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Comput. Methods Appl. Mech. Engrg. 197 (2008) 2030–2045

Reduced-order models for large-amplitude vibrations of shellsincluding in-plane inertia

C. Touze a,*, M. Amabili b, O. Thomas c

a ENSTA-UME, Unite de recherche en Mecanique, Chemin de la Huniere, 91761 Palaiseau cedex, Franceb Universita di Parma, Parco Area delle scienze 181/A, Parma, Italy

c CNAM, Laboratoire de Mecanique des Structures et Systemes Couples, 2 rue Conte, 75003 Paris, France

Received 24 July 2007; received in revised form 20 December 2007; accepted 7 January 2008Available online 24 January 2008

Abstract

Non-linear normal modes (NNMs) are used in order to derive reduced-order models for large amplitude, geometrically non-linearvibrations of thin shells. The main objective of the paper is to compare the accuracy of different truncations, using linear and non-linearmodes, in order to predict the response of shells structures subjected to harmonic excitation. For an exhaustive comparison, three dif-ferent shell problems have been selected: (i) a doubly curved shallow shell, simply supported on a rectangular base; (ii) a circular cylin-drical panel with simply supported, in-plane free edges; and (iii) a simply supported, closed circular cylindrical shell. In each case, themodels are derived by using refined shell theories for expressing the strain–displacement relationship. As a consequence, in-plane inertiais retained in the formulation. Reduction to one or two NNMs shows perfect results for vibration amplitude lower or equal to the thick-ness of the shell in the three cases, and this limitation is extended to two times the thickness for two of the selected models.� 2008 Elsevier B.V. All rights reserved.

Keywords: Shell vibrations; Non-linear normal modes; Model reduction; Geometrical non-linearity

1. Introduction

The large amplitude, geometrically non-linear vibrationsof shells leads to complicated motions with typical non-lin-ear phenomena. As a consequence, a large number ofexpansion functions is generally needed for discretizingthe structure in order to obtain convergence through theGalerkin method. This results in large computational timesthat could be prohibitive in the context of simulation orcontrol. For this reason, there is an important need forthe definition of reduced-order models (ROMs), which cap-ture the most salient features of the non-linear dynamicswith a limited number of degrees-of-freedom (dofs).

Non-linear normal modes (NNMs) are defined in orderto bypass the limitations of the linear normal modes(LNMs) in the non-linear range. The idea is to ‘‘decouple”

0045-7825/$ - see front matter � 2008 Elsevier B.V. All rights reserved.

doi:10.1016/j.cma.2008.01.002

* Corresponding author. Tel.: +33 1 69 31 97 34; fax: +33 1 69 31 97 97.E-mail address: [email protected] (C. Touze).

as much as possible the motions in selected sub-spaces ofthe phase space. This is realized by imposing the invarianceof sub-spaces as the key property that must be conservedwhen non-linearities come into play, and leads to the defi-nition of NNMs as invariant manifolds of the phase space[1]. As the method used for computing the NNMs is purelynon-linear, it is expected to give better results than usingthe LNMs, or modes obtained via the proper orthogonaldecomposition (POD) method [2–5].

Several methods have then been proposed to computethe NNMs. They generally rely on an asymptotic develop-ment for approximating the invariant manifold [6–11].More recently, purely numerical methods have been pro-posed [12–14], but they are often restricted either by com-plexity (i.e. computational time for calculating theROMs) or by practicality, as once the complex geometryof the manifold is computed, one has to project the equa-tions of motion onto it. In the context of shell vibrations,reduction with asymptotic NNMs has already been applied

mailto:[email protected]

x

z

u

w

v

RR 12

ab

h

x1

2

Fig. 1. Geometry and coordinate systems for the selected shells.

C. Touze et al. / Comput. Methods Appl. Mech. Engrg. 197 (2008) 2030–2045 2031

with success on a fluid-filled circular cylindrical shelldescribed by the Donnells’ shallow-shell assumptions [15],and compared with the POD method [2]. It also allows pre-diction of the type of non-linearity (hardening/softeningbehaviour) for shallow spherical shells [16].

In this study, the asymptotic NNM method is applied toshell structures, without the shallow-shell assumption. As aconsequence, in-plane inertia is retained in the equations ofmotions, which are derived via a Lagrangian approach [17–19]. In-plane inertia must be retained for shells that cannotbe considered shallow. The effect of retaining or neglectingin-plane inertia has been addressed by Amabili [17] forclosed circular cylindrical shells, and by Abe et al. [20]for curved panels but only in the linear (natural frequen-cies) part of their study. As a consequence of taking intoaccount these additional degrees-of-freedom, the compu-tation of the LNMs is tedious and is thus bypassed byusing as expansion functions an ad hoc basis verifyingthe boundary conditions. As a consequence, linear cou-pling terms among the discretized oscillator equations arepresent.

The present study is focused on the computation of fre-quency–response curves for harmonically forced shellsvibrating at large amplitude. As a complete bifurcation dia-gram (with stable and unstable solution branches) in thesteady-state is sought, a continuation algorithm is naturallyselected. In this context, structures discretized by finite-ele-ment based methods must obviously be reduced, as thenumber of degrees-of-freedom involved in a classical meshis immediately too large to be treated by standard contin-uation algorithm. For this reason, the LNMs and NNMsare here used for producing this reduction.

The reduction method proposed in [15] is revised inorder to take into account the linear coupling termsbetween oscillators. In particular, these terms link togetherflexural and in-plane motions. The procedure is automatedand thus extends earlier results presented in [21] where thein-plane motions of a plate were slaved to the flexuralmotions by using an invariant manifold approach.Amongst other things, the developments presented hereinon the reduction process with NNMs show that the methodcan easily handle any set of non-linear oscillators, as well asmore refined shell theories. Consequently, the method hasthe potential for a large class of structural problems, andcould be applied to finite elements analysis of shells, wherethe discretization functions, as well as the underlying shelltheories are distinct from those used here [22], providingthat an automated step computing the projection ontothe linear modes have been programmed.

Three structures are selected in order to compare theresults. A doubly curved panel, and a circular cylindricalpanel, with the Donnell non-linear theory without the shal-low-shell assumption, are first derived. Then a closedempty shell, the kinematics of which is expressed with theFlugge-Lur’e-Byrne non-linear theory, is studied. For eachcase, the reference solution is compared to ROMs with anincreasing number of LNMs and NNMs. The amplitude of

the external forcing is also varied in order to test the valid-ity limits of the asymptotic approach used to generate theNNMs. As side result, upper validity limits, in terms ofvibration amplitude with respect to the thickness of theshells, are derived for each model.

2. Theoretical formulation

2.1. Selected cases

Three cases have been selected for studying thereduction method provided by the asymptotic NNMformulation:

(i) A hyperbolic paraboloid panel with rectangular base,referred to as the HP panel in the following.

(ii) A circular cylindrical panel, referred to as the CCpanel.

(iii) A closed circular cylindrical shell, referred to as theFlugge shell.

An exhaustive presentation of the HP panel is given in[18], whereas the CC panel and the Flugge shell are respec-tively documented in [17,19]. These shell models have beenselected in order to draw out a complete picture of thereduction process in different situations. In particular,two different kinematics are used (Donnell’s non-linearshell theory is used for case (i) and (ii), while case (iii) isgoverned by Flugge-Lur’e-Byrne non-linear theory), andthe qualitative behaviour of the closed shell (case (iii)) isappreciably different from the two panels due to the sym-metry of the problem.

