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This study aims to design novel tailorable and effective mechanisms by controlling buckling behaviour in structural elements of a composite wing for future morphing application. Instead of the traditional design against buckling, the idea is to embrace this built-in instability by using the nonlinear post-buckling response to control stiffness changes which redistribute the load in the wing structure. To enable desired multi-stable configurations, three buckling-driven mechanisms are investigated by restraining the out-of-plane buckling deformation using point, area and maximum displacement constraints. Numerical studies of the proposed mechanisms are at first conducted on a composite plate and are later integrated to control twisting of a simplified thin-walled composite wing box. The proposed mechanisms offer effective design opportunities of multi-stable configurations and demonstrate the potential to realise morphing of composite wings employing controlled buckling behaviours in structural components.
Jiayao Zhang; Chiara Bisagni. Buckling-driven mechanisms for twisting control in adaptive composite wings. Aerospace Science and Technology 2021, 118, 107006 .
AMA StyleJiayao Zhang, Chiara Bisagni. Buckling-driven mechanisms for twisting control in adaptive composite wings. Aerospace Science and Technology. 2021; 118 ():107006.
Chicago/Turabian StyleJiayao Zhang; Chiara Bisagni. 2021. "Buckling-driven mechanisms for twisting control in adaptive composite wings." Aerospace Science and Technology 118, no. : 107006.
A laboratory demonstration for a Stability of Structures course is presented, consisting in the buckling test of two cylindrical shells: a 3 D-printed and a composite cylinder. The learning outcomes have been formulated by comparing what can be learnt from theoretical lessons and buckling tests. The activity follows the Interactive Lecture Demonstration approach. Main results show that the activity helped students’ understanding of shell buckling and it increased their enthusiasm for the topic. This demonstration is easily implementable, and the presented step-by-step development methodology provides guidelines to develop similar activities for different engineering subjects.
Marta Gavioli; Chiara Bisagni. Teaching buckling of cylindrical shells through an effective laboratory demonstration. Mechanics of Advanced Materials and Structures 2021, 1 -28.
AMA StyleMarta Gavioli, Chiara Bisagni. Teaching buckling of cylindrical shells through an effective laboratory demonstration. Mechanics of Advanced Materials and Structures. 2021; ():1-28.
Chicago/Turabian StyleMarta Gavioli; Chiara Bisagni. 2021. "Teaching buckling of cylindrical shells through an effective laboratory demonstration." Mechanics of Advanced Materials and Structures , no. : 1-28.
Composite plates in post-buckling regime can experience mode jumping in their buckling shape, suddenly increasing the number of half-waves. This phenomenon can be advantageous, because the shape change could be used for local morphing or structural adaptability in future aerospace structures. A study of this phenomenon under heating is here presented, combining numerical and experimental techniques. At first, a set of parametric analysis was conducted to identify composite panels that present a mode jump when heated. Three plates were selected, one in aluminum alloy 2024 T 3 , and two in AS 4 / 8552 composite material, with layup [ 30 / − 30 / 5 / − 5 ] s and [ 35 / − 35 / 10 / − 10 ] s . The plates were tested in a new test setup for thermal buckling based on low thermal expansion fixtures. The mode jumping was successfully obtained experimentally for both composite plates. Numerical simulations predicted the general trends for all plates, and the mode jumps for the composite plates.
Javier Gutiérrez Álvarez; Chiara Bisagni. A Study on Thermal Buckling and Mode Jumping of Metallic and Composite Plates. Aerospace 2021, 8, 56 .
AMA StyleJavier Gutiérrez Álvarez, Chiara Bisagni. A Study on Thermal Buckling and Mode Jumping of Metallic and Composite Plates. Aerospace. 2021; 8 (2):56.
Chicago/Turabian StyleJavier Gutiérrez Álvarez; Chiara Bisagni. 2021. "A Study on Thermal Buckling and Mode Jumping of Metallic and Composite Plates." Aerospace 8, no. 2: 56.
