Relevant bibliographies by topics / Stiffened composite panel

Academic literature on the topic 'Stiffened composite panel'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 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 'Stiffened composite panel.'

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 "Stiffened composite panel"

1

Shao, Qing, Yu Ting He, Teng Zhang, Hai Wei Zhang, and Qing Shan Kang. "Simulation of Compress Buckling Performance of Composite Stiffened Panel." Applied Mechanics and Materials 184-185 (June 2012): 1189–93. http://dx.doi.org/10.4028/www.scientific.net/amm.184-185.1189.

Full text
Abstract:
Finite element method is applied to analyze the buckling performance of composite stiffened panel. Compress buckling critical loads of six types panels with T or Z-section stiffeners are calculated by FEM. The emulational calculation results show that with same cross section area, critical buckling load of panel with T-section stiffeners increases with the reduction of stiffener pitch and the increase of stiffener numbers, while the buckling load of panel with Z-section stiffeners increases to a certain level and then keep almost changeless. To T-section stiffener panels, the relation between thickness of skin and buckling load is approximately quadratic trinominal. Conclusions obtained can offer a referenced measure for the optimization design and engineering application of the structure.
APA, Harvard, Vancouver, ISO, and other styles
2

Moorhouse, Anna, Micah Shepherd, and Benjamin S. Beck. "Incorporation of acoustic black hole stiffeners into composite airframes for reduction of noise radiation." Journal of the Acoustical Society of America 151, no. 4 (April 2022): A129—A130. http://dx.doi.org/10.1121/10.0010875.

Full text
Abstract:
Stiffened composite panels are commonly used in aerospace structures, because they are lightweight, while maintaining a high load-bearing ability. However, their high stiffness-to-mass ratio makes them efficient noise radiators. In rotorcraft cabins made with composite panels, for example, the internal noise levels can be quite high such that pilot and passenger communication and comfort are disrupted. This has led to a need for innovative noise reduction strategies for composite rotorcraft panels. A specialized stiffener, which incorporates the acoustic black hole (ABH) effect into the cross section, is proposed to improve the damping of stiffened composite panels. By incorporating the damping concept into the stiffeners, the panel’s radiated noise can be reduced while maintaining the weight advantages and panel strength. To determine the advantages and trade-offs of this concept, numerical models have been developed and incorporated into an optimization scheme. Computational studies reveal promising results from the optimized ABH stiffeners as compared to a baseline panel with traditional stiffeners.
APA, Harvard, Vancouver, ISO, and other styles
3

Zhao, Chuang, Zhi Dong Guan, and Xia Guo. "Compression Performance of Repaired Composite Stiffened Panels: Bolted Repair and Scarfed Bonded Repair." Materials Science Forum 813 (March 2015): 152–60. http://dx.doi.org/10.4028/www.scientific.net/msf.813.152.

Full text
Abstract:
In this paper, compression performance of composite stiffened panels after bolted repair and scarfed bonded repair is presented. Several tests have been performed on the four kinds of stiffened panels. All the experiments show the influences of different damage actions, different repair methods for the mechanical properties of stiffened panels are different. Furthermore, numerical finite element models have been developed and solved using the software ABAQUS. In addition, stiffener-skin debonding was considered in the finite element models in order to ensure a better consistence with the fact. The comparison of simulation results and experiment shows that the finite element modeling method is effective. The result suggests that the failure load and the stiffness of the repaired stiffened panel are recovered close to the virgin ones’.
APA, Harvard, Vancouver, ISO, and other styles
4

Liu, Jun, Bao Zong Huang, and Ge Lan Li. "Secondary Buckling and Progressive Failure Analysis of Tailored Composite Panels in Thin-Walled Box-Shape Composite Beams under Bending and Torsion." Advanced Materials Research 41-42 (April 2008): 445–48. http://dx.doi.org/10.4028/www.scientific.net/amr.41-42.445.

Full text
Abstract:
The postbuckling behavior and progressive failure of thin-walled box-shape composite beams (BSCBs) have been studied using a simplified composite panel model. It is shown that the carrying capacity of BSCBs under bending and torsion mainly depends on the postbuckling and progressive failure of panels. It is often necessary to identify and follow secondary buckling of tailored panels for correct estimation of carrying capacity. The failure process of stiffened composite panels is simulated in following path. The criterion of local failure in flange of stiffeners is applied to predict the ultimate failure of stiffened composite panels and thin-walled BSCBs. The comparison of the modeling and test shows that the prediction of BSCBs failure is satisfactory.
APA, Harvard, Vancouver, ISO, and other styles
5

Cherniaev, Aleksandr. "A new laminates encoding scheme for the genetic algorithm-based optimization of stiffened composite panels." Engineering Computations 31, no. 1 (February 25, 2014): 33–47. http://dx.doi.org/10.1108/ec-08-2011-0089.

