Separated representations of 3D elastic solutions in shell geometries
- Brice Bognet^{1},
- Adrien Leygue^{1} and
- Francisco Chinesta^{1}Email author
DOI: 10.1186/2213-7467-1-4
© Bognet et al.; licensee Springer. 2014
Received: 15 August 2013
Accepted: 7 November 2013
Published: 29 January 2014
Abstract
Background
The solution of 3D models in degenerated geometries in which some characteristic dimensions are much lower than the other ones -e.g. beams, plates, shells,...- is a tricky issue when using standard mesh-based discretization techniques.
Methods
Separated representations allow decoupling the meshes used for approximating the solution along each coordinate. Thus, in plate or shell geometries 3D solutions can be obtained from a sequence of 2D and 1D problems allowing fine and accurate representation of the solution evolution along the thickness coordinate while keeping the computational complexity characteristic of 2D simulations. In a former work this technique was considered for addressing the 3D solution of thermoelastic problems defined in plate geometries. In this work, the technique is extended for addressing the solution of 3D elastic problems defined in shell geometries.
Results
The capabilities of the proposed approach are illustrated by considering some numerical examples involving different degrees of complexity, from simple shells to composite laminates involving stiffeners.
Conclusions
The analyzed examples prove the potentiality and efficiency of the proposed strategy, where the computational complexity was found evolving as reported in our former works, proving that 3D solutions can be computed at a 2D cost.
Keywords
PGD Separated representations Model reduction Shell geometriesBackground
Plates and shells are very common in nature and thus they inspired engineers that used both from the very beginning of structural mechanics. Shells offer a diversity of possible shapes and geometries, some of them with simple curvature and most of them with double curvature. Many times they are assembled in complex structural systems, in many applications they contain many stiffeners as in the case of aircraft fuselages.
In general the design of such structural elements requires the calculation of stresses, strains and displacements for the design loads. Strains and stresses are related by the so-called constitutive law. The simplest one consists of the linear elasticity. Despite its simplicity many structures are designed for working precisely within the elastic domain. Other designs require considering more complex behaviors (e.g. non-linear elasticity due to material or geometrical non linearities, elastoplastic behaviors usually encountered in material forming – forging, bending,... –, or complex multiphysics behaviors as the ones encountered in composites manufacturing processes implying change of phases, crystallization, polymerization,... coupled with rich thermomechanical mechanisms).
Design problems always involve the solution of a set of partial differential equations in the degenerate domain of the plate or the shell with appropriate initial and boundary conditions. These domains are degenerated because one of its characteristic dimensions (the thickness in the present case) is much lower that the other characteristic dimensions. We will understand the consequences of such degeneracy later. When analytical solutions are neither available nor possible because the geometrical or behavior complexities, the solution must be calculated by invoking any of the available numerical techniques (finite elements, finite differences, finite volumes, methods of particles,...).
In the numerical framework the solution will be only obtained in a discrete number of points, usually called nodes, distributed in the domain. From the solution at those points, it can be interpolated at any other point in the domain. In general regular nodal distributions are preferred because they offer the best accuracy. In the case of degenerated plate or shell domains one could expect that if the solution evolves significantly in the thickness direction, a large enough number of nodes must be distributed along the thickness direction to ensure the accurate representation of the field evolution in that direction. In that case, a regular nodal distribution in the whole domain will imply the use of an extremely large number of nodes with the consequent impact on the numerical solution efficiently.
When simple behaviors and domains were considered semi-analytical models can be considered [1]. For addressing more complex scenarios plate and shell theories were developed allowing, through the introduction of some hypotheses, reducing the 3D complexity to the 2D related to the problem now formulated by considering the in-plane coordinates. The use of these theories have been extended gradually for addressing larger and more complex geometries (anisotropic laminates,...) and behaviors.
There are thousand of papers concerning the proposal and application of plate and shell models (the interested reader can refer to the recent reviews [2, 3] and the references therein). Some models are based on the introduction of kinematic hypotheses in the thickness (e.g. [4] among many others). Transverse shear can be also taken into account [5]. Recent zig-zag representations [6, 7], layer-wise models [8–10] and solid-shell approaches [11, 12], allow addressing accurately more complex scenarios, by increasing the computational complexity slightly. Stiffeners require an appropriate coupling of beam and shell models in order to perform calculations at a moderate computational cost [13].