This paper presents the derivation of nondimensional buckling equations of sandwich cylindrical shells made of composite facesheets with a shear deformable core. The procedure yields an analytical solution in terms of a series of nondimensional parameters for the axial buckling load investigating the influence of the core transverse shear. The developed equations and the nondimensional parameters are used to study the buckling response of different shells, and the calculated buckling loads are compared to the buckling values obtained by neglecting the transverse shear. Graphs and tables are presented to show the effects of the nondimensional parameters on the nondimensional buckling load. The results are verified by finite element analyses using the commercial code Abaqus.
Ines Uriol Balbin; Chiara Bisagni. Buckling of sandwich cylindrical shells with shear deformable core through nondimensional parameters. Thin-Walled Structures 2021, 161, 107393 .
AMA StyleInes Uriol Balbin, Chiara Bisagni. Buckling of sandwich cylindrical shells with shear deformable core through nondimensional parameters. Thin-Walled Structures. 2021; 161 ():107393.
Chicago/Turabian StyleInes Uriol Balbin; Chiara Bisagni. 2021. "Buckling of sandwich cylindrical shells with shear deformable core through nondimensional parameters." Thin-Walled Structures 161, no. : 107393.
The fatigue life prediction of post-buckled composite structures represents still an unresolved issue due to the complexity of the phenomenon and the high costs of experimental testing. In this paper, a novel numerical approach, called “Min-Max Load Approach”, is used to analyze the behavior of a composite single-stringer specimen with an initial skin-stringer delamination subjected to post-buckling fatigue compressive load. The proposed approach, based on cohesive zone model technique, is able to evaluate the local stress ratio during the delamination growth, performing, in a single Finite Element analysis, the simulation of the structure at the maximum and minimum load of the fatigue cycle. The knowledge of the actual value of the local stress ratio is crucial to correctly calculate the crack growth rate. At first, the specimen is analyzed under quasi-static loading conditions, then the fatigue simulation is performed. The results of the numerical analysis are compared with the data of an experimental campaign previously conducted, showing the capabilities of the proposed approach.
A. Raimondo; C. Bisagni. Fatigue analysis of a post-buckled composite single-stringer specimen taking into account the local stress ratio. Composites Part B: Engineering 2020, 193, 108000 .
AMA StyleA. Raimondo, C. Bisagni. Fatigue analysis of a post-buckled composite single-stringer specimen taking into account the local stress ratio. Composites Part B: Engineering. 2020; 193 ():108000.
Chicago/Turabian StyleA. Raimondo; C. Bisagni. 2020. "Fatigue analysis of a post-buckled composite single-stringer specimen taking into account the local stress ratio." Composites Part B: Engineering 193, no. : 108000.
A closed-form solution is derived for the buckling of orthotropic composite plates under the effect of thermal and mechanical loads. The plates are subjected to constant temperature increment and length variation while the width expansion is constrained. The problem is formulated in terms of displacement components, studied using classical plate theory in combination with classical lamination theory. An analytical formula that relates critical temperatures to applied plate displacements is obtained. The buckling of heated, fully restrained plates is also derived as a particular case. Examples of plates made of different materials and lay-ups are presented in graphical form, and are verified by finite element analysis. The obtained formula can be used during initial design, for sensitivity analysis and also for obtaining desired buckling shapes.
Javier Gutiérrez Álvarez; Chiara Bisagni. Closed-form solutions for thermomechanical buckling of orthotropic composite plates. Composite Structures 2019, 233, 111622 .
AMA StyleJavier Gutiérrez Álvarez, Chiara Bisagni. Closed-form solutions for thermomechanical buckling of orthotropic composite plates. Composite Structures. 2019; 233 ():111622.
Chicago/Turabian StyleJavier Gutiérrez Álvarez; Chiara Bisagni. 2019. "Closed-form solutions for thermomechanical buckling of orthotropic composite plates." Composite Structures 233, no. : 111622.