The three shell models will be presented in a unifiedmanner in this section, by emphasizing the general methodused to obtain the equations of motions. As a consequence,only the common features of the three models are heredescribed. Peculiar features, such as boundary conditionsor projection functions used for discretization, will bereported in Sections 4–6.

Fig. 1 shows the geometry and coordinate system for atypical shell. This geometry can handle the three cases

2032 C. Touze et al. / Comput. Methods Appl. Mech. Engrg. 197 (2008) 2030–2045

and is thus used here as a generic model for presenting theequations of motions. The curvilinear coordinate system isdenoted by ðO; x1; x2; zÞ, with the origin O at one edge of thepanel. R1 and R2 (assumed to be independent of x1 and x2)are the principal radii of curvature, a and b are curvilinearlength, and h is the thickness. The membrane displacementsare denoted by u and v, and the normal displacement is w.In the following, S refers to the surface of the shell, i.e.

S ¼ ½0; a� � ½0; b�.

2.2. Shell kinematics and external loads

The shell kinematics is described by relating the straincomponents e1, e2 and c12 at an arbitrary point of the con-sidered shell to the middle surface strains e1;0, e2;0 and c12;0,and to changes in the curvature and torsion of the middlesurface k1, k2 and k12 by

e1 ¼ e1;0 þ zk1; ð1Þe2 ¼ e2;0 þ zk2; ð2Þc12 ¼ c12;0 þ zk12; ð3Þ

where z is the distance of the arbitrary point from the mid-dle surface.

For the HP and CC panels, Donnell’s non-linear shelltheory is used to express the strain–displacement relation-ship. The full expressions of the relationships between themiddle surface strain–displacement and the changes in cur-vature and torsion can be found, for the HP panel in [18],and for the CC panel in [19]. For the Flugge shell, Flugge-Lur’e-Byrne non-linear theory is used, leading to a morecomplicated relationship that is not reported here for thesake of brevity. The interested reader is referred to[17,23,24] for complete expressions of the kinematics inthat case.

The elastic strain energy US is expressed with the classi-cal assumption of plane stress. According to the geometryshown in Fig. 1, it reads

US ¼1

2

ZS

Z h=2

�h=2

ðr1e1 þ r2e2 þ s12c12Þ 1þ zR1

� �

� 1þ zR2

� �dS dz; ð4Þ

where the stresses r1, r2 and s12 are related to the strainsfor an homogeneous and isotropic material by

r1 ¼E

1� m2ðe1 þ me2Þ; ð5Þ

r2 ¼E

1� m2ðe2 þ me1Þ; ð6Þ

s12 ¼E

2ð1þ mÞ c12: ð7Þ

The kinetic energy T S, by neglecting rotary inertia, reads

T S ¼1

2qhZS

ð _u2 þ _v2 þ _w2ÞdS; ð8Þ

where q is the mass density, and overdot is used forexpressing time derivation.

The virtual work W done by the external forces reads

W ¼ZS

ðqx1uþ qx2

vþ qzwÞdS; ð9Þ

where qx1, qx2

and qz are the distributed forces per unit areaacting in x1, x2 and z directions respectively. For the threecases studied, a pointwise normal excitation due to the con-centrated force ~f , with purely harmonic content, isconsidered:

qx1¼ 0; qx2

¼ 0; and

qz ¼ ~f dðx1 � ~x1Þdðx2 � ~x2Þ cos xt; ð10Þ

where ð~x1;~x2Þ is the position of the excitation point, and xthe excitation frequency. With this expression, Eq. (9)writes

W ðtÞ ¼ ~f cosðxtÞwðx1 ¼ ~x1; x2 ¼ ~x2; tÞ: ð11Þ

2.3. Lagrange equations of motions

The equations of motions are obtained via a Lagrangeformulation. The displacements are expanded on a set ofexpansion functions /ðuÞmn ;/

ðvÞmn;/

ðwÞmn , satisfying identically

the boundary conditions

uðx1; x2; tÞ ¼XMu;Nu

m;n¼1

umnðtÞ/ðuÞmnðx1; x2Þ; ð12aÞ

vðx1; x2; tÞ ¼XMv ;Nv

m;n¼1

vmnðtÞ/ðvÞmnðx1; x2Þ; ð12bÞ

wðx1; x2; tÞ ¼XMw;Nw

m;n¼1

wmnðtÞ/ðwÞmn ðx1; x2Þ: ð12cÞ

The explicit formulation for the selected expansion func-tions will be given in Section 4 for the HP panel, Section5 for the CC panel, and Section 6 for the Flugge shell.The number of basis functions in each direction is freeand governed by the integers Mu;Nu;Mv;Nv;Mw, and Nw.The damping forces are assumed to be of the viscous type.They are taken into account using Rayleigh’s dissipationfunction

F ¼ 1

2cZS

ð _u2 þ _v2 þ _w2ÞdS; ð13Þ

where c is the damping coefficient. In the remainder, modaldamping is assumed, such that c will give birth to modaldamping factors, that are different from one mode toanother.

Let q be the vector of generalized coordinates, gatheringtogether all the unknown functions of time introduced bythe expansions given in Eqs. (12)

q ¼ ½um;n; vm;n;wm;n�T; m ¼ 1; . . . ;Mu;Mv;Mw;

n ¼ 1; . . . ;N u;Nv;Nw: ð14Þ


In the remainder, P refers to the dimension of q, i.e. thenumber of generalized coordinates used for discretizing theshell. The generic element of q is denoted by qp.

The generalized forces Qp are obtained by differentiationof Rayleigh’s dissipation function F, provided by Eq. (13),and of the virtual work W done by external forces, Eq. (9).It reads

Qp ¼ �oFo _qpþ oW

oqp

: ð15Þ

The Lagrange equations of motion can now be expressed:

8p ¼ 1; . . . ; P :d

dtoT S

o _qp

� �� oT S

oqp

þ oU S

oqp

¼ Qp: ð16Þ

As a consequence of the kinetic energy expression, it isfound that oT S=o _qp ¼ 0. The derivation of the elastic strainenergy US with respect to qp shows very complicatedexpressions involving quadratic and cubic non-linear cou-pling terms among the equations. Finally, in the three con-sidered cases, the result of the discretization gives a set ofcoupled non-linear oscillator equations to solve. Theywrites

€qp þ 2fpxp _qp þXP

i¼1

zpi qi þ

XP

i;j¼1

zpi;jqiqj þ

XP

i;j;k¼1

zpi;j;kqiqjqk

¼ fp cosðxtÞ: ð17Þ

Modal damping in Eq. (17) is considered in the classicalform 2fpxp _qp, and f ¼ ½f1 . . . fP �T is the vector of the pro-jected external forcing considered.

2.4. Discussion on in-plane inertia

In-plane inertia must be retained for shells that cannotbe considered shallow. Moreover, for higher vibrationmodes of shallow shells, in-plane inertia must also beretained. A specific case is a closed circular cylindricalshells for modes with a number of circumferential waveslower than four or five. However, even for shallow curvedpanels and closed shells with circumferential wavenumberequal or higher than five, in-plane inertia can play a signif-icant role, as shown by Amabili [17]. For very shallow pan-els, the effect of in-plane inertia can be negligible on bothnatural frequencies and non-linear responses.

