including the wing jig-shape, the control surface rotations and the aeroelastic tailoring scheme using composite laminates with ply-drop for wing skin design, a MDAO framework, which has the capabilities in total structural weight minimization, total drag minimization during cruise, ground roll distance minimization in takeoff and load alleviation in various maneuver loads by morphing its shape, is developed for designing models used in the PAAW program. A bilevel programming (BLP) multidisciplinary design optimization (MDO) architecture is developed for the MDAO framework. The upper-level optimization problem entails minimization of weight, drag and ground roll distance, all subjected to both static constraints and the global dynamic requirements including flutter mode and free vibration modes due to the specified control law design for body freedom flutter suppression and static margin constraint. The lower-level optimization is conducted to minimize the total drag by morphing wing shape, to minimize wing root bending moment by scheduling flap rotations (a surrogate for weight reduction), and to minimize the takeoff ground roll distance. Particle swarm optimization and gradient-based optimization are used, respectively, in the upper-level and the lower-level optimization problems. Optimization results show that the wing box with SpaRibs can further improve the aircraft performances, especially in a large weight saving, as compared to the wing with traditional spars and ribs. Additionally, the nonuniform chord control surface associated with the wing with SpaRibs achieve further reductions in structural weight, total drag and takeoff ground roll distance for an improved aircraft performance. For a further improvement of the global wing skin panel design, an efficient finite element approach is developed in designing stiffened composite panels with arbitrarily shaped stiffeners for buckling and vibration analyses. The developed approach allows the finite element nodes for the stiffeners and panels not to coincide at the panel-stiffeners interfaces. The stiffness, mass and geometric stiffness matrices for the stiffeners can be transformed to those for the panel through the displacement compatibility at their interfaces. The method improves the feasible model used in shape optimizing by avoiding repeated meshing for stiffened plate. Also, it reduces the order of the finite element model, a fine mesh typically associated with the skin panel stiffened by many stiffeners, for an efficient structural analysis. Several benchmark cases have been studied to verify the accuracy of the developed approach for stiffened composite panel structural analyses. Several parametric studies are conducted to show the influence of stiffener shape/placement/depth-ratio on panel's buckling and vibration responses. The developed approach shows a potential benefit of using gradient-based optimization for stiffener shape design.
Ph. D.
APA, Harvard, Vancouver, ISO, and other styles
9

Nielsen, Mark. "Design of aerospace laminates for multi-axis loading and damage tolerance." Thesis, University of Bath, 2018. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.760971.

Full text
Abstract:
Acknowledging the goal of reduced aircraft weight, there is a need to improve on conservative design techniques used in industry. Minimisation of laminate in-plane elastic energy is used as an appropriate in-plane performance marker to assess the weight saving potential of new design techniques. MATLAB optimisations using a genetic algorithm were used to find the optimal laminate variables for minimum in-plane elastic energy and/or damage tolerance for all possible loadings. The use of non-standard angles was able to offer equivalent, if not better in-plane performance than standard angles, and are shown to be useful to improve the ease of manufacture. Any standard angle laminate stiffness was shown to be able to be matched by a range of two non-standard angle ply designs. This non-uniqueness of designs was explored. Balancing of plus and minus plies about the principal loading axes instead of themanufacturing axes was shown to offer considerable potential for weight saving as the stiffness is better aligned to the load. Designing directly for an uncertain design load showed little benefit over the 10% ply percentage rule in maintaining in-plane performance. This showed the current rule may do a sufficient job to allow robustness in laminate performance. This technique is seen useful for non-standard angle design that lacks an equivalent 10% rule. Current use of conservative damage tolerance strain limits for design has revealed the need for more accurate prediction of damage propagation. Damage tolerance modelling was carried out using fracture mechanics for a multi-axial loading considering the full 2D strain energy and improving on current uni-axial models. The non-conservativeness of the model was evidenced to be from assumptions of zero post-buckled stiffness. Preliminary work on conservative multi-axial damage tolerance design, independent of thickness, is yet to be confirmed by experiments.
APA, Harvard, Vancouver, ISO, and other styles
10

Dasgupta, Anshuman. "Tailoring traditional optimizations for runtime compilation." Thesis, 2007. http://hdl.handle.net/1911/20595.