Aeronautical composite stiffened structures have the capability to carry loads deep into postbuckling, yet they are typically designed to operate below the buckling load to avoid potential issues with durability and structural integrity. Large out-of-plane postbuckling deformation of the skin can result in the opening of the skin-stringer interfaces, especially in the presence of defects, such as impact damage. To ensure that skin-stringer separation does not propagate in an unstable mode that can cause a complete collapse of the structure, a deeper understanding of the interaction between the postbuckling deformation and the development of damage is required. The present study represents a first step towards a methodology based on analysis and experiments to assess and improve the strength, life, and damage tolerance of stiffened composite structures subjected to postbuckling deformations. Two regions were identified in a four-stringer panel in which skin-stringer separation can occur, namely the region of maximum deflection and the region of maximum twisting. Both regions have been studied using a finite element model of a representative single-stringer specimen. For the region of maximum deflection, a seven-point bending configuration was used, in which five supports and two loading points induce buckling waves to the specimen. The region of maximum twisting was studied using an edge crack torsion configuration, with two supports and two loading points. These two configurations were studied by changing the positions of the supports and the loading points. An optimization procedure was carried out to minimize the error between the out-of-plane deformation of the representative single-stringer specimen and the corresponding region of the fourstringer panel.
Luc Kootte; Chiara Bisagni; Carlos Davila; Vipul Ranatunga. Study of Skin-Stringer Separation in Postbuckled Composite Aeronautical Structures. American Society for Composites 2018 2018, 1 .
AMA StyleLuc Kootte, Chiara Bisagni, Carlos Davila, Vipul Ranatunga. Study of Skin-Stringer Separation in Postbuckled Composite Aeronautical Structures. American Society for Composites 2018. 2018; ():1.
Chicago/Turabian StyleLuc Kootte; Chiara Bisagni; Carlos Davila; Vipul Ranatunga. 2018. "Study of Skin-Stringer Separation in Postbuckled Composite Aeronautical Structures." American Society for Composites 2018 , no. : 1.
An experimental and numerical investigation was conducted to study the skin–stiffener separation of single T-shape stiffener specimens in postbuckling condition. Three specimens were manufactured with a centrally located Teflon insert, and were loaded in compression until collapse. Deformation patterns and separation evolution were monitored during the tests. To measure the full-field displacements and the strain distributions of the specimens, a digital image correlation (DIC) system was used. Skin–stiffener separation was observed and measured with an ultrasound system. Finite-element (FE) analyses were conducted to capture interlaminar damage mechanism based on the virtual crack closure technique. The numerical analysis accurately predicted the postbuckling deformation and the skin–stiffener separation behavior. The close correlation between the experimental and numerical results allows for further exploitation of the strength reserve in the postbuckling region and wider design options for the next generation of composite aircraft designs.
Duo Zou; Chiara Bisagni. Skin–Stiffener Separation in T-Stiffened Composite Specimens in Postbuckling Condition. Journal of Aerospace Engineering 2018, 31, 04018027 .
AMA StyleDuo Zou, Chiara Bisagni. Skin–Stiffener Separation in T-Stiffened Composite Specimens in Postbuckling Condition. Journal of Aerospace Engineering. 2018; 31 (4):04018027.
Chicago/Turabian StyleDuo Zou; Chiara Bisagni. 2018. "Skin–Stiffener Separation in T-Stiffened Composite Specimens in Postbuckling Condition." Journal of Aerospace Engineering 31, no. 4: 04018027.
A semi-analytical method for the buckling and postbuckling analysis of composite-stiffened panels is presented. The method is formulated in the context of a variational framework and is based on the method of Ritz. Two levels of approximation are introduced, consisting of a plate assembly representation for the buckling analysis and an elastically restrained panel for the postbuckling assessment. Two aeronautical panels with open-section and closed-section stringer profiles are analyzed, illustrating the comparison with finite element predictions and with experimental data taken from the literature. The results indicate that accurate predictions can be obtained in terms of buckling loads, postbuckling reduction in stiffness, and out-of-plane deflections with an analysis time of the order of a few seconds.