Full text
Abstract:
Purpose – The genetic algorithm (GA) technique is widely used for the optimization of stiffened composite panels. It is based on sequential execution of a number of specific operators, including the encoding of particular design variables. For instance, in the case of a stiffened composite panel, the design variables that need to be encoded are: the number of plies and their stacking sequences in the panel skin and stiffeners. This paper aims to present a novel, implicit, heuristic approach for encoding composite laminates and, through its use, demonstrates an improvement in the optimization process. Design/methodology/approach – The stiffened panel optimization has been formulated as a constrained discrete minimum-weight design problem. GAs, which use both new encoding schemes and those previously described in the literature, have been used to find near-optimal solutions to the formulated problem. The influence of the new encoding scheme on the searching capabilities of the GA has been investigated using comparative analysis of the optimization results. Findings – The new encoding scheme allows the definition of stacking sequences in composites using shorter symbolic representations as compared with standard encoding operators and, as a result of this, a reduction in the problem design space. According to numerical experiments performed in this work, this feature enables GA to obtain near-optimal designs using smaller population sizes than those required if standard encoding schemes are used. Originality/value – The approach to encoding laminates presented in this paper is based on the original heuristics. In the context of GA-based optimization of stiffened composite panels, the use of the new approach rather than the standard encoding technique can lead to a significant reduction in computational time employed.
APA, Harvard, Vancouver, ISO, and other styles
6

Sanchez-Carmona, Alejandro, and Cristina Cuerno-Rejado. "Composite stiffened panel sizing for conceptual tail design." Aircraft Engineering and Aerospace Technology 90, no. 8 (November 5, 2018): 1272–81. http://dx.doi.org/10.1108/aeat-05-2017-0129.

Full text
Abstract:
Purpose A conceptual design method for composite material stiffened panels used in aircraft tail structures and unmanned aircraft has been developed to bear compression and shear loads. Design/methodology/approach The method is based on classical laminated theory to fulfil the requirement of building a fast design tool, necessary for this preliminary stage. The design criterion is local and global buckling happen at the same time. In addition, it is considered that the panel does not fail due to crippling, stiffeners column buckling or other manufacturing restrictions. The final geometry is determined by minimising the area and, consequently, the weight of the panel. Findings The results obtained are compared with a classical method for sizing stiffened panels in aluminium. The weight prediction is validated by weight reductions in aircraft structures when comparing composite and aluminium alloys. Research limitations/implications The work is framed in conceptual design field, so hypotheses like material or stiffeners geometry shall be taken a priori. These hypotheses can be modified if it is necessary, but even so, the methodology continues being applicable. Practical implications The procedure presented in this paper allows designers to know composite structure weight of aircraft tails in commercial aviation or any lifting surface in unmanned aircraft field, even for unconventional configurations, in early stages of the design, which is an aid for them. Originality/value The contribution of this paper is the development of a new rapid methodology for conceptual design of composite panels and the feasible application to aircraft tails and also to unmanned aircraft.
APA, Harvard, Vancouver, ISO, and other styles
7

Sahadevan, Vijay, Yoann Bonnefon, and Tim Edwards. "A Meta-Heuristic Based Weight Optimisation for Composite Wing Structural Analysis." Applied Mechanics and Materials 5-6 (October 2006): 305–14. http://dx.doi.org/10.4028/www.scientific.net/amm.5-6.305.

Full text
Abstract:
This paper presents a two-stage meta-heuristic approach to producing weight-optimised solutions needed prior to the detailed finite element analysis of composite wing. Composite wing covers are assumed to take the form of a group of stiffened sub-panels with varying skin and stiffener geometries according to the wing layout and loads. A population of limited solutions satisfying various design constraints was created using layout (skin and stiffener geometry), selected lay-ups, rule based stacking sequence and various assumed loads. The closed form analytical solutions of flat stiffened orthotropic plates are used for calculating buckling reserve factors and strength margins. For each sub-panel, a meta-heuristic rule was imposed to search for a suitable combination of skin and stiffener geometry. The criterion used was minimum weight satisfying laminate continuity accounting for manufacturability. Later, the optimised solutions for each sub-panel are converted into a format supported by the conventional finite element tool (NASTRAN). The use of meta-heuristic approach and their automation in Visual Basic for Applications resulted in fast convergence and potential time-saving compared to genetic algorithms.
APA, Harvard, Vancouver, ISO, and other styles
8

Li, Yeou-Fong, Habib Meda, and Walter Chen. "The Design and Analysis of Internally Stiffened GFRP Tubular Decks—A Sustainable Solution." Sustainability 10, no. 12 (December 1, 2018): 4538. http://dx.doi.org/10.3390/su10124538.

Full text
Abstract:
The aim of this paper was to find an optimal stiffener configuration of thin-wall tubular panels made by glass fiber reinforced polymer (GFRP) composite material, which is a low carbon emission, low life cycle cost, and sustainable material. Finite-element analysis (FEA) was used to investigate the flexural and torsional stiffness of various internally stiffened sections of thin-wall GFRP decks. These decks consist of internally stiffened tubular profiles laid side by side and bonded together with epoxy to ensure the panel acts as an assembly. Three-dimensional models of the seven proposed decks were assembled with tubular profiles of different stiffener patterns. First, the non-stiffened tube profile was tested experimentally to validate the parameters used in the subsequent numerical analysis. Then, the finite element software, ANSYS, was used to simulate the flexural and torsional behavior of the decks with different stiffener patterns under bending and torsional loads. The decks with stiffener patterns such as “O” type, “V” type, and “D” type were found to be the most effective in bending. For torsion, there was a distinct tendency for deck panels with closed shaped stiffener patterns to perform better than their counterparts. Overall, the “O” type deck panel was an optimal stiffener configuration.
APA, Harvard, Vancouver, ISO, and other styles
9

Guofan, Zhang, Wan Chunhua, and Nie Xiaohua. "Study on compressive bearing capacity and efficiency of composite stiffened panels with different cross-sections." Journal of Physics: Conference Series 2336, no. 1 (August 1, 2022): 012027. http://dx.doi.org/10.1088/1742-6596/2336/1/012027.