Full text
Abstract:
Runtime compilation, due to its online nature, presents unique challenges and opportunities to compiler designers. Since compilation occurs during program execution, a just-in-time compiler (JIT) must be judicious in expending compilation time. The literature on traditional, offline compilers describes numerous program transformation techniques that strive to increase execution efficiency. However, while optimization passes for static compilers are well understood and have been thoroughly investigated, many such transformation algorithms cannot be implemented on a JIT environment due to compilation-time constraints. Further, offline algorithms are not designed to exploit information available to an online compiler at program execution time. The thesis of the research presented in this document is that program optimization techniques designed for traditional, offline compilers can be profitably adapted for a runtime compiler by effectively respecting the constraints imposed on compilation time and by exploiting the opportunities available in a runtime compilation environment. To that end, the dissertation explores the complexity of implementing program transformations for a runtime compiler and redesigns two optimization techniques for a JIT: register allocation and loop unrolling. The two transformations present contrasting challenges when they are included in a runtime compiler. While several offline, heuristic allocation algorithms achieve impressive results, they consume large amounts of compilation-time that are typically unacceptable for a JIT. We describe the design of two allocation algorithms that reduce allocation time while preserving the advantages of strong techniques authored for offline compilers. An experimental evaluation of the new algorithms demonstrates their effectiveness on a runtime compilation environment. While a runtime compiler is limited by the constraints imposed by its environment, compiling just prior to program invocation provides certain advantages over an offline compiler. In particular, it can examine information only available at program execution time. We describe the design of a lightweight runtime value-examining mechanism and a loop unrolling algorithm that work in tandem. Our experimental results indicate that the runtime unroller achieves significant improvements on floating point, scientific benchmarks. In summary, thus, the research described in this dissertation demonstrates how compiler optimization algorithms can be effectively tailored for runtime compilation.
APA, Harvard, Vancouver, ISO, and other styles

Books on the topic "Tailoring optimization"

1

Morel, M. Concurrent micromechanical tailoring and fabrication process optimization for metal-matrix composites. [Washington, DC]: National Aeronautics and Space Administration, 1991.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
2

C, Chamis C., and United States. National Aeronautics and Space Administration., eds. Composite laminate tailoring with probabilistic constraints and loads. [Washington, D.C.]: NASA, 1990.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
3

Simultaneous Composite Tailoring and Bending Control Optimization for Damping the Torsional Vibration of a Plate. Storming Media, 1996.

Find full text
APA, Harvard, Vancouver, ISO, and other styles

Book chapters on the topic "Tailoring optimization"

1

Oliva, E., Ph Zeitoun, P. Velarde, M. Fajardo, K. Cassou, D. Ros, D. Portillo, and S. Sebban. "Optimization of soft x-ray amplifiers by tailoring plasma hydrodynamic." In Springer Proceedings in Physics, 137–42. Dordrecht: Springer Netherlands, 2011. http://dx.doi.org/10.1007/978-94-007-1186-0_16.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

Cenerini, Costanza, Luca Vollero, Giorgio Pennazza, Marco Santonico, and Flavio Keller. "Audio Visual Association Test in Non Synesthetic Subjects: Technological Tailoring of the Methods." In Machine Learning, Optimization, and Data Science, 432–37. Cham: Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-25891-6_32.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

Alirezaeizanjani, Zahra, Jan-Hendrik Trösemeier, Christel Kamp, and Sophia Rudorf. "Tailoring Codon Usage to the Underlying Biology for Protein Expression Optimization." In Methods in Molecular Biology, 85–92. New York, NY: Springer US, 2022. http://dx.doi.org/10.1007/978-1-0716-1859-2_4.

Full text
APA, Harvard, Vancouver, ISO, and other styles
4

Casarin, Michele, Riccardo Ceccato, and Vincenzo M. Sglavo. "Tailoring the Anode Microstructure in Micro-Tubular Sofcs by the Optimization of the Slurry." In Advances in Solid Oxide Fuel Cells VIII, 23–33. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2012. http://dx.doi.org/10.1002/9781118217481.ch3.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Alexandersen, Joe, and Boyan Stefanov Lazarov. "Tailoring Macroscale Response of Mechanical and Heat Transfer Systems by Topology Optimization of Microstructural Details." In Computational Methods in Applied Sciences, 267–88. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-18320-6_15.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

"Tailoring Heterogeneous Catalysts for Pollutant Combustion with High-Throughput Methods." In Combinatorial and High-Throughput Discovery and Optimization of Catalysts and Materials, 193–212. CRC Press, 2006. http://dx.doi.org/10.1201/9781420005387-17.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

Majumdar, Jyotsna Dutta, Andreas Weisheit, and I. Manna. "Laser Surface Processing for Tailoring of Properties by Optimization of Microstructure." In Advances in Civil and Industrial Engineering, 121–71. IGI Global, 2016. http://dx.doi.org/10.4018/978-1-5225-0329-3.ch006.

Full text
Abstract:
Laser surface processing involves modification of surface microstructure and/or composition of the near surface region of a component using a high power laser beam. The advantages of laser surface processing over conventional equilibrium surface processing include rapid processing rate, retention of non-equilibrium microstructure, alloying in liquid state and development of processed zone with superior properties as compared to the same developed by equilibrium processing route. Microstructure plays an important role to control the final properties of the tailored component. In the present contribution, with a brief introduction to laser, and its application, the microstructures developed under optimum conditions by different laser surface processing will be discussed with the corresponding improvement in properties. Finally, a brief review of the future scope of research in laser surface processing will be presented.
APA, Harvard, Vancouver, ISO, and other styles
8

Mylavarapu, Deepak, Manas Das, and Ganesh Narayanan R. "Prediction of Temperature Evolution During Self-Pierced Riveting of Sheets." In Handbook of Research on Manufacturing Process Modeling and Optimization Strategies, 381–98. IGI Global, 2017. http://dx.doi.org/10.4018/978-1-5225-2440-3.ch018.