The drawback of retaining in-plane inertia is that addi-tional degrees-of-freedom must be taken into the expansionas a consequence that the simplified Donnell’s shallow-shellformulation cannot be used. Secondly, the computation ofthe eigenmodes can become more difficult. Analyticaleigenmodes of panels with in-plane inertia are simplyobtained in case of simply supported boundary conditions.In other cases, the formulation become much more com-plex and it is convenient to approach the problem numer-ically, e.g. by using the Rayleigh–Ritz method. For thesereasons, ad hoc expansion functions are here used for dis-cretizing the problem.

3. Reduced-order modeling

3.1. Reference solution

The response of the three selected shells to concentratedharmonic force is sought. The excitation frequency x isselected close to the first eigenfrequency of the systems.Frequency–response curves are numerically obtained withthe software AUTO [25], by continuation of the solutionswith the pseudo-arclength method. Bifurcation analysis,branch switching and computation of the stability is per-formed by AUTO. In practice, the shell response to har-monic excitation is found in two steps. Firstly, thefrequency x is set apart of the eigenfrequency, and the exci-tation amplitude is used as bifurcation parameter. Fromthe stable state at rest, the excitation amplitude is raisedfrom zero to the desired magnitude. Once this value isreached, the excitation frequency is then selected as bifur-cation parameter to obtain the frequency–response curve.

The reference solution is obtained with the describedmethod, applied to Eq. (17). The convergence of the solu-tions with respect to the number P of generalized coordi-nates retained has already been done in previous studies.It has been shown that, for the HP panel, P ¼ 22 basisfunctions were needed for obtaining convergence [18].For the CC panel, 19 basis functions were needed [19],whereas convergence was obtained for the Flugge shellwith 16 basis functions [17]. As a consequence of theselarge values, computation time associated with the numer-ical simulations with AUTO for obtaining a single fre-quency–response curve are large.

The next two subsections describe two strategies forreducing the dimension P, i.e. the number of oscillatorequations to simulate to recover the correct behaviour.These reduction strategies are crucial in order to reducethe important computational time associated to simula-tions with a large number of dofs, that are unavoidablewhen dealing with geometrically non-linear structures.

Direct integration of the equations of motion is also per-formed in order to obtain time responses of the selectedstructures. The Gear’s BDF method, implemented in theDIVPAG routine of the Fortran Library IMSL, has beenselected to handle the high-dimensionality of the problemassociated with stiff behaviour.

3.2. Numerical computation of the linear normal modes

The first idea for reducing the size of the system is to usethe linear normal modes (LNMs). Let L ¼ ½zp

i �p;i be the lin-ear part of Eq. (17), and P the matrix of eigenvectors(numerically computed) of L such that: P�1LP ¼ K, withK ¼ diag½x2

p�, and xp the eigenfrequencies of the structure.A linear change of coordinates is computed, q ¼ PX, whereX ¼ ½X 1 . . . X P �T is, by definition, the vector of modal coor-dinates. Application of P makes the linear part diagonal, sothat the dynamics can now be expressed in the eigenmodesbasis, and reads, 8p ¼ 1; . . . ; P :


€X p þ 2fpxp_X p þ x2

pX p þXP

i;j¼1

gpijX iX j

þXP

i;j;k¼1

hpijkX iX jX k

¼ F p cosðxtÞ: ð18Þ

The application of P let the viscous dampingunchanged, and F ¼ P�1f ¼ ½F 1 . . . F P �T is the new vectorof modal forces. The quadratic and cubic non-linear cou-pling coefficients fgp

ijg and fhpijkg are computed from the

fzpi;jg and fzp

i;j;kg appearing in Eq. (17) with matrix opera-tions involving P. The dimension of X is P, but truncationcan now be realized by keeping any number of LNMs. LetP LNM be the dimension of the truncation operated in X.Convergence studies will be realized by increasing P LNM

from 1 to P. Since the LNMs possesses some interestingproperties (in particular orthogonality), it is awaited toobtain convergence for P LNM 6 P .

3.3. Non-linear normal modes (NNMs)

Asymptotic approximation of the NNMs of theunforced structure is used to obtain further reduction ofthe size of the system. NNMs are defined as invariant man-ifold in phase space, tangent at the origin (representing thestructure at rest) to the linear eigenmodes [1]. The proce-dure, based on normal form theory, is here briefly recalled.A complete description is provided in [15,10].

A non-linear change of coordinates is performed, inorder to express the dynamics within the phase spacespanned by the invariant manifolds. The invariance prop-erty is the key that allows finding reduced-order modelsof lower dimension than those obtained using the eigen-modes [10]. The modal velocity Y p ¼ _X p is used to recastthe dynamical equation (18) into its first-order form. Thenon-linear change of coordinates, up to the third order, iscomputed once and for all. It reads, 8p ¼ 1; . . . ; P

X p ¼ Rp þXP

i¼1

XP

jPi

ðapijRiRj þ bp

ijSiSjÞ þXP

i¼1

XP

j¼1

cpijRiSj

þXP

i¼1

XP

jPi

XP

kPj

ðrpijkRiRjRk þ sp

ijkSiSjSkÞ

þXP

i¼1

XP

j¼1

XP

kPj

ðtpijkSiRjRk þ up

ijkRiSjSkÞ; ð19aÞ

Y p ¼ Sp þXP

i¼1

XP

jPi

ðapijRiRj þ bp

ijSiSjÞ þXP

i¼1

XP

j¼1

cpijRiSj

þXP

i¼1

XP

jPi

XP

kPj

ðkpijkRiRjRk þ lp

ijkSiSjSkÞ

þXP

i¼1

XP

j¼1

XP

kPj

ðmpijkSiRjRk þ fp

ijkRiSjSkÞ ð19bÞ

The newly introduced variables, ðRp; SpÞ, are respectivelyhomogeneous to a displacement and a velocity, and arecalled the normal coordinates. The introduced coefficientsin Eqs. (19) are the transformation coefficients, whose ana-lytical expressions are given in [15]. Substitution of (19)into (18) gives the dynamics expressed in the invariant-based span of the phase space. It reads, 8p ¼ 1; . . . ; P

€Rp þ x2pRp þ 2fpxp

_Rp þ hpppp þ Ap

ppp

� �R3

p þ BppppRp

_R2p

þ CppppR2

p_Rp þ Rp

"XN

j>p

hðhp

pjj þ Appjj þ Ap

jpjÞR2j þ Bp

pjj_R2

j

þðCppjj þ Cp

jpjÞRj_Rj

i

þXi<p

ðhpiip þ Ap

iip þ AppiiÞR2

i þ Bppii

_R2i þ ðC

ppii þ Cp

ipiÞRi_Ri

h i#

þ _Rp

XN

j>p

BpjpjRj

_Rj þ CpjjpR2

j

� �þXi<p

ðBpiipRi

_Ri þ CpiipR2

i Þ" #

¼ F p cosðxtÞ: ð20Þ

Eq. (20) is the normal form, up to the third order, of Eq.(18), computed without the forcing term on the right-handside. The forcing term F ¼ ½F 1 . . . F P �T is added after thenon-linear change of coordinates on the normal oscillatorequations. As a consequence of this treatment of the forc-ing term, the non-linear change of coordinate is time-inde-pendent. Hence two approximations have been used tobuild the reduced-order model based on NNMs. Firstly,the invariant manifolds are approximated via an asymp-totic development up to order three. Secondly, time-inde-pendent NNMs are used to approximate time-dependentmanifolds. In the mechanical context, a time-dependentformulation for computation of NNMs have been pro-posed by Jiang et al. [13,26], by adapting a numericalGalerkin procedure earlier developed by Pesheck et al.[12,27]. Their numerical results shows, amongst otherthings, that for moderate values of the forcing, the oscilla-tions of the manifolds are small. Moreover, taking theminto account requires a huge numerical effort.