Full text
Abstract:
Abstract The post-buckling behavior and load bearing efficiency of composite panels with three kinds of stiffeners subject to the axial compression load were investigated. The progressive damage analysis models considering the failure of fiber/matrix, debonding of adhesive interface and stiffness degradation were established. The buckling load, failure load and failure process for three types of stiffened panels were derived. The numerical results coincide with tests, and the relative errors are all less than 6%, which indicates the FEM model given in this paper is reliable and practical. Further, the load bearing efficiency of these three kinds of stiffened panels with the same weight was discussed. Results reveal that the bearing capacity and efficiency of I-shape stiffened panel is the highest, and its bearing efficiency reaches 154.5N/g. The results of the paper provide a reference for engineering application of composite stiffened structure design.
APA, Harvard, Vancouver, ISO, and other styles
10

KALNINS, KASPARS, ROLANDS RIKARDS, JANIS AUZINS, CHIARA BISAGNI, HAIM ABRAMOVICH, and RICHARD DEGENHARDT. "METAMODELING METHODOLOGY FOR POSTBUCKLING SIMULATION OF DAMAGED COMPOSITE STIFFENED STRUCTURES WITH PHYSICAL VALIDATION." International Journal of Structural Stability and Dynamics 10, no. 04 (October 2010): 705–16. http://dx.doi.org/10.1142/s0219455410003695.

Full text
Abstract:
A metamodeling methodology has been proposed for postbuckling simulation of stiffened composite structures with integrated degradation scenarios. The presence of artificial damage between the outer skin and stiffeners has been simulated as softening of the material properties in predetermined regions of the structure. The proposed methodology for the fast design procedure of axially or torsionally loaded stiffened composite structures is based on response surface methodology (RSM) and design and analysis of computer experiments (DACE). Numerical analyses have been parametrically sampled by means of the ANSYS/LS-DYNA probabilistic design toolbox extracting the load-shortening response curves in the preselected domain of interest. These response curves have been simplified using piecewise linear approximation identifying the buckling and postbuckling stiffness ratios along with the values of the skin and the stiffener buckling loads. Three stiffened panel designs and a closed box structure with preselected damage scenarios have been elaborated and validated with the tests performed within the COCOMAT project. The resulting design procedure provides a time-effective design tool for preliminary study and for elaboration of the optimum design guidelines for composite stiffened structures with material degradation restraints.
APA, Harvard, Vancouver, ISO, and other styles
More sources

Dissertations / Theses on the topic "Stiffened composite panel"

1

Liu, Yifei. "Optimum design of a composite outer wing subject to stiffness and strength constraints." Thesis, Cranfield University, 2011. http://dspace.lib.cranfield.ac.uk/handle/1826/6833.

Full text
Abstract:
Composite materials have been more and more used in aircraft primary structures such as wing and fuselage. The aim of this thesis is to identify an effective way to optimize composite wing structure, especially the stiffened skin panels for minimum weight subject to stiffness and strength constraints. Many design variables (geometrical dimensions, ply angle proportion and stacking sequence) are involved in the optimum design of a composite stiffened panel. Moreover, in order to meet practical design, manufacturability and maintainability requirements should be taken into account as well, which makes the optimum design problem more complicated. In this thesis, the research work consists of three steps: Firstly, attention is paid to metallic stiffened panels. Based on the study of Emero’s optimum design method and buckling analysis, a VB program IPO, which employs closed form equations to obtain buckling load, is developed to facilitate the optimization process. The IPO extends the application of Emero’s method to an optimum solution based on user defined panel dimensional range to satisfy practical design constraints. Secondly, the optimum design of a composite stiffened panel is studied. Based on the research of laminate layup effects on buckling load and case study of bucking analysis methods, a practical laminate database (PLDB) concept is presented, upon which the optimum design procedure is established. By employing the PLDB, laminate equivalent modulus and closed form equations, a VB program CPO is developed to achieve the optimum design of a composite stiffened panel. A multi-level and step-length-adjustable optimization strategy is applied in CPO, which makes the optimization process efficient and effective. Lastly, a composite outer wing box, which is related to the author’s GDP work, is optimized by CPO. Both theoretical and practical optimum solutions are obtained and the results are validated by FE analysis.
APA, Harvard, Vancouver, ISO, and other styles
2

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
3

Jrad, Mohamed. "Multidisciplinary Optimization and Damage Tolerance of Stiffened Structures." Diss., Virginia Tech, 2015. http://hdl.handle.net/10919/52276.