However, as soon as richer physics are involved in the models and the considered geometries differ of those ensuring the validity of the different reduction hypotheses, efficient simulations are compromised. For example in composites manufacturing processes of large parts many reactions and thermal processes inducing significant evolutions on the thermomechanical fields in the thickness occur. These inhomogeneities are at the origin of residual stresses and the associated distortion of the formed parts [14].
In these circumstances as just indicated the reduction from the 3D model to a 2D simplified one is not obvious, and 3D simulations appear many times as the only valid route for addressing such models, that despite the fact of being defined in degenerated geometries (plate or shell) they seem requiring a fully 3D solution. However in order to integrate such calculations (fully 3D and implying an impressive number of degrees of freedom) in usual design procedures, a new efficient (fast and accurate) solution procedure is needed.
The Saint Venant’s principle was extensively used in the Ladeveze’s works for defining elegant and efficient 3D simplified models [15]. This technique was then generalized to dynamics [16]. This technique allowed significant reduction of computational complexity.
Later, a new discretization technique based on the use of separated representations was proposed for addressing space-time nonlinear models [17] and then it was generalized for defining general separated representations of solutions involving conformational coordinates [18], space and time and even parameters considered as extra-coordinates. The interested reader can refer to the recent reviews [19–22] and the references therein.
A direct consequence was the separated representations involving the space coordinates. Thus in plate domains an in-plane-out-of-plane decomposition was proposed for solving flow problems in laminates [20], then for solving thermal problems in extruded geometries [23], elasticity problems [24] and coupled multiphycisc problems [25]. In those cases the 3D solution was obtained from the solution of a sequence of 2D problems (the ones involving the in-plane coordinates) and 1D problems (the ones involving the coordinate related to the plate thickness).
It is important emphasizing the fact that these approaches are radically different to standard plate and shell approaches. We proposed a 3D solver able to compute the different unknown fields without the necessity of introducing any hypothesis. The most outstanding advantage is that 3D solutions can be obtained with a computational cost characteristic of standard 2D solutions. Moreover, as noticed in [24] no locking effects were found, possibly because the fully 3D solution accomplished.
In this work we will generalize the just referred approach considered in the case of plate domains for calculating the fully 3D solution of the elastic problem in shell domains. The 3D solution will be calculated again from the solution of a sequence of 2D and 1D problems thanks to the in-plane-out-of-plane separated representation.
It is important to note that in this paper we are not addressing a new shell modeling, and by this reason we do not need neither establishing a precise state of the art on shell theories nor comparing our approach with the solutions obtained by using shell models. As we are proposing a new procedure for calculating 3D solutions (keeping a computational complexity characteristic of 2D solution procedures) we will compare our solutions with the ones obtained by considering the fully 3D elastic solution in the shell geometries computed with standard 3D solvers (e.g. finite elements).
Before generalizing the technique proposed in [24] for treating elastic problems defined in shell domains we are summarizing it.
In-plane-out-of-plane separated representation of elastic problems defined in plate domains
where ${P}_{k}^{i}$, k=1,2,3, are functions of the in-plane coordinates (x_{1},x_{2}) whereas ${T}_{k}^{i}$, k=1,2,3, are functions involving the thickness coordinate x_{3}. In [24] we compared the first modes of such separated representations with the kinematic hypotheses usually considered in plate theories. Similar behavior was noticed in the case of elastic solutions in shell domains with respect to classical shell theories.
where vectors P^{ i } and T^{ i } contains functions ${P}_{k}^{i}$ and ${T}_{k}^{i}$ respectively.
Because neither the number of terms in the separated representation of the displacement field nor the dependence on x_{3} of functions ${T}_{k}^{i}$ are assumed a priori, the approximation is flexible enough for representing the fully 3D solution, being obviously more general than theories assuming particular a priori evolutions in the thickness direction x_{3}.
Depending on the number of non-zero elements in the K matrix, the development of ε(u^{∗})^{ T }·K· ε(u) involves different number of terms, 21 in the case of an isotropic material and 41 in the case of general anisotropic behaviors.
where both vectors P^{ n } and T^{ n } containing functions ${P}_{i}^{n}$ and ${T}_{i}^{n}$ (i=1,2,3) depending on (x_{1},x_{2}) and x_{3} respectively, are unknown at the present iteration. The test function u^{∗} reads u^{∗}=P^{∗}∘T^{ n }+P^{ n }∘T^{∗}.