Due to these two approximations, it is thus expected toobtain very good results for moderate values of the forcingand of the amplitude of the response. By increasing the ampli-tude of the forcing, the results are expected to deteriorate. Onepurpose of the present study is also to give an upper validitylimit, in terms of the amplitude of the response, of theseapproximated NNMs, as three different cases are tested.

On the other hand, the proposed method bears a num-ber of advantages. On the theoretical viewpoint, the mainadvantage of the NNM method is that it relies on the ideaof invariance, ensuring proper truncations, as alreadyshown in [10], and in [2] where a full comparison withthe POD method is performed. Secondly, as compared tomore numerically involved methods as the one by Jianget al. [13], the reduction process is here quick and easy touse. Finally, the number of NNMs that one must keep in

0.5

1

1.5

2

max

(w

/h)

1,1

reference

NNM

LNM

(A)


the truncation is known beforehand by simply looking atthe internal resonances in the linear spectrum. If no inter-nal resonance is present, a single NNM is enough to catchthe dynamics. This will be shown in Sections 4 and 5. Ifinternal resonances are present, one has to keep all theNNMs involved in the internal resonance. One key pointof the method presented here, relying on normal form the-ory, is that no extra work is needed to handle the case ofinternal resonance. In Section 6 concerned with the Fluggeshell, as a consequence of the fact that the shell is closed,degenerate eigenvalues are present, giving birth to compan-ion modes, linearly independent but having the same eigen-frequency. Thus 1:1 internal resonance are present, andtwo NNMs will be kept in order to reduce the system.

0.8 1 1.2 1.4 1.6 1.8 20

ω/ω1

Fig. 2. Frequency–response curve for the HP panel, harmonically excitedin the vicinity of the first eigenfrequency x1. The reference solution iscompared to the solution given by keeping a single linear mode (LNM) ora single NNM. The excitation amplitude is ~f ¼ 4:37 N. Point (A), withx ¼ 1:3x1, is used for time integration, see Fig. 5.

4. Hyperbolic paraboloid panel

4.1. Boundary conditions and projection functions

The HP panel is shown in Fig. 1. The curvilinear axialcoordinates are specified by setting x1 ¼ x, and x2 ¼ y.The radii of curvature are such that Rx ¼ �Ry .

Classical simply supported boundary conditions at thefour edges are assumed, so that:

v ¼ w ¼ N x ¼ Mx ¼ 0 at x ¼ 0; a; ð21aÞu ¼ w ¼ N y ¼ My ¼ 0 at y ¼ 0; b; ð21bÞ

where Nx;N y are the normal forces and Mx;My the bendingmoments per unit length.

The basis functions are respectively

/ðuÞm;nðx; yÞ ¼ cosðmpx=aÞ sinðnpy=bÞ; ð22aÞ/ðvÞm;nðx; yÞ ¼ sinðmpx=aÞ cosðnpy=bÞ; ð22bÞ/ðwÞm;nðx; yÞ ¼ sinðmpx=aÞ sinðnpy=bÞ: ð22cÞ

Two non-linear terms u and v are added to Eqs. (22a)and (22b), respectively, in order to identically satisfy theboundary conditions, as shown in [18].

4.2. Simulation results

Numerical simulations have been performed for a HPpanel with a ¼ b ¼ 0:1 m, Rx ¼ �Ry ¼ 1 m, and thicknessh ¼ 1 mm. The material is linear elastic with Young’s mod-ulus E ¼ 206:109 Pa, density q ¼ 7800 kg m�3 and Pois-son’s ratio m ¼ 0:3. The response of the HP panel toharmonic excitation in the vicinity of the first eigenfrequen-cy x1 is numerically computed. The convergence of thesolution has been carefully studied in [18] for an excitationamplitude ~f of 4.37 N applied at the center of the panel. Ithas been shown that 22 basis functions were necessary toobtain convergence. More precisely, the generalized coor-dinates retained for this reference solution are w1;1, w1;3,w3;1, w3;3, u1;1, u3;1, u1;3, u3;3, u1;5, u5;1, u3;5, u5;3, u5;5, v1;1,v3;1, v1;3, v3;3, v1;5, v5;1, v3;5, v5;3, v5;5. The damping parameter

fp has been set to 0.004 for each mode: 8p ¼ 1 . . .22; fp ¼ 0:004.

Fig. 2 shows the frequency–response curve for this refer-ence solution, numerically obtained by a continuationmethod (pseudo-arclength is used) implemented withinthe software AUTO [25]. The reference solution with 22basis functions is compared to two severely reduced-ordermodels, composed of a single oscillator equation. The firstone is obtained by keeping in the truncation only the firstLNM (P LNM ¼ 1). Eq. (18) are restricted to the first one

€X 1 þ 2f1x1_X 1 þ x2

1X 1 þ g111X 2

1 þ h1111X 3

1

¼ F 1 cosðxtÞ: ð23Þ

Branches of solution are numerically obtained by continu-ation with AUTO, then the original coordinates are recov-ered via: q ¼ PX, where, in X, only the first coordinate X 1

is different from zero.The second reduced-order model is obtained by keeping

the first NNM: Eq. (20) are truncated by lettingRp ¼ 0; 8p ¼ 2 . . . 22: The dynamics onto the invariantmanifold is then governed by

€R1 þ 2f1x1_R1 þ x2

1R1 þ ðh1111 þ A1

111ÞR31 þ B1

111R1_R2

1

þ C1111R2

1_R1 ¼ F 1 cosðxtÞ: ð24Þ

Eq. (24) is solved numerically with AUTO, then oneuses Eqs. (19) to come back to the modal coordinates,and finally the matrix of eigenvectors P allows reconstitu-tion of the amplitudes in the basis of selected projectionfunctions. Thanks to the non-linear nature of the changeof variable (19), all the modal amplitudes are non-zero.

Fig. 2 shows the main coordinate w1;1, having the mostsignificant response. One can observe that the non-linearity


is of the hardening type, and that the amplitude of theresponse, of the order of two times the thickness, is large.The two reduced models have been selected because theyshare the same complexity: a single oscillator equation isused. Whereas reduction to a single linear mode gives poorresult, reduction to a single NNM give a satisfactory result,with a slight overestimation of the maximum vibrationamplitude.

Moreover, as shown in Fig. 3, the reduced model com-posed of a single NNM, thanks to the non-linear changeof coordinate, allows recovering all the other coordinatesthat are not directly excited. Fig. 3 shows the six maincoordinates, i.e. the first four coordinates in transversedirection, w1;1, w3;1, w1;3 and w3;3, as well as the first twolongitudinal coordinates u1;1 and v1;1. It is observed thatwith the NNM ROM, energy is recovered in all the coordi-nates, with a good approximation of the original ampli-tudes. On the other hand, for the model composed of asingle linear mode, non-zero amplitudes are recovered onlyon w1;1, u1;1 and v1;1, as these three coordinates are linearlycoupled to create the first eigenmode described by X 1 whichis simulated. But a vanishing response is found with thisLNM ROM for w3;1, w1;3 and w3;3.