Full text
Abstract:
The structural optimization of a cantilever aircraft wing with curvilinear spars and ribs and stiffeners is described. The design concept of reinforcing the wing structure using curvilinear stiffening members has been explored due to the development of novel manufacturing technologies like electron-beam-free-form-fabrication (EBF3). For the optimization of a complex wing, a common strategy is to divide the optimization procedure into two subsystems: the global wing optimization which optimizes the geometry of spars, ribs and wing skins; and the local panel optimization which optimizes the design variables of local panels bordered by spars and ribs. The stiffeners are placed on the local panels to increase the stiffness and buckling resistance. The panel thickness, size and shape of stiffeners are optimized to minimize the structural weight. The geometry of spars and ribs greatly influences the design of stiffened panels. During the local panel optimization, the stress information is taken from the global model as a displacement boundary condition on the panel edges using the so-called "Global-Local Approach". The aircraft design is characterized by multiple disciplines: structures, aeroelasticity and buckling. Particle swarm optimization is used in the integration of global/local optimization to optimize the SpaRibs. The interaction between the global wing optimization and the local panel optimization is usually computationally expensive. A parallel computing technology has been developed in Python programming to reduce the CPU time. The license cycle-check method and memory self-adjustment method are two approaches that have been applied in the parallel framework in order to optimize the use of the resources by reducing the license and memory limitations and making the code robust. The integrated global-local optimization approach has been applied to subsonic NASA common research model (CRM) wing, which proves the methodology's application scaling with medium fidelity FEM analysis. Both the global wing design variables and local panel design variables are optimized to minimize the wing weight at an acceptable computational cost. The structural weight of the wing has been, therefore, reduced by 40% and the parallel implementation allowed a reduction in the CPU time by 89%. The aforementioned Global-Local Approach is investigated and applied to a composite panel with crack at its center. Because of composite laminates' heterogeneity, an accurate analysis of these requires very high time and storage space. In the presence of structural discontinuities like cracks, delaminations, cutouts etc., the computational complexity increases significantly. A possible alternative to reduce the computational complexity is the global-local analysis which involves an approximate analysis of the whole structure followed by a detailed analysis of a significantly smaller region of interest. We investigate here the performance of the global-local scheme based on the finite element method by comparing it to the traditional finite element method. To do so, we conduct a 2D structural analysis of a composite square plate, with a thin rectangular notch at its center, subjected to a uniform transverse pressure, using the commercial software ABAQUS. We show that the presence of the thin notch affects only the local response of the structure and that the size of the affected area depends on the notch length. We investigate also the effect of the notch shape on the response of the structure. Stiffeners attached to composite panels may significantly increase the overall buckling load of the resultant stiffened structure. Buckling analysis of a composite panel with attached longitudinal stiffeners under compressive loads is performed using Ritz method with trigonometric functions. Results are then compared to those from ABAQUS FEA for different shell elements. The case of composite panel with one, two, and three stiffeners is investigated. The effect of the distance between the stiffeners on the buckling load is also studied. The variation of the buckling load and buckling modes with the stiffeners' height is investigated. It is shown that there is an optimum value of stiffeners' height beyond which the structural response of the stiffened panel is not improved and the buckling load does not increase. Furthermore, there exist different critical values of stiffener's height at which the buckling mode of the structure changes. Next, buckling analysis of a composite panel with two straight stiffeners and a crack at the center is performed. Finally, buckling analysis of a composite panel with curvilinear stiffeners and a crack at the center is also conducted. ABAQUS is used for these two examples and results show that panels with a larger crack have a reduced buckling load. It is shown also that the buckling load decreases slightly when using higher order 2D shell FEM elements. A damage tolerance framework, EBF3PanelOpt, has been developed to design and analyze curvilinearly stiffened panels. The framework is written with the scripting language PYTHON and it interacts with the commercial software MSC. Patran (for geometry and mesh creation), MSC. Nastran (for finite element analysis), and MSC. Marc (for damage tolerance analysis). The crack location is set to the location of the maximum value of the major principal stress while its orientation is set normal to the major principal axis direction. The effective stress intensity factor is calculated using the Virtual Crack Closure Technique and compared to the fracture toughness of the material in order to decide whether the crack will expand or not. The ratio of these two quantities is used as a constraint, along with the buckling factor, Kreisselmeier and Steinhauser criteria, and crippling factor. The EBF3PanelOpt framework is integrated within a two-step Particle Swarm Optimization in order to minimize the weight of the panel while satisfying the aforementioned constraints and using all the shape and thickness parameters as design variables. The result of the PSO is used then as an initial guess for the Gradient Based Optimization using only the thickness parameters as design variables. The GBO is applied using the commercial software VisualDOC.
Ph. D.
APA, Harvard, Vancouver, ISO, and other styles
4

Shenoy, Sudhir Lankarani Hamid M. "Energy absorption of a car roof reinforced with a grid stiffened composite panel in the event of a rollover." Diss., Click here for available full-text of this thesis, 2006. http://library.wichita.edu/digitallibrary/etd/2006/t073.pdf.

Full text
Abstract:
Thesis (M.S.)--Wichita State University, College of Engineering.
"May 2006." Title from PDF title page (viewed on October 29, 2006). Thesis adviser: Hamid M. Lankarani. Includes bibliographic references (leaves 57-59).
APA, Harvard, Vancouver, ISO, and other styles
5

Shenoy, Sudhir Shivaraya. "Energy absorption of a car roof reinforced with a grid stiffened composite panel in the event of a rollover." Thesis, Wichita State University, 2006. http://hdl.handle.net/10057/386.

Full text
Abstract:
Rollovers tend to be very severe crashes because of the energy required to roll a vehicle over unlike front and side crashes. This study is an effort towards reducing the severity of a rollover crash by strengthening the roof of a passenger car. The main focus of this thesis is to study the effect of reinforcing the roof of a car, in the event of a rollover. An Eglass/polypropylene isogrid composite panel, which is known for high specific energy absorption under impact, is used in reinforcing the roof of a ford Taurus car and the force-displacement response of the roof structure is observed in contrast to the same while without the roof reinforcement. The non-linear Finite Element Analysis (FEA) simulation of this rollover event is performed in LS DYNA computer code. The simulation setup is done in accordance with Federal Motor Vehicle Standard (FMVSS) No. 216, which is a static study of roof strength in the case of rollover accidents. A study of roof strength characteristics under dynamic loading, involving rollover forces and velocities, is also carried out. The simulation in the latter case involves dropping the car, inverted at a certain pitch and roll offset against gravity from a certain predetermined height onto a concrete surface. The results of the above simulations show that Isogrid composite panels are excellent reinforcements for a car roof, stiffening the roof and increasing its resistance to crush in a rollover accident. This study will help in recommending the use of isogrid panels in the design of car roofs with better roof crush characteristics.
Thesis (M.S.)--Wichita State University, College of Engineering, Dept. of Mechanical Engineering
"May 2006."
Includes bibliographic references (leaves 57-59)
APA, Harvard, Vancouver, ISO, and other styles
6

Cil, Kursad. "Free Flexural (or Bending) Vibrations Analysis Of Doubly Stiffened, Composite, Orthotropic And/or Isotropic Base Plates And Panels (in Aero-structural Systems)." Master's thesis, METU, 2003. http://etd.lib.metu.edu.tr/upload/2/1062256/index.pdf.