The introduction of Eq. (7) into (3) results in a non-linear problem. We proceed by considering the simplest linearization strategy, an alternated directions fixed point algorithm, that proceeds by calculating P^{n,k} from T^{n,k-1} and then by updating T^{n,k} from the just calculated P^{n,k} where k refers to the step of the non-linear solver. The iteration procedure continues until convergence, that is, until reaching the fixed point ∥P^{n,k}∘T^{n,k}-P^{n,k-1}∘T^{n,k-1}∥<ε, that results in the searched functions P^{n,k}→P^{ n } and T^{n,k}→T^{ n }. Then, the enrichment step continues by looking for the next mode P^{n+1}∘T^{n+1}. The enrichment stops when the model residual becomes small enough.
When T^{ n } is assumed known, we consider the test function u^{⋆} given by P^{⋆}∘T^{ n }. By introducing the trial and test functions into the weak form and then integrating in$\phantom{\rule{0.1em}{0ex}}\mathcal{I}$ because all the functions depending on the thickness coordinate are known, we obtain a 2D weak formulation defined in Ω whose discretization (by using a standard discretization strategy, e.g. finite elements) allows computing P^{ n }.
Analogously, when P^{ n } is assumed known, the test function u^{⋆} is given by P^{ n }∘T^{⋆}. By introducing the trial and test functions into the weak form and then integrating in Ω because all the functions depending on the in-plane coordinates (x_{1},x_{2}) are at present known, we obtain a 1D weak formulation defined in$\phantom{\rule{0.1em}{0ex}}\mathcal{I}$ whose discretization (using any technique for solving standard ODE equations) allows computing T^{ n }.
The problems related to the solution of functions P^{ n } and T^{ n } are defined in Appendix A.
As discussed in [24] this separated representation allows computing 3D solutions while keeping a computational complexity characteristic of 2D solution procedures. If we consider a hexahedral domain discretized using a regular structured grid with N_{1}, N_{2} and N_{3} nodes in the x_{1}, x_{2} and x_{3} directions respectively, usual mesh-based discretization strategies imply a challenging issue because the number of nodes involved in the model scales with N_{1}·N_{2}·N_{3}, however, by using the separated representation and assuming that the solution involves N modes, one must solve about N 2D problems related to the functions involving the in-plane coordinates (x_{1},x_{2}) and the same number of 1D problems related to the functions involving the thickness coordinate x_{3}. The computing time related to the solution of the one-dimensional problems can be neglected with respect to the one required for solving the two-dimensional ones. Thus, the resulting complexity scales as N·N_{1}·N_{2}. By comparing both complexities we can notice that as soon as N_{3}≫N the use of separated representations leads to impressive computing time savings, making possible the solution of models never until now solved, and even using light computing platforms.
In [24] we considered the simplest approximations of functions involving the in-plane coordinates ${P}_{k}^{i}({x}_{1},{x}_{2})$ by considering bilinear quadrilateral finite elements and piecewise linear 1D elements for approximating functions involving the thickness coordinate x_{3}, ${T}_{k}^{i}\left({x}_{3}\right)$. Richer approximations were analyzed in [26].
In the present work we are generalizing the just described separated representation for solving 3D models defined in shell domains.
Methods
3D elastic problem in a shell domain: Shell representation
whose expression is given in the Appendix B (Eqs. (73) and (74) that involve Eqs. (42), (43) and (49)).
The inverse transformation (x_{1},x_{2},x_{3})→(ξ,η,ζ), described by ${\stackrel{~}{\mathbf{F}}}^{-1}$ is also given in the appendix (Eq. (75)).
3D elastic problem in a shell domain: Weak form
Now we are considering the coordinates transformation introduced in the previous section and deeply developed in the appendix, mapping x∈Ω^{ S } into $(\xi ,\eta ,\zeta )\in \Xi =\Omega \times \mathcal{I}$, with $(\xi ,\eta )\in \Omega \subset {\mathcal{R}}^{2}$ and $\zeta \in \mathcal{I}\subset \mathcal{R}$.
where ∇_{ ξ }(·) denotes the gradient in the parametric space.
with a is the determinant of the metric tensor related to the middle surface mapping (46) and H and K the curvatures given by Eqs. (56) and (57) respectively. Finally the integrals applying on the domain boundary (where tractions apply) are transformed according to Eq. (68).