Riccardo Vescovini; Chiara Bisagni. Buckling and Postbuckling Analysis of Composite-Stiffened Panels Using a Semi-Analytical Approach. Wear in Advanced Engineering Applications and Materials 2018, 173 -207.
AMA StyleRiccardo Vescovini, Chiara Bisagni. Buckling and Postbuckling Analysis of Composite-Stiffened Panels Using a Semi-Analytical Approach. Wear in Advanced Engineering Applications and Materials. 2018; ():173-207.
Chicago/Turabian StyleRiccardo Vescovini; Chiara Bisagni. 2018. "Buckling and Postbuckling Analysis of Composite-Stiffened Panels Using a Semi-Analytical Approach." Wear in Advanced Engineering Applications and Materials , no. : 173-207.
The fatigue life and damage tolerance of composite stiffened panels with indentation damage are investigated experimentally using single-stringer compression specimens. The indentation damage was induced to one of the two flanges of the stringer of every panel. The advantages of indentation compared to impact are the simplicity of application, less dependence on boundary conditions, better controllability, and repeatability of the imparted damage. The tests were conducted using advanced instrumentation, including digital image correlation, passive thermography, and in situ ultrasonic scanning. Specimens with initial indentation damage ranging between 32 and 56 mm in length were tested quasi-statically and in fatigue, and the effects of cyclic load amplitude and damage size were studied. A means of comparison of the damage propagation rates and collapse loads based on a stress intensity measure and the Paris law is proposed. The stress intensity measure provides the means to compare the collapse loads of specimens with different damage types and damage sizes, while the Paris law is used to compare the damage propagation rates in specimens subjected to different cyclic loads. This approach enables a comparison of different tests and the potential identification of the effects that influence the fatigue lives and damage tolerance of postbuckled structures with defects.
Carlos G Dávila; Chiara Bisagni. Fatigue life and damage tolerance of postbuckled composite stiffened structures with indentation damage. Journal of Composite Materials 2017, 52, 931 -943.
AMA StyleCarlos G Dávila, Chiara Bisagni. Fatigue life and damage tolerance of postbuckled composite stiffened structures with indentation damage. Journal of Composite Materials. 2017; 52 (7):931-943.
Chicago/Turabian StyleCarlos G Dávila; Chiara Bisagni. 2017. "Fatigue life and damage tolerance of postbuckled composite stiffened structures with indentation damage." Journal of Composite Materials 52, no. 7: 931-943.
Ditching, which is a controlled landing of an airplane on water, is an emergency condition to be investigated in order to improve the aircraft global crashworthiness. The complex hydrodynamic phenomena involved in ditching events are difficult to simulate and the accuracy of the results depends on the capability to reproduce the forces related to the interaction of the fuselage with the water surface. In the first part of the paper, the vertical impact on water of a rigid sphere is analysed using the explicit solver LS-DYNA in order to compare different modelling strategies. Four models of the fluid domain are presented: Lagrangian, arbitrary Lagrangian–Eulerian, smoothed particle hydrodynamics and hybrid Lagrangian-smoothed particle hydrodynamics. In the second part, the ditching of a scaled simplified airplane is simulated considering two different models for the water region. Experimental data from the literature are used to validate the simulations. The analysis, where the water and the air are modelled with the arbitrary Lagrangian–Eulerian method, shows a better correlation with the experimental data because this formulation can reproduce the suction force which acts on the fuselage and affects significantly the ditching dynamics.
C. Bisagni; M.S. Pigazzini. Modelling strategies for numerical simulation of aircraft ditching. International Journal of Crashworthiness 2017, 23, 377 -394.
AMA StyleC. Bisagni, M.S. Pigazzini. Modelling strategies for numerical simulation of aircraft ditching. International Journal of Crashworthiness. 2017; 23 (4):377-394.
Chicago/Turabian StyleC. Bisagni; M.S. Pigazzini. 2017. "Modelling strategies for numerical simulation of aircraft ditching." International Journal of Crashworthiness 23, no. 4: 377-394.