Full text
Abstract:
In this Thesis, the problem of the Free Vibrations Analysis of Doubly Stiffened Composite, Orthotropic and/or Isotropic, Base Plates or Panels (with Orthotropic Stiffening Plate Strips) is investigated. The composite plate or panel system is made of an Orthotropic and/or Isotropic Base Plate stiffened or reinforced by adhesively bonded Upper and Lower Orthotropic Stiffening Plate Strips. The plates are assumed to be the Mindlin Plates connected by relatively very thin adhesive layers. The general problem under study is considered in terms of three problems, namely Main PROBLEM I Main PROBLEM II and Main PROBLEM III. The theoretical formulation of the Main PROBLEMS is based on a First Order Shear Deformation Plate Theory (FSDPT) that is, in this case, the Mindlin Plate Theory. The entire composite system is assumed to have simple supports along the two opposite edges so that the Classical Levy'
s Solutions can be applied in that direction. Thus, the transverse shear deformations and the rotary moments of inertia of plates are included in the formulation. The very thin, yet elastic deformable adhesive layers are considered as continua with transverse normal and shear stresses. The damping effects in the plates and the adhesive layers are neglected. The sets of the systems of equations of the Mindlin Plate Theory are reduced to a set of the Governing System of First Order Ordinary Differential Equations in the state vector form. The sets of the Governing System for each Main PROBLEM constitute a Two-Point Boundary Value Problem in the y-direction which is taken along the length of the plates. Then, the system is solved by the Modified Transfer Matrix Method (with Interpolation Polynomials and/or Chebyshev Polynomials)which is a relatively semi-analytical and numerical technique. The numerical results and important parametric studies of the natural modes and the corresponding frequencies of the composite system are presented.
APA, Harvard, Vancouver, ISO, and other styles
7

Cohen, David. "Calculation of skin-stiffener interface stresses in stiffened composite panels." Diss., Virginia Polytechnic Institute and State University, 1987. http://hdl.handle.net/10919/82897.

Full text
Abstract:
A method for computing the skin-stiffener interface stresses in stiffened composite panels is developed. Both geometrically linear and nonlinear analyses are considered. Particular attention is given to the flange termination region where stresses are expected to exhibit unbounded characteristics. The method is based on a finite-element analysis and an elasticity solution. The finite-element analysis is standard, while the elasticity solution is based on an eigenvalue expansion of the stress functions. The eigenvalue expansion is assumed to be valid in the local flange termination region and is coupled with the finite-element analysis using collocation of stresses on the local region boundaries. In the first part of the investigation the accuracy and convergence of the local elasticity solution are assessed using a geometrically linear analysis. It is found that the finite-element/local elasticity solution scheme produce a very accurate interface stress representation in the local flange termination region. The use of 10 to 15 eigenvalues, in the eigenvalue expansion series, and 100 collocation points results in a converged local elasticity solution. In the second part of the investigation, the local elasticity solution is extended to include geometric nonlinearities. Using this analysis procedure, the influence of geometric nonlinearities on skin-stiffener interface stresses is evaluated. It is found that in flexible stiffened skin structures, which exhibit out-of-plane deformation on the order of 2 to 4 times the skin thickness, inclusion of geometrically nonlinear effects in the calculation of interface stresses is very important. Thus, the use of a geometrically linear analysis, rather than a nonlinear analysis, can lead to considerable error in the computation of the interface stresses. Finally, using the analytical tool developed in this investigation, it is possible to study the influence of stiffener parameters on the state of interface stresses.
Ph. D.
APA, Harvard, Vancouver, ISO, and other styles
8

Grall, Bruno. "Structural analysis of geodesically stiffened composite panels with variable stiffener distribution." Thesis, This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-12232009-020522/.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Uzman, Burak Jr. "Thermal Analysis and Response of Grid-Stiffened Composite Panels." Thesis, Virginia Tech, 1997. http://hdl.handle.net/10919/31381.

Full text
Abstract:
A study aimed at determining the thermal deformation response and thermal buckling loads of rectangular grid-stiffened composite panels is presented. Two edge conditions are considered for the panel, one in which all panel edges are free to deform, and another when all the edges are restrained. In the first case panel deformations due to a uniformly distributed thermal load are analyzed. In the latter case, thermal loads causing buckling failure due to the suppressed in-plane deformations are determined. The panel is composed of a skin and a network of stiffeners, which are all made of the same graphite-epoxy composite material. Kirchhoff's Theory is used to determine the pre-buckling deformations and load distributions of the composite laminates for a panel with free to deform edges. To illustrate both the in-plane and out-of-plane deformations of plate structures under uniform thermal loads, two thermal coefficient vectors, thermal expansion and thermal bending coefficient vectors are introduced. Linear panel buckling analysis performed by assuming a linear undeformed prebuckling state. Rayleigh-Ritz Method, which utilizes minimization of the total energy of a structure to determine the buckling loads, is used to govern the buckling analysis of composite laminates forming the panel. Lagrange Multiplier Method is used along with the Rayleigh-Ritz Method to enforce the deformation continuity constraints at discrete locations along the skin and stiffener interface. As a result, graphical and numerical presentations of the effects of skin and stiffener laminate stacking sequences on the thermal deformations and on the thermal buckling load of the grid-stiffened panel are given.
Master of Science
APA, Harvard, Vancouver, ISO, and other styles
10

Henderson, Joseph Lynn. "Combined structural and manufacturing optimization of stiffened composite panels." Thesis, This resource online, 1996. http://scholar.lib.vt.edu/theses/available/etd-09182008-063429/.