Full text
Abstract:
Weight reduction of automotive components by tailoring materials is the state of the art. This basically has resulted in the development of advanced joining methods like clinching, friction stir welding, self-pierced riveting etc. to assemble similar or dissimilar materials, with significant change in sheet properties. In the present work, the main aim is to predict the temperature evolution during Self-Pierced Riveting (SPR) of sheets by Finite Element (FE) analyses. Load evolution is also predicted. Generally temperature estimation during SPR is not attempted. The influence of a few selected SPR parameters has been studied on the temperature and load evolution through FE simulations. The relationship between these parameters and the temperature and the load evolution are revealed. Later a neural network model is developed to predict the temperature rise during SPR. The same has been validated at 20 intermediate levels and the predictions are accurate. Thus a hybrid FEM-ANN model for SPR has been developed to predict the SPR outputs efficiently.
APA, Harvard, Vancouver, ISO, and other styles

Conference papers on the topic "Tailoring optimization"

1

Opgenoord, Max M., and Karen E. Willcox. "Aeroelastic Tailoring using Additively Manufactured Lattice Structures." In 2018 Multidisciplinary Analysis and Optimization Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-4055.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

NARAYANAN, G., E. REDDY, G. ABUMERI, DALE HOPKINS, and CHRISTOS CHAMIS. "Structural Tailoring/Analysis for Hypersonic Components - A computational simulation." In 4th Symposium on Multidisciplinary Analysis and Optimization. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-4722.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

Perera, Melanie, and Shijun Guo. "Structural and Aeroelastic Tailoring of a Seamless Aeroelastic Wing." In 12th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-5969.

Full text
APA, Harvard, Vancouver, ISO, and other styles
4

Chattopadhyay, Aditi, Charles E. Seeley, and Ratneshwar Jha. "Aeroelastic tailoring using piezoelectric actuation and hybrid optimization." In 5th Annual International Symposium on Smart Structures and Materials, edited by Mark E. Regelbrugge. SPIE, 1998. http://dx.doi.org/10.1117/12.316909.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Liu, Wenli, and Richard Butler. "Buckling Optimization for Composite Panels with Elastic Tailoring." 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/10.2514/6.2008-2125.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

Vial, B., and Yang Hao. "Tailoring near and Far Electromagnetic Fields Through Optimization." In 12th European Conference on Antennas and Propagation (EuCAP 2018). Institution of Engineering and Technology, 2018. http://dx.doi.org/10.1049/cp.2018.0651.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

REDDY, E., G. ABUMERI, P. MURTHY, and C. CHAMIS. "Structural tailoring of aircraft engine blade subject to ice impact constraints." In 4th Symposium on Multidisciplinary Analysis and Optimization. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-4710.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

Cornette, Donatien, Benjamin Kerdreux, Yves Gourinat, and Guilhem Michon. "Aeroelastic Tailoring of Helicopter Blades." In ASME 2013 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/detc2013-12848.

Full text
Abstract:
The dynamic loads transmitted from the rotor to the airframe are responsible for vibrations, discomfort and alternate stress of components. A new and promising way to minimize vibration is to reduce dynamic loads at their source by performing an aeroelastic optimization of the rotor. This optimization is done thanks to couplings between the flapwise-bending motion and the torsion motion. The impact of elastic couplings (composite anisotropy) on the blade dynamic behaviour and on dynamic loads are evaluated in this paper. Firstly, analytical results, based on a purely linear modal approach, are given to understand the influence of those couplings in terms of frequency placement, aerodynamic lift load and vertical shear modification. Then, those elastic couplings are introduced on a simplified but representative blade (homogeneous beam with constant chord) and results are presented.
APA, Harvard, Vancouver, ISO, and other styles
9

Magdaleno, Andrea Magalhaes. "An Optimization-based Approach to Software Development Process Tailoring." In 2010 Second International Symposium on Search Based Software Engineering (SSBSE). IEEE, 2010. http://dx.doi.org/10.1109/ssbse.2010.15.

Full text
APA, Harvard, Vancouver, ISO, and other styles
10

Zeng, Jie, Wenmin Qian, and Chuanjun Liu. "Application of Shape Function for Aeroelastic Tailoring of the Composite Wing Structure." In 18th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-4146.

Full text
APA, Harvard, Vancouver, ISO, and other styles

Reports on the topic "Tailoring optimization"

1

Federinko, John, Rusti L. Pool, William Z. Zeck, and Joseph D. Martin. Unit Type Code Development, Tailoring, and Optimization (UTC-DTO) Phase 2 Final Report. Fort Belvoir, VA: Defense Technical Information Center, December 1997. http://dx.doi.org/10.21236/ada388557.

Full text
APA, Harvard, Vancouver, ISO, and other styles
You might also be interested in the extended bibliographies on the topic 'Tailoring optimization' for particular source types:
Journal articles
We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!

To the bibliography