An experimental study has been carried out to investigate the behaviour of co-bonded carbon fibre reinforced plastics joints with a novel design incorporating a through the thickness local reinforcement. Different specimens were manufactured to investigate static and fatigue behaviour, as well as delamination size after impact and damage tolerance characteristics. The mechanical performances of the specimens with local reinforcement, consisting of the insertion of spiked thin metal sheets between co-bonded laminates, were compared with those ones obtained from specimens with purely co-bonded joints. This novel design demonstrated by tests that damage progression under cycling load results significantly delayed by the reinforcements. A significant number of experimental results were obtained that can be used to define preliminary design guidelines.
Chiara Bisagni; Domenico Furfari; Marco Pacchione. Experimental investigation of reinforced bonded joints for composite laminates. Journal of Composite Materials 2017, 52, 431 -447.
AMA StyleChiara Bisagni, Domenico Furfari, Marco Pacchione. Experimental investigation of reinforced bonded joints for composite laminates. Journal of Composite Materials. 2017; 52 (4):431-447.
Chicago/Turabian StyleChiara Bisagni; Domenico Furfari; Marco Pacchione. 2017. "Experimental investigation of reinforced bonded joints for composite laminates." Journal of Composite Materials 52, no. 4: 431-447.
A series of experimental tests have been carried out on three types of novel sandwich panels mainly designed for application in lightweight mobile housing. Two types of the panels are manufactured entirely from wood-based materials while the third one presents a combination of plywood for surfaces and corrugated thermoplastic composite as a core part. All sandwich panels are designed to allow rapid one-shot manufacturing. Mechanical performance has been evaluated in four-point bending comparing the data to the reference plywood board. Additionally, finite element simulations were performed to evaluate global behavior, stress distribution and provide the basis for a reliable design tool. Obtained results show sufficient mechanical characteristics suitable for floor and wall units. Compared to a solid plywood board, sandwich alternative can reach up to 42% higher specific stiffness, at the same time maintaining sufficient strength characteristics.
Edgars Labans; Kaspars Kalnins; Chiara Bisagni. Flexural behavior of sandwich panels with cellular wood, plywood stiffener/foam and thermoplastic composite core. Journal of Sandwich Structures & Materials 2017, 21, 784 -805.
AMA StyleEdgars Labans, Kaspars Kalnins, Chiara Bisagni. Flexural behavior of sandwich panels with cellular wood, plywood stiffener/foam and thermoplastic composite core. Journal of Sandwich Structures & Materials. 2017; 21 (2):784-805.
Chicago/Turabian StyleEdgars Labans; Kaspars Kalnins; Chiara Bisagni. 2017. "Flexural behavior of sandwich panels with cellular wood, plywood stiffener/foam and thermoplastic composite core." Journal of Sandwich Structures & Materials 21, no. 2: 784-805.
The paper presents a probabilistic methodology for the buckling analysis of sandwich composite cylindrical shells. The sensitivity to experimentally-measured imperfections is probabilistically assessed in terms of a loading factor, named probabilistic buckling factor. This factor corresponds to a required level of probability that shell withstands compressive load, and allows for a first evaluation of the buckling response and the imperfection sensitivity of the shells. In particular, the imperfections considered in this study include geometric imperfections, thickness variation, ply misalignment and boundary imperfections. An application is reported taking into account the geometric imperfections and thickness variation measured on a scaled shell of the Dual Launch System (SYLDA) of Ariane 5 launcher. Because only a scaled shell was available and was measured, the probabilistic buckling factor here obtained cannot be considered as the lower bound factor for the buckling response of the cylindrical shells manufactured nominally-identical to the SYLDA shell, but nevertheless allows to illustrating the complete methodology
Chiara Bisagni; Michela Alfano. Probabilistic Buckling Analysis of Sandwich Composite Cylindrical Shells based on Measured Imperfections. 58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference 2017, 1 .
AMA StyleChiara Bisagni, Michela Alfano. Probabilistic Buckling Analysis of Sandwich Composite Cylindrical Shells based on Measured Imperfections. 58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. 2017; ():1.