3D elastic problem in a shell domain: In-plane-out-of-plane separated representation
With the weak form defined in $\Xi =\Omega \times \mathcal{I}$ the situation is quite similar to the one encountered in the analysis of elastic problems in plate geometries, that was addressed in [24] and we just summarized in section 'Background’.
By introducing (17) in the weak form and using the alternated directions fixed point algorithm we can calculate P^{ n }(ξ,η) by assuming T^{ n }(ζ) known and then updated T^{ n }(ζ) from the just calculated P^{ n }(ξ,η). The iteration continues until reaching the convergence (the fixed point) that determines both functions P^{ n }(ξ,η) and T^{ n }(ζ).
However, the decomposition in a problem defined in Ω for calculating function P^{ n }(ξ,η), obtained by integrating the weak form in$\phantom{\rule{0.1em}{0ex}}\mathcal{I}$, and in another problem defined in$\phantom{\rule{0.1em}{0ex}}\mathcal{I}$ for calculating function T^{ n }(ζ), obtained by integrating the weak form in Ω, requires the separated representation of all the operators, variables, coefficients and functions involved in the weak form.
For the displacement (the trial u and the test u^{∗} displacements) we just indicated the separated in-plane-out-of-plane representation. This representation allows defining a separated representation of the associated strain tensors ε(u) and ε(u^{∗}) as illustrated in Eq. (6) but for this purpose we must define a separated representation of the transformation gradient involved in Eq. (13) ${\stackrel{~}{\mathbf{F}}}^{-1}$.
where b_{ n } and F only depend on the middle surface parametrization.
When this approximation (small thickness and curvatures) does not apply we should consider the separated representation of ${\stackrel{~}{\mathbf{F}}}^{-1}$ by applying a singular value decomposition –SVD–.
The elasticity tensor and the applied forces must be also expressed in a separated form. Most of time this decomposition is direct and in the more complex cases the application of a singular value decomposition allows such decomposition.
From Eq. (68) we can expect a similar decomposition of the surface element.
3D elastic problem in a shell domain: Composite laminates
In this section we consider composite laminates composed of P anisotropic (generally orthotropic) plies of thickness h (for the sake of simplicity and without loss of generality we assume all the plies with the same thickness).
We consider the mechanical behavior of each ply i expressed by its elasticity tensor ${\mathcal{K}}^{i}$ whose form is quite simple when it is expressed in the basis related to its mechanical principal directions.
Now, for the sake of simplicity we are also considering a local orthonormal basis defined at each point on the middle surface (t_{1},t_{2},n), where the normal vector n is the one previously considered, and the tangent vectors t_{1} and t_{2} to the middle surface at the considered location can be chosen arbitrarily under the constraints: t_{1}·t_{2}=0, t_{1}·n=0, t_{2}·n=0, ∥t_{1}∥=1 and ∥t_{2}∥=1.
Results and discussion
Strategy verification
with $\overline{R}=2.5$, $\xi \in [0,2\xb7\pi \xb7\overline{R}]$ and η∈[0,1] (we are considering an arbitrary tube length due to the plane state of strain).
The shell geometry is defined by introducing the thickness coordinate ζ∈[-0.5,0.5].
In the numerical solution the domain $(\xi ,\eta )\in \Omega =[0,2\xb7\pi \xb7\overline{R}]\times [0,1]$ is discretized by using a regular mesh of rectangular bilinear elements whereas the thickness interval $\zeta \in \mathcal{I}=[-0.5,0.5]$ is discretized by using standard one-dimensional linear elements (the simplest choices, but higher order approximations can be used in Ω and/or$\phantom{\rule{0.1em}{0ex}}\mathcal{I}$). The displacement is constrained at some appropriate locations in order to avoid rigid body movements.