This first result emphasizes the main characteristic of theNNM ROM: the geometrical complexity due to the curva-ture of the invariant manifold, is first computed in the non-linear change of coordinates. Once the dynamics reducedto the manifold, a single oscillator equation is sufficientto recover the dynamics. Then, coming back to the originalcoordinates allows recovering energy onto the slave modesthanks to the non-linear projection.

1 1.5 20

0.5

1

1.5

2

10

0.05

0.1

0.15

0.2

1 1.50

0.01

0.02

0.03

0.04

1 1.0

0.05

0.1

1

max

(w

/h)

max

(u

/h)

max

(w

/h)

1,1

1,1

max

(w

/h)

3,1

3,3

NNM

NNM

NNM

LNM

LN

ω/ω ω

1ω/ω ω

Fig. 3. Maximum amplitude of the response of six generalized coordinatesReference solution (thick line) is compared to the reduction to a single linear momaximum of w3;1, (c) maximum of w1;3, (d) maximum of w3;3, (e) maximum o

Fig. 4 shows a representation of the invariant manifold(the first NNM) for the HP panel. The dimension of thephase space is 45 (22 oscillator equations with displacementand velocity as independent variables plus the externalforcing), and the NNM surface is two-dimensional. A pro-jection in the reduced space ðw1;1; _w1;1;w3;1Þ is shown. A tra-jectory is also represented, which has been computed bynumerically integrating the original system described byEq. (17). The closed orbit represents the true solution, asthe reference equations have been used. One can observethat the closed orbit do not fully belong to the invariantmanifold. This is the consequence of the two assumptionsused to generate the NNM solutions: a third-order asymp-totic development is used to approach the invariant mani-fold, and secondly, a time-invariant manifold is used. As aconsequence, the trajectory do not fall completely withinthe NNM. However a good approximation of the localgeometry is provided.

The time solutions for the four most significant coordi-nates is shown in Fig. 5. Once again, the reference solutionis compared to the two reduced models composed of a sin-gle linear and non-linear mode. Time integrations havebeen performed for ~f ¼ 4:37 N and x ¼ 1:3x1 (Point (A)in Fig. 2). Whereas the reduction to a single linear modeis not acceptable, the solutions provided by a singleNNM are very good. Despite the fact that only oneoscillator-equation is simulated, a variety of complexsignals are recovered thanks to the non-linear change ofcoordinates.

The convergence of the solution with an increasingnumber of LNMs is shown in Fig. 6 for the excitation

1.5 1 1.50

0.05

0.1

0.15

5 2 1 1.5 20

0.02

0.04

0.06

0.08

max

(w

/h)

max

(v

/h)

1,1

1,3

NNMNNM

NNM

LNM

M

1/ω

1ω/ω

1/ω

1ω/ω

versus excitation frequency, for an excitation amplitude of ~f ¼ 4:37 N.de (LNM) and a single non-linear mode (NNM): (a) maximum of w1;1, (b)

f u1;1 and (f) maximum of v1;1.

−20

2.5

−2

0

2

−0.08

0

0.12

w1,1

1,1

w3,1

w

Fig. 4. The invariant manifold (first NNM) for the HP panel in the reduced phase space ðw1;1; _w1;1;w3;1Þ, calculated with the third-order approximationderived from Eqs. (19). The orbit has been computed by integrating the temporal dynamics of the reference solution, with ~f ¼ 4:37 N and x ¼ 1:3x1.

1.2425 1.243 1.2435 1.244

x 104

−1.5

0

1.5

1.2425 1.243 1.2435 1.244

x 104

−0.06

−0.03

0

0.03

0.06

1.2425 1.243 1.2435 1.244

x 104

−0.01

0

0.01

1.2425 1.243 1.2435 1.244

x 104

−0.03

0

0.03

0.06

w1,

1

w3,

1u

1,1

w3,

3

t [non−dim] t [non−dim]


Fig. 5. Time-domain response of four generalized coordinates of the HP panel, excitation frequency x ¼ 1:3x1, amplitude ~f ¼ 4:37 N. Reference solution(thick line) is compared to the NNM solution (thin line), and the LNM solution (dashed line).


amplitude of 4.37 N. It is found that the convergence isvery slow: 15 LNMs are necessary to obtain an acceptablesolution. The solution with 11 LNMs is qualitatively differ-ent from the converged solution with a strange loopappearing in the frequency response, and is thus notacceptable. Hence a very slow convergence with respect

to increasing P LNM is found, and using the linear normalmodes is not very favourable as compared to the projectionfunctions used. On the other hand, it has been found thatincreasing the number of NNMs kept in the truncation inEq. (20) do not change anything in the solution: the addedNNMs have been found to stay with constant neglectable

0.8 1 1.2 1.4 1.6 1.8 2 2.20

0.5

1

1.5reference

1 LNM

5 LNM

11 LNM

15 LNM

max

(w

/h)

1,1

ω/ω1

Fig. 6. Maximum amplitude response of w1;1 versus excitation frequencyfor ~f ¼ 4:37 N, showing the convergence of the solution when increasingP LNM. Reference solution (22 basis functions) is compared to truncationswith 1 linear mode, 5 LNM, 11 LNM and 15 LNM.


amplitude, and the same solution is found as the oneobtained with a single NNM. This is a logical consequenceof the invariance property of the NNMs. Hence the solu-tion with a single NNM seems to be the best ROM possi-ble. The only way to improve the results found here is notin increasing the number of NNMs, but in overshootingthe two limitations of the present approximation used forgenerating the NNMs.

Finally, the robustness of the ROMs with respect toincreasing the amplitude of the forcing, is studied. Fig. 7shows the results obtained for a lower excitation ampli-tude: ~f ¼ 2:84 N, and for a larger one:~f ¼ 6:62 N. For~f ¼ 2:84 N, the result given by the NNM ROM is almostperfectly coincident with the reference solution obtainedwith 22 basis function, whereas the model with a singlelinear mode give unacceptable results. For the larger ampli-

0.8 1 1.2 1.4 1.6 1.80

0.5

1

1.5

max

(w

/h)

1,1

refNNM

LNM

ω/ω 1

Fig. 7. Frequency–response curve for (a) ~f ¼ 2:84 N, and (b) ~f ¼ 6:62 N. Ref(LNM) and a single non-linear mode (NNM).

tude, ~f ¼ 6:62 N, the result deteriorates for the NNM-reduced model, which is not able to catch the saturationloop found by the reference solution at the top of the fre-quency–response curve. The observation of the other coor-dinates (not shown for the sake of brevity) shows that thisloop reflects the fact that most of the energy is, at thispoint, absorbed by the higher modes, the amplitude ofwhich significantly and abruptly increase. This subtilchange in the dynamics of the system is not caught bythe reduced model, which overpredict the maximumamplitude.

As a conclusion on the HP panel, the dynamics has beenreduced from 22 dofs to a single NNM. Results shows thatthe reduction, computed with an asymptotic expansion toapproach the invariant manifold, gives very good resultsfor vibration amplitudes up to 1.5 times the panel thicknessh. Beyond this value, the two approximations used for gen-erating the ROM do not hold anymore. On the other hand,using truncations with LNMs did not allow substantialimprovement as compared to the selected basis functionsused for discretizing the problem.