Chicago/Turabian StyleChiara Bisagni; Michela Alfano. 2017. "Probabilistic Buckling Analysis of Sandwich Composite Cylindrical Shells based on Measured Imperfections." 58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference , no. : 1.
The objective of the running EU project DESICOS (New Robust DESign Guideline for Imperfection Sensitive COmposite Launcher Structures) is to formulate an improved shell design methodology in order to meet the demand of aerospace industry for lighter structures. Within the project, this article discusses the development of a probability-based methodology developed at Politecnico di Milano. It is based on the combination of the Stress–Strength Interference Method and the Latin Hypercube Method with the aim to predict the bucking response of three sandwich composite cylindrical shells, assuming a loading condition of pure compression. The three shells are made of the same material, but have different stacking sequence and geometric dimensions. One of them presents three circular cut-outs. Different types of input imperfections, treated as random variables, are taken into account independently and in combination: variability in longitudinal Young's modulus, ply misalignment, geometric imperfections, and boundary imperfections. The methodology enables a first assessment of the structural reliability of the shells through the calculation of a probabilistic buckling factor for a specified level of probability. The factor depends highly on the reliability level, on the number of adopted samples, and on the assumptions made in modeling the input imperfections. The main advantage of the developed procedure is the versatility, as it can be applied to the buckling analysis of laminated composite shells and sandwich composite shells including different types of imperfections.
M. Alfano; C. Bisagni. Probability-based methodology for buckling investigation of sandwich composite shells with and without cut-outs. International Journal for Computational Methods in Engineering Science and Mechanics 2017, 18, 77 -90.
AMA StyleM. Alfano, C. Bisagni. Probability-based methodology for buckling investigation of sandwich composite shells with and without cut-outs. International Journal for Computational Methods in Engineering Science and Mechanics. 2017; 18 (1):77-90.
Chicago/Turabian StyleM. Alfano; C. Bisagni. 2017. "Probability-based methodology for buckling investigation of sandwich composite shells with and without cut-outs." International Journal for Computational Methods in Engineering Science and Mechanics 18, no. 1: 77-90.
The paper proposes an optimisation strategy for the design of structures made of three-dimensional woven composites. The knowledge of the weaving architecture is essential to properly optimise the design of the structural components subjected to specific load conditions. Owing to the hierarchy and periodicity of the textile composite materials, a multi-scale parameterisation modelling strategy combining the adoption of a representative volume element and periodic boundary conditions is employed to estimate the behaviour of stiffened panels. In order to minimise the expensive computational cost, response surface method techniques are used to generate the approximated structural responses in an efficient and applicable way. The approach here proposed consists of a multi-scale parameterization analysis strategy and an optimisation framework based on the response surface technique and genetic algorithms. The optimal design results are verified by finite element analysis proving that the response surface method integrated with genetic algorithms allows to easily investigate the influence of the fabrics constitutive parameters on the structural behaviour
Xinwei Fu; Sergio Ricci; Chiara Bisagni. Multi-scale analysis and optimisation of three-dimensional woven composite structures combining response surface method and genetic algorithms. CEAS Aeronautical Journal 2016, 8, 129 -141.
AMA StyleXinwei Fu, Sergio Ricci, Chiara Bisagni. Multi-scale analysis and optimisation of three-dimensional woven composite structures combining response surface method and genetic algorithms. CEAS Aeronautical Journal. 2016; 8 (1):129-141.
Chicago/Turabian StyleXinwei Fu; Sergio Ricci; Chiara Bisagni. 2016. "Multi-scale analysis and optimisation of three-dimensional woven composite structures combining response surface method and genetic algorithms." CEAS Aeronautical Journal 8, no. 1: 129-141.