Meshes considered in the numerical solution
N _{ ξ } | N _{ η } | N _{ ζ } | |
---|---|---|---|
MESH 1 | 8 | 2 | 2 |
MESH 2 | 16 | 2 | 4 |
MESH 3 | 32 | 2 | 8 |
The problem is also solved numerically by using a 3D finite element discretization operating on the domain Ξ by considering regular meshes of 3D trilinear elements, compatible with the description given by the meshes in Table 1 consisting of 32, 128 and 384 3D-elements respectively.
Because the solution of the considered problem only involves radial (thickness) displacements depending on the radial coordinate, a 3D elastic solution seems to be the most appropriate and simplest choice, more natural than using computational shell theories. This problem can be solved easily with quadratic finite elements or isogeometric ones by only one element across the thickness. Also with axisymmetric representation only one 8 nodes element gives a nearly perfect solution. However here we prefer using linear finite elements in order to compare with the linear representation of functions involved in the PGD representation here considered, even if we could use higher order representations within the PGD framework. The objective here is proving the convergence and comparing the simplest finite elements and PGD formulations.
This numerical example served to validate the proposed approach based on the use of separated representations for solving 3D elastic problems in shell domains. It is important to notice that we compute the fully 3D solution with a prescribed accuracy. Thus, the proposed procedure should be viewed as a 3D solver that due to the separated representation of the 3D fields involved in the model allows a reduction of the computational complexity to the one characteristic of 2D solutions.
Elliptic tube
In order to address a problem whose solution consists of more than a single mode, we consider in this section a slightly different problem. It concerns a tube of infinite length but now with an elliptical cross section and again subjected to an internal pressure.
where $\overline{R}=2.5$, $\xi \in [0,2\xb7\pi \xb7\overline{R}]$ and η∈[0,1] (we are considering an arbitrary tube length due to the plane strain assumption). The tube thickness is defined from ζ∈[-0.5,0.5]. Material parameters are the same than in the previous test.
We consider the same discretization than in the previous example, bilinear rectangles in Ω and standard one-dimensional linear elements in the thickness (again the simplest choice).
Tube with finite length
Twisted tourus
where R=2, r=4 and e=0.15.
Scordelis-Lo roof
The problem material and geometrical parameters are the following E=3 10^{6}, ν=0, a=600, r=300, e=3 and α=π/3. The shell is subjected to a surface load of 0.625 that induces a vertical displacement of 3.6288 at position A in Figure 27[27].
From this comparison we can conclude that our approach based on a separated representation converges and that it exhibits similar convergence behavior than standard linear 3D finite elements.
Multilayered tube
We solved the same elastic problem than in section 'Strategy verification’, being the only difference the one related to the material mechanical behavior. The in-plane discretization of Ω was performed by considering a regular mesh composed of 40×2 2D bilinear finite elements, whereas 80 one-dimensional linear elements were considered for discretizing the thickness interval$\phantom{\rule{0.1em}{0ex}}\mathcal{I}$. Thus each ply is represented by 10 elements ensuring a rich description (perhaps too rich in the case of elastic behaviors but that could be compulsory for addressing more complex mechanical behaviors). In this work we would like emphasizing that the proposed strategy allows very rich descriptions of the thickness coordinate without a significant impact on the numerical efficiency.
Analysis of large composite structural parts
The laminate is composed of 12 plies, each 0.125 m m thick and involving an unidirectional reinforcement. The stacking sequence is [0,45,0,-45]_{3S}.
The 3D solution was obtained by using an in-plane-out-of-plane separated representation of the elastic fields. The approximation of functions involving the thickness direction was performed by considering 10 elements per ply. An equivalent finite element mesh of the whole part would have implied 7·10^{7} elements with 2·10^{8} nodes, each one involving 3 degrees of freedom.
The main advantage of the procedure that we propose does not concern the possibility of addressing laminates involving several plies, because when elastic behaviors are considered they exist advanced shell elements able to address efficiently such configurations. However, our technique allows considering in an unified description the laminates and the stiffeners placed on it, by using the same in-plane-out-of-plane representation, as was widely discussed in [24]. The consideration of all these stiffeners within a standard shell theory requires special treatments, however in our fully 3D approach, both the shell laminate and the stiffeners are integrated in an unified hypotheses-free description.