5. Circular cylindrical panel


The CC panel is shown in Fig. 8. The coordinates usedto describe the geometry are x1 ¼ x and x2 ¼ h, where ðx; hÞare the cylindrical coordinates shown in Fig. 8. As a conse-quence, the radii of curvature are such that R1 ¼ Rx ¼ 1,and R2 ¼ R. The angular span is a, length is a and thicknessh. The selected boundary conditions are:

w ¼ N x ¼ Mx ¼ 0; N x;y ¼ 0; at x ¼ 0; a; ð25aÞw ¼ N y ¼ My ¼ 0; Ny;x ¼ 0; at y ¼ 0; b; ð25bÞ

where y ¼ Rh and b ¼ Ra. They modelize a restrained con-dition in transverse direction with fully free in-planedisplacements.

1 1.5 2 2.50

0.5

1

1.5

2

2.5

max

(w

/h)

1,1

ω/ω 1

ref

NNM

LNM

erence solution (ref) is compared to truncations with a single linear mode

Fig. 8. Geometry and coordinates axis for the circular cylindrical panel.


The basis functions are respectively

/ðuÞm;nðx; yÞ ¼ cosðmpx=aÞ cosðnph=aÞ; ð26aÞ/ðvÞm;nðx; yÞ ¼ cosðmpx=aÞ cosðnph=aÞ; ð26bÞ/ðwÞm;nðx; yÞ ¼ sinðmpx=aÞ sinðnph=aÞ: ð26cÞ

Two non-linear terms u and v are added to Eqs. (26a)and (26b), respectively, in order to identically satisfy theboundary conditions, as shown in [19,28].


Numerical simulations have been performed for a spe-cific panel with a ¼ 0:1 m, R ¼ 1 m and h ¼ 1 mm. Theangular span is a ¼ 0:1 rad, so that the panel length equalsthe circumferential width. Material properties are identicalto that used for the HP panel so that E, q and m areunchanged. The CC panel response to harmonic excitationin the vicinity of the first eigenfrequency is studied. Theconvergence of the reference solution has been carefullychecked in [19,28], for an excitation amplitude of~f ¼ 4:4 N applied at the center of the panel. It has beenfound that the minimal number of basis functions should

0.9 1 1.1 10

0.25

0.5

0.75

ω/ω1

LNM

max

(w

/h)

1,1

Fig. 9. Maximum amplitude of coordinate w1;1 versus excitation frequency freference solution. Truncated solution with a single linear mode (LNM) is als

be 19. This solution will be referred to as the reference solu-tion; the selected basis functions are: w1;1, w1;3, w3;1, w3;3,u1;0, u1;2, u1;4, u3;0, u3;2, u3;4, v0;1, v2;1, v4;1, v0;3, v2;3, v4;3, v0;5,v2;5, v4;5. Damping coefficient fp has been set equal to0.004 for each generalized coordinate.

Fig. 9 shows the response of the main coordinate w1;1 foran excitation amplitude of ~f ¼ 2:2 N. The reference solu-tion, obtained with 19 dofs, is contrasted to two ROMscomposed of a single dof: a single LNM and a singleNNM. The results are comparable to those obtained forthe HP panel. The response of the panel is of the hardeningtype. The restriction to a single linear mode is a too severetruncation that leads to a huge overestimation of the hard-ening behaviour of the panel. On the other hand, theresponse provided by the NNM ROM is quasi-coincidentwith the reference solution.

As already mentioned for the HP panel, the NNMROM allows recovering non-directly excited coordinatesthanks to the non-linear relationship between the original(modal) coordinates and the master mode that is retainedfor simulation. Comparison of other coordinates areshown in Fig. 10. A particular feature of this model isthe weak coupling observed between the coordinates. Thisis revealed here by the very small values of maximumamplitude of the non-directly excited coordinates, recov-ered via the changes of variables: they are an order of mag-nitude less compared to the HP panel. On the geometricalviewpoint, it means that the invariant manifold is ratherflat. The non-linearity is here more focused on the self-exciting terms present in the normal form than in thecoupling amongst eigenmodes, which are treated by thecurvature of the NNM manifold. The convergence ofthe reduced systems have also been tested. As in the prec-edent case of the HP panel, a very slow convergence withincreasing the number of linear modes have been found:15 LNMs were necessary in order to recover the originalresults. Other more severe truncations with a number oflinear modes less or equal than 8 gave unacceptable results.

Fig. 11 shows the comparison between the NNM ROMand the reference solution, for an excitation amplitude of

.2 1.30.99 1 1.01

0.5

0.6

0.7

0.8

zoom

reference

NNM

or the CC panel, ~f ¼ 2:2 N. NNM solution is quasi-coincident with theo shown.

0.96 1 1.04 1.080

0.005

0.01

0.9 1 1.1 1.20

0.01

0.02

0.96 1 1.04 1.080

0.5

1

1.5

2x 10

−3

0.96 1 1.04 1.080

2

4

6x 10

−3

ω/ω1 ω/ω1

ω/ω1ω/ω1

NNM

LNM

NNM

LNM

NNM

NNM

max

(w

/h)

max

(u

/h)

max

(w

/h)

max

(w

/h)

3,1

1,3

3,3

1,0

Fig. 10. Maximum amplitude versus excitation frequency, CC panel, ~f ¼ 2:2 N. Reference solution (thick line) is compared to single NNM and singleLNM solutions. Four non-directly excited coordinates are shown: (a) w3;1, (b) w1;3, (c) w3;3 and (d) u1;0.

0.94 0.97 1 1.03 1.06 1.090

0.5

1

1.5

0.94 0.97 1 1.03 1.06 1.090

1

2

3

ω/ω1 ω/ω1

−min

(w

/h)

1,1

1,1

max

(w

/h)

reference

NNM

NNM

reference(B)

(B)

Fig. 11. Frequency–response curve for coordinate w1;1, excitation amplitude of 4.4 N: (a) maximum amplitude response (outwards deflection) and (b)minimum amplitude response (inwards deflection). Reference solution is compared to single NNM truncation. Point (B), with x ¼ x1, is used for timeintegration, see Fig. 12.


4.4 N. The results provided by the single linear mode ROMhas not been plotted as it was completely unacceptable. Asa consequence of the weak coupling amongst generalizedcoordinates detected before, the NNM simulation fails inrecovering the resonance curve for this level of excitation.It can be explained by the fact that the NNM ROM, inits third-order asymptotic approximation used here, hasthe primary ability to catch very well the coupling amongstlinear modes through the non-linear change of coordinates.As these couplings are here weak, the ROM is rapidly lim-ited by its third-order expansion, that shows some difficul-ties to recover the non-linearity exhibited in this case.

Moreover, the reference simulation shows an importantasymmetry between outwards displacements (Fig. 11a withthe maximum amplitude) and inwards displacements(Fig. 11b with the minimum amplitude). This asymmetryis caught by the NNM ROM but dramatically increased.This, once again, shows that, in this case, the third-orderexpansion is not enough to have a good approximationof the dynamics.

Direct integration of the equations of motion for the ref-erence model is compared to the single LNM and NNMtime simulations in Fig. 12, for this large value of excitation~f ¼ 4:4 N, and x ¼ x1. As predicted by the frequency–

1.2065 1.207 1.2075 1.208 1.2085 1.209

x 104

−1

−0.5

0

0.5

1

1.2065 1.207 1.2075 1.208 1.2085 1.209

x 104

−5

0

5

10

15

20x 10

−3

1.2065 1.207 1.2075 1.208 1.2085 1.209

x 104

−0.005

0

0.01

0.02

0.03

1.2065 1.207 1.2075 1.208 1.2085 1.209

x 104

−2

0

2

4

6

8x 10

−3

w1,

1w

1,3



w3,

1u

1,0

Fig. 12. Time-domain response of four generalized coordinates of the CC panel, excitation frequency x ¼ x1, amplitude ~f ¼ 4:4 N. Reference solution(thick line) is compared to the NNM solution (thin line), and the LNM solution (dashed line).


response curve, the asymmetry is overestimated by theNNM ROM. However, as in the case of the HP panel, alarge variety of non-linear temporal signals are well recov-ered, whereas a single oscillator-equation is simulated.