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

Books on the topic "Stiffened composite panel"

1

L, Phillips John. Structural analysis and optimum design of geodesically stiffened composite panels. Blacksburg, Va: Virginia Polytechnic Institute and State University, Center for Composite Materials and Structures, 1990.

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

Simitses, George J. Buckling of delaminated long panels under pressure and of radially-loaded stiffened annular plates. Atlanta, Ga: Georgia Institute of Technology, 1985.

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

Levon, Minnetyan, and United States. National Aeronautics and Space Administration., eds. Discontinuously stiffened composite panel under compressive loading. [Washington, DC: National Aeronautics and Space Administration, 1995.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
4

Detailed analysis and test correlation of a stiffened composite wing panel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1991.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
5

W, Hyer M., and United States. National Aeronautics and Space Administration., eds. Calculation of skin-stiffener interface stresses in stiffened composite panels. Blacksburg, Virginia: College of Engineering, Virginia Polytechnic Institute and State University, 1987.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
6

W, Hyer M., and United States. National Aeronautics and Space Administration, eds. Calculation of skin-stiffener interface stresses in stiffened composite panels. Blacksburg, Virginia: College of Engineering, Virginia Polytechnic Institute and State University, 1987.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
7

W, Hyer M., and United States. National Aeronautics and Space Administration, eds. Calculation of skin-stiffener interface stresses in stiffened composite panels. Blacksburg, Virginia: College of Engineering, Virginia Polytechnic Institute and State University, 1987.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
8

Calculation of skin-stiffener interface stresses in stiffened composite panels. Blacksburg, Virginia: College of Engineering, Virginia Polytechnic Institute and State University, 1987.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
9

Calculation of skin-stiffener interface stresses in stiffened composite panels. Blacksburg, Virginia: College of Engineering, Virginia Polytechnic Institute and State University, 1987.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
10

Structural analysis and design of geodesically stiffened composte panels with variable stiffener distribution. [Washington, DC: National Aeronautics and Space Administration, 1992.

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

Book chapters on the topic "Stiffened composite panel"

1

Wiggenraad, J. F. M., and N. R. Bauld. "Interlaminar Stress Analysis at the Skin/Stiffener Interface of a Grid-Stiffened Composite Panel." In Composite Structures, 415–31. Dordrecht: Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3662-4_32.

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

Tserpes, Konstantinos, Elli Moutsompegka, Mareike Schlag, Kai Brune, Christian Tornow, Ana Reguero Simón, and Romain Ecault. "Characterization of Pre-bond Contamination and Aging Effects for CFRP Bonded Joints Using Reference Laboratory Methods, Mechanical Tests, and Numerical Simulation." In Adhesive Bonding of Aircraft Composite Structures, 51–117. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-319-92810-4_2.

Full text
Abstract:
AbstractIn this chapter, the pre-bond contamination and ageing effects on carbon fiber reinforced plastic (CFRP) adherends and CFRP bonded joints are characterized by means of reference laboratory non-destructive testing (NDT) methods, mechanical tests, and numerical simulation. Contaminations from two fields of application are considered, namely in aircraft manufacturing (i.e. production) and for in-service bonded repair. The production-related scenarios comprise release agent, moisture, and fingerprint, while the repair-related scenarios comprise fingerprint, thermal degradation, de-icing fluid, and a faulty curing of the adhesive. For each scenario, three different levels of contamination were pre-set and applied, namely low, medium and high level. Furthermore, two types of samples were tested, namely coupons and pilot samples (a stiffened panel and scarf repairs). The CFRP adherends were contaminated prior to bonding and the obtained surfaces were characterized using X-ray photoelectron spectroscopy. After bonding, the joints were tested by ultrasonic testing. To characterize the effects of each contamination on the strength of the bonded joints, mode-I and mode-II fracture toughness tests, and novel centrifuge tests were conducted on the coupons, while tensile tests were performed on the scarfed samples. Additionally, numerical simulation was performed on CFRP stiffened panels under compression using the LS-DYNA finite element (FE) platform.
APA, Harvard, Vancouver, ISO, and other styles
3

Indira, Sai, D. Mallikarjuna Reddy, Jayakrishna Kandasamy, M. Rajesh, Vishesh Ranjan Kar, and M. T. H. Sultan. "Damage Characterization of Composite Stiffened Panel Subjected to Low Velocity Impact." In Structural Health Monitoring System for Synthetic, Hybrid and Natural Fiber Composites, 37–50. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-8840-2_4.

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

Park, Chan Yik. "Damage Index Comparison for a Composite Stiffened Panel Using Lamb Wave." In Advanced Materials Research, 1265–68. Stafa: Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-463-4.1265.

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

Bi, Xue, Peng Zou, and Xiangming Chen. "Study on Bearing Mechanism of Composite Stiffened Panel with Delamination Under Shear Load." In Mechanical Engineering and Materials, 155–72. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-68303-0_13.

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

El Samrout, Ahmad, Oussama Braydi, Rafic Younes, Francois Trouchu, and Pascal Lafon. "A New Hybrid Method to Solve the Multi-objective Optimization Problem for a Composite Hat-Stiffened Panel." In Bioinspired Heuristics for Optimization, 77–88. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-95104-1_5.