A semi-analytical approach is presented for the analysis and optimization of laminated panels with non-symmetric lay-ups, and with the possibility of introducing requirements on the buckling load, the postbuckling response and the eigenfrequencies. The design strategy relies on the combined use of semi-analytical techniques for the structural analysis and genetic algorithms for the optimization. The structural analysis is performed with a highly efficient code based on thin plate theory, where the problem is formulated in terms of Airy stress function and out of plane displacement, expanded using trigonometric series. Eigenvalue analyses are performed to determine eigenfrequencies and buckling load, while an arc-length method is adopted for the postbuckling computation. The genetic algorithm is implemented with proper alphabet cardinalities to handle different steps for the angles of orientation, while specific mutation operators are used to guarantee good reliability of the optimization. To show the potentialities of the proposed optimization toolbox, two examples are presented regarding the design of balanced non-symmetric laminates subjected to linear and nonlinear constraints. The accuracy of the semi-analytical predictions is demonstrated by comparison with finite element results and benchmark cases taken from the literature.
Riccardo Vescovini; Chiara Bisagni. Fast analysis of non-symmetric panels using semi-analytical techniques. Composites Part B: Engineering 2016, 99, 48 -62.
AMA StyleRiccardo Vescovini, Chiara Bisagni. Fast analysis of non-symmetric panels using semi-analytical techniques. Composites Part B: Engineering. 2016; 99 ():48-62.
Chicago/Turabian StyleRiccardo Vescovini; Chiara Bisagni. 2016. "Fast analysis of non-symmetric panels using semi-analytical techniques." Composites Part B: Engineering 99, no. : 48-62.
The paper describes a modeling strategy for multi-scale analysis and optimization of stiffened panels, made of three-dimensional woven composites. Artificial neural network techniques are utilized to generate an approximate response for the optimum structural design in order to increase efficiency and applicability. The artificial neural networks are integrated with genetic algorithms to optimize mixed discrete–continuous design variables for the three dimensional woven composite structures. The proposed procedure is then applied to the multi-objective optimal design of a stiffened panel subject to buckling and post-buckling requirements
Xinwei Fu; Sergio Ricci; Chiara Bisagni. Minimum-weight design for three dimensional woven composite stiffened panels using neural networks and genetic algorithms. Composite Structures 2015, 134, 708 -715.
AMA StyleXinwei Fu, Sergio Ricci, Chiara Bisagni. Minimum-weight design for three dimensional woven composite stiffened panels using neural networks and genetic algorithms. Composite Structures. 2015; 134 ():708-715.
Chicago/Turabian StyleXinwei Fu; Sergio Ricci; Chiara Bisagni. 2015. "Minimum-weight design for three dimensional woven composite stiffened panels using neural networks and genetic algorithms." Composite Structures 134, no. : 708-715.
H. Abramovich; Chiara Bisagni. Behavior of curved laminated composite panels and shells under axial compression. Progress in Aerospace Sciences 2015, 78, 74 -106.
AMA StyleH. Abramovich, Chiara Bisagni. Behavior of curved laminated composite panels and shells under axial compression. Progress in Aerospace Sciences. 2015; 78 ():74-106.
Chicago/Turabian StyleH. Abramovich; Chiara Bisagni. 2015. "Behavior of curved laminated composite panels and shells under axial compression." Progress in Aerospace Sciences 78, no. : 74-106.
Thomas Ludwig; Mathias Doreille; Silvio Merazzi; Riccardo Vescovini; Chiara Bisagni. Dynamic finite element simulations of composite stiffened panels with a transverse-isotropic viscoelastic energy dissipation model. Progress in Aerospace Sciences 2015, 78, 30 -38.
AMA StyleThomas Ludwig, Mathias Doreille, Silvio Merazzi, Riccardo Vescovini, Chiara Bisagni. Dynamic finite element simulations of composite stiffened panels with a transverse-isotropic viscoelastic energy dissipation model. Progress in Aerospace Sciences. 2015; 78 ():30-38.
Chicago/Turabian StyleThomas Ludwig; Mathias Doreille; Silvio Merazzi; Riccardo Vescovini; Chiara Bisagni. 2015. "Dynamic finite element simulations of composite stiffened panels with a transverse-isotropic viscoelastic energy dissipation model." Progress in Aerospace Sciences 78, no. : 30-38.