Finally, in the case of the CC panel, the NNM ROMgives good results for vibration amplitudes up to 0.9h.

6. Closed circular cylindrical shell


The third example is a closed, empty shell of length a.The geometry and coordinate system is deduced from theCC panel by selecting a ¼ 2p for the angular span.Whereas the strain–displacement relationship for the twoprecedent example was given by Donnell’s non-linear the-ory with in-plane inertia, Flugge-Lur’e-Byrne non-lineartheory is used here. The reader is referred to [17,23,24]for a more thorough description of the kinematics.

The boundary conditions are simply supported at thetwo ends x ¼ 0; a

w ¼ Mx ¼ v ¼ N x ¼ 0; at x ¼ 0; a; ð27Þ

where Mx and Nx are respectively the bending moment andthe axial force per unit length.

The response of the shell to harmonic forcing in thevicinity of mode ðm; nÞ, where m is the number of longitu-

dinal half-waves, and n of circumferential waves, is consid-ered. Based on past studies, where a detailed convergencestudy was considered for mode (1,5) (see e.g. [17] and ref-erences therein), the minimal expansion used for discretiz-ing the shell has been found to be the following:

uðx; h; tÞ ¼X2

k¼1

½u1;5k;cðtÞ cosð5khÞ þ u1;5k;sðtÞ sinð5khÞ� cosðk1xÞ

þX2

m¼1

u2m�1;0ðtÞ cosðk2m�1xÞ þ u; ð28aÞ

vðx; h; tÞ ¼X2

k¼1

½v1;5k;cðtÞ sinð5khÞ þ v1;5k;sðtÞ cosð5khÞ� sinðk1xÞ

þ ½v3;10;cðtÞ sinð10hÞ þ v3;10;sðtÞ cosð10hÞ� sinðk3xÞ;ð28bÞ

wðx; h; tÞ ¼ ½w1;5;cðtÞ cosð5hÞ þ w1;5;sðtÞ sinð5hÞ� sinðk1xÞ

þX2

m¼1

w2m�1;0ðtÞ sinðk2m�1xÞ; ð28cÞ

where km ¼ mpa , and u is a non-linear term added to satisfy

exactly the boundary condition N x ¼ 0. Because of the cir-cumferential symmetry, degenerate modes appear in thestructure; they are here denoted with the additional sub-script c or s, indicating if the generalized coordinates isassociated with a cos or sin function in the angular coordi-nate h for w. This expansion gives the reference solution,


which is obtained here with 16 generalized coordinates.One can observe that the basis functions are in fact theeigenmodes of the empty shell for the transversecomponent.

The point excitation considered is located at a node ofthe mode ð1; 5; sÞ. Consequently, mode ð1; 5; cÞ is calledthe driven mode, and mode ð1; 5; sÞ, which is not directlyexcited by the external load, is the companion mode. Thedamping coefficient fp is selected such that fp ¼ f ¼ 0:001for each asymmetric modes, whereas for axisymmetricmodes (present in the truncation via w1;0; w3;0; u1;0 andu3;0) we have: f1;0 ¼

x1;0

x1;5f and f3;0 ¼

x3;0

x1;5f.


Numerical simulations have been performed for a shellwhose geometric dimensions are: a ¼ 520 mm, R ¼

0.992 0.994 0.996 0.998 1 1.0020

0.5

1

1.5

2

1,5,

cm

ax(w

/h)

ω/ω1,5

BP

BPTR

TR

Fig. 13. Maximum amplitude of vibration versus excitation frequency for the Fsolution (thick line) to the ROM composed of two NNMs (NNM): (a) maximucompanion mode wð1;5;sÞ. BP: branch points on the single-mode branch of solutibifurcation points leading to quasi-periodic solutions.

0.98 1 1.020

0.5

1

1.5

2

2.5

3

3.5

4

4.5

1,5,

cm

ax(w

/h)

ω/ω1,5

NNM

reference

Fig. 14. Maximum amplitude of vibration versus excitation frequency for theROm composed of two NNMs (NNM): (a) maximum amplitude of the driven

149:4 mm, h ¼ 0:519 mm. Material properties are:E ¼ 1:98� 1011 Pa, q ¼ 7800 kg m�3, m ¼ 0:3. As a conse-quence of the circumferential symmetry and the appearanceof degenerate modes, 1:1 internal resonances are present inthe system. More particularly in the present case, the drivenmode and the companion mode are 1:1 internally resonant.Hence the minimal model that could capture the dynamicsshould contain at least two oscillator equations. This mini-mal model is given by keeping the first two NNMs, corre-sponding respectively to the continuation of driven andcompanion modes, in the same way as the truncation real-ized on a fluid-filled cylindrical shell described by Donnellshallow-shell theory, see [15,2].

In the remainder of the study, the reference solutionobtained with 16 basis functions will be compared to thesolution given by the reduced model composed of 2NNMs. The comparison with a truncation of linear modes,

0.992 0.994 0.996 0.998 1 1.0020

0.2

0.4

0.6

0.8

1

1.2m

ax(w

/h)

1,5,

s

ω/ω1,5

BP BP

TR

TR

reference

NNM

lugge shell, with an excitation amplitude of 2 N. Comparison of referencem amplitude of the driven mode wð1;5;cÞ and (b) maximum amplitude of theon, leading to coupled solutions (branch 2). TR: Neimarck-Sacker (Torus)

0.97 0.98 0.99 1 1.010

0.5

1

1.5

2

2.5

max

(w

/h

)1,

5,s

ω/ω1,5

reference

NNM

Flugge shell, ~f ¼ 4 N. Comparison of reference solution (thick line) to themode wð1;5;cÞ and (b) maximum amplitude of the companion mode wð1;5;sÞ.

Table 1Comparisons of accuracy and computational times for the three selectedmodels

Reference LNM NNM

HP Panel 22 dofs 1 dof 1 dofComp. time 1 h 56 min 36 s 4 min 47 sValidity limits / 0.1h 1.5h

CC Panel 19 dofs 1 dof 1 dofComp. time 1 h 28 min 35 s 3 min 43 sValidity limits / 0.1h 0.9h

Flugge shell 16 dofs 2 dofs 2 dofsComp. time 1 h 37 min / 2 min 48 sValidity limits / 0.1h 3h

The computational time is defined as the time needed for computing atypical frequency–response curves. For the reference solution, thisincludes the time spent during an AUTO-run. For the LNM ROM, to thetime spent in an AUTO-run is added the time spent in the linear change ofcoordinates (application of P). For the NNM ROM, the time spent forcomputing and applying the non-linear change of coordinate is alsoadded. The amplitude of the forcing used for this table is: 4.37 N for theHP panel, 4.4 N for the CC panel, and 2 N for the Flugge shell. Com-putations have been realized on a standard PC with a Pentium IV pro-cessor working at 2.4 GHz. Computational time associated to the Fluggeshell reduced to two LNMs is not mentioned as the model has not beenable to recover to two solution branches.


as in the precedent cases, will not be shown for the follow-ing reason. Once again, the convergence of the solutionwith the number of linear modes was very slow. Moreover,all the truncations tried with an increasing number of linearmodes predicted a hardening-type non-linearity, except thesolution with 16 linear modes which recovers the originalsolution with a softening-type non-linearity for the drivenmode. Hence the minimal number of linear modes is also16, and no other truncation is acceptable.