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

Smith, C. S., and R. S. Dow. "Interactive Buckling Effects in Stiffened FRP Panels." In Composite Structures 4, 122–37. Dordrecht: Springer Netherlands, 1987. http://dx.doi.org/10.1007/978-94-009-3455-9_9.

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

Smith, C. S., and R. S. Dow. "Compressive Strength of Longitudinally Stiffened GRP Panels." In Composite Structures 3, 468–90. Dordrecht: Springer Netherlands, 1985. http://dx.doi.org/10.1007/978-94-009-4952-2_33.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Tripathy, Biswajit, and K. P. Rao. "Optimum Design for Buckling of Plain and Stiffened Composite Cylindrical Panels." In Composite Structures, 371–81. Dordrecht: Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3662-4_29.

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

Chandra, K. S. Subash, T. Rajanna, and K. Venkata Rao. "Thermal Buckling Analysis of Stiffened Composite Cutout Panels." In Recent Trends in Construction Technology and Management, 935–48. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-2145-2_69.

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

Conference papers on the topic "Stiffened composite panel"

1

Kidane, Samuel, Eyassu Woldesenbet, Guoqiang Li, Jack Helms, and Brett H. Smith. "Preliminary Analysis of Grid Stiffened Composite Cylinders." In ASME 2002 Engineering Technology Conference on Energy. ASMEDC, 2002. http://dx.doi.org/10.1115/etce2002/ot-29153.

Full text
Abstract:
Stiffened cylindrical shells are major components of Aerospace structure application. Two models were developed for assessing the universal buckling load of a generally cross and horizontal stiffened composite cylinder. The first model uses a simple conservation of volume and direction of stiffener orientation, while the second model analyzes the force and moment interaction of the stiffeners and the shell. Based on these models the A, B and D matrix stiffness parameters were determined for the overall cylinder panel. The buckling load was solved for a particular stiffener configuration by using the energy method. Buckling test was also performed on a stiffened composite cylinder and compared with buckling load results of both analytical models, and conclusions were drawn on the degree of reliability of the models developed. Finally, parametric analysis of some of the important design variables was performed based on the ‘Force Smearing’ model.
APA, Harvard, Vancouver, ISO, and other styles
2

Yuceoglu, Umur, Jaber Javanshir, and O¨zen Guvendik. "On a General Approach to Free Vibrations Response of Integrally-Stiffened and/or Stepped-Thickness Rectangular Plates or Panels." In ASME 2008 International Mechanical Engineering Congress and Exposition. ASMEDC, 2008. http://dx.doi.org/10.1115/imece2008-66980.

Full text
Abstract:
This study is mainly concerned with a “General Approach” to the “Theoretical Analysis and the Solution of the Free Vibrations Response of Integrally-Stiffened and/or Stepped-Thickness Plates or Panels with Two or more Integral Plate Stiffeners”. In general, the “Stiffened System” (regardless of the number of “Plate Stiffeners”) is considered to be composed of dissimilar “Orthotropic Mindlin Plates” with unequal thicknesses. The dynamic governing equations of the individual plate elements of the “System” and the stress resultant-displacement expressions are combined and algebraically manipulated. These operations lead to a new “Governing System of the First Order Ordinary Differential Equations” in “state vector” forms. The new “Governing System of Equations” facilitates the direct application of the present method of solution, namely, the “Modified Transfer Matrix Method (MTMM) (with Interpolation Polynomials)”. As shown in the present study, the “MTMM” is sufficiently general to handle the “Free Vibrations Response” of the “Stiffened System” (with, at least, one or up to three or four “Integral Plate Stiffeners”). The present analysis and the method of solution are applied to the typical “Stiffened Plate or Panel System with Two Integral Plate Stiffeners”. The mode shapes with their natural frequencies are presented for the “Isotropic Al-Alloy” and “Orthotropic Composite” cases and for several sets of support conditions. As an additional example, the case of the “Stiffened Plate or Panel System with Three Integral Plate Stiffeners” is also considered and is shown in terms of the mode shapes and their natural frequencies for one set of the boundary conditions. Also, some parametric studies of the natural frequencies versus the “Stiffener Thickness Ratio” and the “Stiffener Length (or Width) Ratio” are investigated and are graphically presented.
APA, Harvard, Vancouver, ISO, and other styles
3

BROER, AGNES, NAN YUE, GEORGIOS GALANOPOULOS, RINZE BENEDICTUS, THEODOROS LOUTAS, and DIMITRIOS ZAROUCHAS. "ON THE CHALLENGES OF UPSCALING DAMAGE MONITORING METHODOLOGIES FOR STIFFENED COMPOSITE AIRCRAFT PANELS." In Structural Health Monitoring 2021. Destech Publications, Inc., 2022. http://dx.doi.org/10.12783/shm2021/36237.