Conclusions
We proposed in our former works a procedure based on the separated representation of the displacement field involved in elastic problems defined in plate domains that allowed calculating fully 3D elastic solutions by solving a sequence of 2D and 1D problems, the former ones define in the plane and the last ones in the thickness. Thus, we calculated 3D solutions with a computational cost characteristic of 2D problems, as the ones related to standard plate theories, however here, as we compute directly the 3D solution, we do not need introducing any hypothesis or correction.
In the present paper we extended that methodology for solving elastic linear problems defined in shell geometries. For that purpose we proposed to use a standard mapping of the real geometry to a plate-type parametric domain in which the procedure proposed in our former works was applied. However, the main difficulty when using this procedure concerns the necessity of performing a separated representation of displacement and strain fields, loads, material behavior (elasticity tensor), the differential operators as well as the surface and volume elements. This decomposition is for some problems quite direct and in all cases it can be performed by invoking the singular value decomposition.
The analyzed examples prove the potentiality and efficiency of the proposed strategy, where the computational complexity was found evolving as reported in [24], proving that 3D solutions can be computed at a 2D cost. On the other hand the fact of solving fully 3D models avoids the locking issue that was never found in our analysis.
The extension of this strategy for addressing more complex scenarios involving material or geometrical non-linearities or for considering more complex geometries in which the domain thickness could vary from one point to other represent some of the works in progress.
Appendix A
In-plane and out-of-plane problems
By integrating Eq. (37) along the coordinate x_{3} we obtain a discrete system from which results P^{ n }.
and by integrating in Ω it results the linear problem from with it results T^{ n }.
Appendix B
Elements of differential geometry
Surface fundamental forms
Shell description
that establishes a mapping between (ξ,η,ζ) and (x_{1},x_{2},x_{3}).
When this approximation fails we should consider the full inverse of $\stackrel{~}{\mathbf{F}}$.
Declarations
Authors’ Affiliations
References
- Timoshenko SP, Woinowsky-Krieger S: Theory of plates and shells. New York,: McGraw-Hill classic textbook reissue; 1959. second edition second editionGoogle Scholar
- Qatu MS: Review of recent literature on static analyses of composite shells: 2000–2010. Open J Composite Mater 2012,2(3):61–86. 10.4236/ojcm.2012.23009View ArticleGoogle Scholar
- Zhang YX, Yang CH: Recent developments in finite element analysis for laminated composite plates. Composite Struct 2009,88(1):147–157. 10.1016/j.compstruct.2008.02.014View ArticleGoogle Scholar
- Reddy JN, Arciniega RA: Shear deformation plate and shell theories: from Stavsky to present. Mech Adv Mater Struct 2004,11(6):535–582. 10.1080/15376490490452777View ArticleGoogle Scholar
- Viola E, Tornabene F, Fantuzzi N: Static analysis of completely doubly-curved laminated shells and panels using general higher-order shear deformation theories. Composite Struct 2013, 101: 59–93.View ArticleGoogle Scholar
- Carrera E: Historical review of Zig-Zag theories for multilayered plates and shells. Appl Mech Rev 2003,56(3):287. 10.1115/1.1557614View ArticleGoogle Scholar
- Sedira L, Ayad R, Sabhi H, Hecini M, Sakami S: An enhanced discrete Mindlin finite element model using a zigzag function. Eur J Comput Mech 2012,21(1–2):122–140.Google Scholar
- Carrera E: Theories and finite elements for multilayered, anisotropic, composite plates and shells. Arch Comput Methods Eng 2002,9(2):87–140. 10.1007/BF02736649MathSciNetView ArticleGoogle Scholar
- Carrera E: Theories and finite elements for multilayered plates and shells: a unified compact formulation with numerical assessment and benchmarking. Arch Comput Methods Eng 2003,10(3):215–296. 10.1007/BF02736224MathSciNetView ArticleGoogle Scholar