Fig. 13 shows the comparison between the referencesolution and the reduced model composed of two NNMs,for an excitation amplitude ~f ¼ 2 N. The solution is com-posed of two branches. The first branch corresponds to thesingle-mode response: the companion mode has a zeroamplitude. This branch displays a softening-type non-line-arity, and shows two branch points (BP), from which thesecond branch arises. This second branch corresponds tocoupled solutions where both driven and companion modehave a non-zero amplitude. Following branch 2, a bifurca-tion occurs via torus (Neimarck-Sacker) bifurcations (TR),leading to a quasi-periodic regime.

As shown in Fig. 13, the reduced model perfectly recov-ers all the details of this complicated bifurcation diagram.A slight overestimation of the softening non-linearity isdetected, but all the bifurcation points, as well as their nat-ure, are perfectly recovered. In contrast, no other solutionwith a truncation with the linear modes, was able to catchthe softening type non-linearity. This excellent result con-firms earlier investigations led on a fluid-filled cylindricalshell, see [15,2].

The robustness of the ROM is tested by increasing theexternal forcing amplitude up to ~f ¼ 4 N. The correspond-ing frequency–response is shown in Fig. 14. Despite anincrease in the overestimation of the maximum amplitude,all the bifurcation points are once again recovered. Fromthese studies, it can be concluded that the ROM is reliablefor vibration amplitudes up to 3h.

7. Discussion

Reduction methods is a central question in the simula-tion of vibrating structures. Many different methods havebeen proposed in the past, one of the most popular beingthe Proper Orthogonal Decomposition (POD) method [3–5,29]. In this paper, the NNMs of the unforced structureare tested as basis functions for reducing the dynamicsfor shell models with harmonic forcing.

On the computational viewpoint, one of the main draw-back of the present method is the number of coefficientsthat have to be computed for obtaining the reduced model.The main task consists in the computation of all the linearfzp

i gp;i¼1...P , quadratic fzpi;jgp;i;j¼1...P and cubic fzp

i;j;kgp;i;j;k¼1...P

coupling coefficients appearing in Eq. (17). This can be seenas an extra work as compared to other methods, e.g. dis-cretization based on finite elements procedures, where thesecoefficients are generally not computed for solving out tem-poral response for instance. However, in the context of this

study where one is interested with frequency–responsecurves with bifurcation points, this step is necessary. Itcan also be remarked that the computation of these coeffi-cients are here realized on the basis of analytical develop-ments, however they can easily be implemented within afinite-element based discretization. The second family ofcoefficients that have to be computed are those from thenon-linear change of coordinates defined by Eqs. (19).However the numerical burden associated with this stepis limited, so that this does not appear as a limiting factorof the method. Moreover, all these computations are madeonce and for all, and for the unforced structure, so thatthese can be seen as off-line calculations, that have not tobe repeated for computing other responses. This is ofcourse an advantage as compared to the POD method.

An assessment of the computational burden associatedwith the numerical results shown in previous section isgiven in Table 1. The computational times are only indica-tory, as they strongly depend on the processor and onnumerous parameters that can be tuned in a typicalAUTO-run. Moreover, the computation of solutionbranches with AUTO depends on the complexity of thesolution, thus the computational time also depends onthe amplitude of the forcing. These values are here givenin order to better quantify the gain in using ROMs in typ-ical situations, which is very important. A typical AUTO-run for computing a single-dof frequency–response curveis of the order of 30 s (values given for the LNM ROM).For the NNM ROM, about 3 min are spent in order tocompute the non-linear change of coordinates, that areadded to the 30 s of the AUTO-run. However, as thenon-linear change of coordinates is computed once andfor all, the single-dof NNM ROM can be used for comput-


ing any solution, so that the computational time indicatedin the NNM column must be understood as an upper limit.From Table 1, one can see that the computation timesobtained with the NNM ROMs have been reduced by asignificant factor, ranging from 23 (HP panel) to 32(Flugge shell).

The upper validity limit has also been estimated in eachcase by increasing the amplitude of the forcing. No validitylimits is indicated for the reference solution. However, iflarger values of the forcing would have been considered,the convergence study with the projection functions shouldhave been done once again. The reduction to a single LNMgenerally provided poor results, and once the value of 0.1times the thickness h is reached, the reduction to a singleLNM is not acceptable. For the single NNM ROM, thisvalue is much larger. It has been found that the NNMROM was very accurate for amplitude up to 1.5h for theHP panel, 0.9h for the CC panel, and 3h for the Fluggeshell. To these three cases, the case of the water-filled circu-lar cylindrical shell studied in [2] can be added, where theaccuracy has been estimated to 2.5h.

Finally, one can also remark that the present reductionmethod is particularly efficient for harmonically forcedresponses, as the motion is confined in the vicinity of theNNMs. However, for other dynamical behaviour (e.g. freevibration of response to white noise), the benefit in usingNNMs instead of LNMs is questionable. Due the dynam-ical characteristics, it is not awaited, in these cases, toobtain as good results as those presented here for forcedresponses.

Further research in the area of model reduction withNNMs will consist in application of the present methodto structures discretized with finite elements procedures.As shown in this study, the method can handle differentkinematics, and thus can be interfaced with a finite ele-ments method. Overcoming the limitation of the asymp-totic development is also the key to a reliable solutionthat is not amplitude-dependent.

8. Conclusion

The non-linear response to harmonic forcing in thevicinity of the first eigenfrequencies of three shell structureshave been studied. Particular attention has been paid to thederivation of reduced-order models (ROMs), that could beable to describe with accuracy the non-linear frequency–response curves. Linear normal modes and non-linear nor-mal modes computed by an asymptotic approach havebeen used, for three selected systems: a hyperbolic parabo-loid panel, a circular cylindrical panel and a closed emptycircular cylindrical shell.

For the first two cases, the reduction to a single NNMhas been possible, showing very good results for moderatevibration amplitude. On the other hand, it has beenobserved that using the LNMs did not allow for a substan-tial improvement of the results, as compared to the firstexpansion functions used for discretizing the panels. A sin-

gle LNM gives unacceptable results, and the linear conver-gence was very slow in the two cases. Using NNMs thusappears as the best solution for reducing the system. Inthe third case, a 1:1 internal resonance was present in thesystem, so that the minimal model was composed of twoNNMs, and showed very good results in recovering everybifurcations points as well as the nature of the dynamicalregimes.

However, the NNM ROMs have been computed withtwo approximations: a third-order asymptotic developmentis used to approach the invariant manifold, and time-invariant NNM is used whereas a time-dependent oneshould be used to recover the dependence introduced bythe external forcing. Hence, for large amplitude of vibra-tions, the results deteriorate.

As a conclusion, one can note that the present reductionmethod bears a number of advantage, as it is quick andeasy-to-use, and overcomes the problems of internal reso-nances without extra work. Its reliability can be said tobe very good up to h for shell structures, and generallycan give good results up to 2h except in the case wherethe coupling between the modes is weak. To overcome thislimitation, the two approximations presently used for gen-erating the NNMs must be revised.

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