Full text
Abstract:
Health management methodologies for condition-based maintenance are often developed using sensor data collected during experimental tests. Most tests performed in laboratories focus on a coupon level or flat panels, while structural component testing is less commonly seen. As researchers, we often consider our experimental tests to be representative of a structure in a final application and consider the developed methodologies to be transferrable to these real-life structures. Yet, structures in their final applications such as wind turbines or aircraft are often larger, more complex, might contain various assembly details, and are loaded in complex conditions. These factors might influence the performance of developed diagnostic and prognostic methodologies and should therefore not be ignored. In our work, we consider the aspects of upscaling structural health monitoring (SHM) methodologies for stiffened composite panels with the design of the panels inspired by an aircraft wing structure. For this, we examine two levels of panels, namely a single- and multi-stiffener composite panel, where we consider the single-stiffener panel to be a representative lower-level version of the multi-stiffener panel. Multiple SHM sensors (acoustic emission, Lamb waves, strain sensing) were installed on both composite panels to monitor damage propagation during testing. We identify and analyse challenges and further discuss considerations that must be taken during upscaling of diagnostics and prognostics, and with that, aid in the development of health management methodologies for condition-based maintenance.
APA, Harvard, Vancouver, ISO, and other styles
4

Sundararaj, K., and M. Ganesh. "Numerical investigation of composite stiffened panel with various stiffeners under axial compression." In PROCEEDINGS OF ADVANCED MATERIAL, ENGINEERING & TECHNOLOGY. AIP Publishing, 2020. http://dx.doi.org/10.1063/5.0019625.

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

Akula, Venkata M. K. "Low-Velocity Impact Analysis of a Stiffened Composite Panel." In ASME 2015 Pressure Vessels and Piping Conference. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/pvp2015-45727.

Full text
Abstract:
The layered architecture of composite material allows for designing light-weight structural components. However, one of the challenges associated with composite structures is design and analysis considering impact damage. Although the damage associated with high-velocity impact events is often readily observed in a structure, by loss of material, for example, low-velocity impact damage is not always visible. However, low-velocity impact damage can undermine the strength capacity of a composite component. To ensure the structural integrity of components, predicting the residual strength after impact damage is critical. In this paper, a methodology for analysis of low-velocity impact on a curved composite panel is discussed. First, impact analysis of the panel utilizing Abaqus\Explicit is presented. A metallic projectile is utilized to simulate a tool drop event. Thereafter, a simulation technique for predicting the residual strength of the panel is discussed. The residual strength is measured in terms of collapse load when the panel is subjected to axial compression. Finally, parameter sensitivity analysis is performed to understand the influence of the various design parameters on the residual strength of the component after impact. This procedure requires automating the entire simulation workflow. The results of the simulation are presented along with the important observations.
APA, Harvard, Vancouver, ISO, and other styles
6

Mucha, Waldemar, Wacław Kuś, Júlio C. Viana, and João Pedro Nunes. "Comparison of numerical and experimental strain distributions in composite panel for aerospace applications." In VI ECCOMAS Young Investigators Conference. València: Editorial Universitat Politècnica de València, 2021. http://dx.doi.org/10.4995/yic2021.2021.12572.

Full text
Abstract:
In structural applications of the aerospace industry, weight efficiency, understood as minimal weight and maximal stiffness, is of great importance. This criterion can be achieved by composite lightweight structures. Typical structures for the aforementioned applications are sandwich panels (e.g. with honeycomb core) and stiffened panels (e.g. with blade ribs, T-bar ribs, or hat ribs) [1-3]. In the paper, hat-stiffened panel, made of carbon/epoxy woven composite, is considered. Results of experiments, consisting of loading the panel and measuring exciting forces and strains (using strain gages), are presented. The results are compared to strains distribution obtained from finite element model of the panel. An idea of real-time system for load monitoring of the structure, using artificial intelligence techniques [4], is also presented. An high fidelity digital model with a big compliance of the computed and measured strain distributions is crucial for the performance of such a cyber-physical system.
APA, Harvard, Vancouver, ISO, and other styles
7

Umezawa, Keisuke, and Takahira Aoki. "Postbuckling Analysis of Composite Stiffened Panel under Shear Load." In 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-1432.

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

Taki, Toshimi, and Tomohiro Kitagawa. "Postbuckling strength of composite stiffened panel under shear load." In Aircraft Engineering, Technology, and Operations Congress. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-3934.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Abramovich, Haim, Chiara Bisagni, and Potito Cordisco. "Post-Buckling Test Simulation of a Stiffened Composite Panel." In 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-2126.

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

Rout, Mrutyunjay, Sasank Shekhar Hota, and Amit Karmakar. "Multiple Low Velocity Impact on Twisted Composite Stiffened Blade: A Finite Element Approach." In ASME 2017 Gas Turbine India Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gtindia2017-4772.

Full text
Abstract:
This paper presents the numerical modeling of a twisted stiffened cylindrical shell employing finite element approach to investigate the transient response due to impact of multiple masses, wherein the shell and the stiffener are modeled as 8 noded isoparametric shell element with five degrees of freedom per node and 3 noded isoparametric curved beam element having four degrees of freedom per node, respectively. The stiffener element is considered as a discrete beam element and its nodal degrees of freedom are transferred to the corresponding degrees of freedom of the shell element considering curvature and eccentricity. The impact force is predicted by employing modified Hertzian contact law relating the contact force to local indentation. As indentation takes place the impactor induces damage and permanent deformation in the contact zone of stiffened panel, as a result the loading and unloading curves are different. Different mathematical equations are considered for both loading and unloading cases in the stiffened panel during low-velocity impact. The accuracy and effectiveness of the finite element approach is verified by comparing the results with the corresponding solutions of analytical as well as standard computational methods available in the open literature. The optimum design of a structure can only be obtained by understanding the impact behavior and the roles of various parameters affecting the response. Hence, parametric study has been carried out to predict the time histories of contact force, displacement of the impact point and in-plane stresses during low-velocity concurrent/delayed impact at multiple locations of the stationary and rotating stiffened shell.
APA, Harvard, Vancouver, ISO, and other styles
You might also be interested in the extended bibliographies on the topic 'Stiffened composite panel' for particular source types:
Journal articles Dissertations / Theses Books
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