- Kratzig WB, Jun D: Multi-layer multi-director concepts for D-adaptivity in shell theory. Comput Struct 2002,80(9):719–734.View ArticleGoogle Scholar
- Naceur H, Shiri S, Coutellier D, Batoz JL: On the modeling and design of composite multilayered structures using solid-shell finite element model. Finite Elem Anal Design 2013, 70: 1–14.View ArticleGoogle Scholar
- Trinh V-D, Abed-Meraim F, Combescure A: A new assumed strain solid-shell formulation “SHB6” for the six-node prismatic finite element. J Mech Sci Technol 2011,25(9):2345–2364. 10.1007/s12206-011-0710-7View ArticleGoogle Scholar
- Quatmann M, Aswini N, Reimerdes HG, Gupta NK: Superelements for a computationally efficient structural analysis of elliptical fuselage sections. Aerosp Sci Technol 2013,27(1):76–83. 10.1016/j.ast.2012.06.009View ArticleGoogle Scholar
- Wisnom MR, Gigliotti M, Ersoy N, Campbell M, Potter KD: Mechanisms generating residual stresses and distortion during manufacture of polymer-matrix composite structures. Composites Part A: Appl Sci Manuf 2006,37(4):522–529. 10.1016/j.compositesa.2005.05.019View ArticleGoogle Scholar
- Hochard Ch, Ladeveze P, Proslier L: A simplified analysis of elastic structures. Eur J Mech A/Solids 1993,12(4):509–535.MathSciNetGoogle Scholar
- Ladeveze P, Arnaud L, Rouch P, Blanz C: The variational theory of complex rays for the calculation of medium-frequency vibrations. Eng Comput 2001,18(1–2):193–221.View ArticleGoogle Scholar
- Ladeveze P: Nonlinear computational structural mechanics. New York: Springer; 1999.View ArticleGoogle Scholar
- Ammar A, Mokdad B, Chinesta F, Keunings R: A new family of solvers for some classes of multidimensional partial differential equations encountered in kinetic theory modeling of complex fluids. J Non-Newtonian Fluid Mech 2006, 139: 153–176. 10.1016/j.jnnfm.2006.07.007View ArticleGoogle Scholar
- Chinesta F, Ammar A, Cueto E: Recent advances and new challenges in the use of the Proper Generalized Decomposition for solving multidimensional models. Arch Comput Methods Eng 2010, 17: 327–350. 10.1007/s11831-010-9049-yMathSciNetView ArticleGoogle Scholar
- Chinesta F, Ammar A, Leygue A, Keunings R: An overview of the Proper Generalized Decomposition with applications in computational rheology. J Non-Newtonian Fluid Mech 2011, 166: 578–592. 10.1016/j.jnnfm.2010.12.012View ArticleGoogle Scholar
- Chinesta F, Ladeveze P, Cueto E: A short review in model order reduction based on Proper Generalized Decomposition. Arch Comput Methods Eng 2011, 18: 395–404. 10.1007/s11831-011-9064-7View ArticleGoogle Scholar
- Chinesta F, Leygue A, Bordeu F, Aguado JV, Cueto E, Gonzalez D, Alfaro I, Ammar A, Huerta A: Parametric PGD based computational vademecum for efficient design, optimization and control. Arch Comput Methods Eng 2013, 20: 31–59. 10.1007/s11831-013-9080-xMathSciNetView ArticleGoogle Scholar
- Leygue A, Chinesta F, Beringhier M, Nguyen TL, Grandidier JC, Pasavento F, Schrefler B: Towards a framework for non-linear thermal models in shell domains. Int J Numerical Methods Heat Fluid Flow 2013,23(1):55–73. 10.1108/09615531311289105View ArticleGoogle Scholar
- Bognet B, Leygue A, Chinesta F, Poitou A, Bordeu F: Advanced simulation of models defined in plate geometries: 3D solutions with 2D computational complexity. Comput Methods Appl Mechanics Eng 2012, 201: 1–12.View ArticleGoogle Scholar
- Chinesta F, Leygue A, Bognet B, Ghnatios Ch, Poulhaon F, Bordeu F, Barasinski A, Poitou A, Chatel S: First steps towards an advanced simulation of composites manufacturing by automated tape placement. Int J Mater Forming 2014. http://www.springerlink.com/index/10.1007/s12289-012-1112-9Google Scholar
- Vidal P, Gallimard L, Polit O: Proper Generalized Decomposition and layer-wise approach for the modeling of composite plate structures. Int J Solids Struct 2013,50(14–15):2239–2250.View ArticleGoogle Scholar
- Macneal RH, Harder RL: A proposed standard set of problems to test finite element accuracy. Finite Elem Anal Design 1985, 1: 3–20. 10.1016/0168-874X(85)90003-4View ArticleGoogle Scholar
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