Open access peer-reviewed chapter

Vibration Method in Stability Analysis of Planar Constrained Elastica

By Jen-San Chen and Wei-Chia Ro

Submitted: October 14th 2011Reviewed: March 29th 2012Published: August 1st 2012

DOI: 10.5772/45806

Downloaded: 1376

1. Introduction

The primary goal of the research in constrained elastica is to understand the behavior of a thin elastic strip under end thrust when it is subject to lateral constraints. It finds applications in a variety of practical problems, such as in compliant foil journal bearing, corrugated fiberboard, deep drilling, structural core sandwich panel, sheet forming, non-woven fabrics manufacturing, and stent deployment procedure. By assuming small deformation, Feodosyev (1977) included the problem of a buckled beam constrained by a pair of parallel walls as an exercise for a university strength and material course. Vaillette and Adams (1983) derived a critical axial compressive force an infinitely long constrained elastica can support. Adams and Benson (1986) studied the post-buckling behavior of an elastic plate in a rigid channel. Chateau and Nguyen (1991) considered the effect of dry friction on the buckling of a constrained elastica. Adan et al. (1994) showed that when a column with initial imperfection positioned at a distance from a plane wall is subject to compression, contact zones may develop leading to buckling mode transition. Domokos et al. (1997), Holms et al. (1999), and Chai (1998, 2002) investigated the planar buckling patterns of an elastica constrained inside a pair of parallel plane walls. It was observed that both point contact and line contact with the constraint walls are possible. Kuru et al. (2000) studied the buckling behavior of drilling pipes in directional wells. Roman and Pocheau (1999, 2002) used an elastica model to investigate the post-buckling response of bilaterally constrained thin plates subject to a prescribed height reduction. Chen and Li (2007) and Lu and Chen (2008) studied the deformation of a planar elastica inside a circular channel with clearance. Denoel and Detournay (2011) proposed an Eulerian formulation of the constrained elastica problem.

The emphasis of these studies was placed on the static deformations of the constrained elastica. Very often, multiple equilibria under a specified set of loading condition are possible. Since only stable equilibrium configurations can exist in practice, there is a need to determine the stability of each of these equilibria in order to predict the behavior of the constrained elastica as the external load varies. For an unconstrained elastica, vibration method is commonly used to determine its stability; see Perkins (1990), Patricio et al. (1998), Santillan, et al. (2006), and Chen and Lin (2008). This conventional method, however, becomes useless in the case of constrained elastica.

The difficulty of the conventional vibration method arises from the existence of unilateral constraints. A unilateral constraint is capable of exerting compressive force onto the structure, but not tension. Mathematically, this type of constraints can be represented by a set of inequality equations. This poses challenges in determining the critical states of the loaded structure. In order to overcome this difficulty, the conventional stability analysis needs modification. In this chapter, we introduce a vibration method which is capable of determining the stability of a constrained elastica once the equilibrium configuration is known. The key of solving the vibration problem in constrained elastica is to take into account the sliding between the elastica and the space-fixed unilateral constraint during vibration.

In this chapter, we consider the vibration of an elastica constrained by a space-fixed point constraint. This particular constrained elastica problem is used to demonstrate the vibration method which is suitable to analyze the stability of a structure under unilateral constraint. In Section 2, we describe the studied problem in detail. In Section 3, we describe the static load-deflection relation. In Section 4, we introduce the theoretical formulation of the vibration method. In Section 5 an imperfect system when the point constraint is not at the mid-span is analyzed. In Section 6, several conclusions are summarized.

2. Problem description

Figure 1 shows an inextensible elastic strip with the right end fully clamped at a point B. On the left hand side there is a straight channel with an opening at point A. The distance between points A and B is L. Part of the strip is allowed to slide without friction and clearance inside the channel. A longitudinal pushing force FAis applied at the left end of the strip inside the channel causing it to buckle in the domain of interest between points A and B. An xy-coordinate system is fixed at point A. A point H fixed at position x=L/2and y=hprevents the elastica from deforming freely after the elastica contacts point H.

The elastic strip is assumed to be straight and stress-free when FA=0. The effect of gravity is ignored. The strip is uniform in all mechanical properties along its length. The length and the shape of the elastica in the domain of interest vary as the pushing force FAincreases. The boundary condition at point A may be called “partially clamped,” by which we mean that the strip is allowed to slide freely through the opening A, while the lateral displacement and slope at A are fixed. The dashed and solid curves in Figure 1 represent two typical stages of the elastica deformation when FAincreases beyond the buckling load. The dashed curve is a symmetric deformation pattern before the elastica contacts the point constraint. The solid curve represents an asymmetric deformation after the elastica contacts the point H. Other deformation patterns may also exist, which will be discussed later.

Figure 1.

An elastica constrained by a space-fixed point at H. The dashed and solid curves represent typical symmetric and asymmetric deformations, respectively.

3. Load-deflection relation

The equilibrium equation at any point (x,y) of the buckled strip between points A and B, as shown in Figure 1, can be written as

EIdθds=QAxFAy+MAE1

QAand MAare the internal shear force and bending moment, respectively, provided by the partial clamp at A. θ(positive when counter-clockwise) is the rotation angle of the strip at point (x,y). EI is the flexural rigidity of the elastic strip. s is the length of the strip measured from point A. For convenience we introduce the following dimensionless parameters (with asterisks):

(s*,x*,y*)=(s,x,y)L,(Q*A,FA*)=L24π2EI(QA,FA),MA*=L4π2EIMAt=1L2EIμ t,ω=L2μEI ω

μis the mass per unit length of the elastica. t is time and ωis a circular natural frequency, which will be discussed in the dynamic analysis later. After substituting the above relations into Equation (1), and dropping all the superposed asterisks thereafter for simplicity, we obtain the dimensionless equilibrium equation

dθds=4π2(MAQAxFAy)E4

The method of static analysis can be found in Chen and Ro (2010). In this section we introduce several deformation patterns of the constrained elastica. All the physical quantities described henceforth are dimensionless.

The length of the elastica being pushed in through the opening isΔl=l1, where l is the dimensionless length of the elastica between points A to B. Figure 2 shows the relation between the edge thrust FAand the length incrementΔl. The height of the point constraint h is 0.03. The dashed and solid curves in this load-deflection diagram represent unstable and stable configurations, respectively. The method used in determining the stability of the static deformation will be described in detail in Section 4.

Figure 2.

Load-deflection curves for h=0.03. The solid and dashed curves represent stable and unstable deformations, respectively.

The symmetric deformation before contact occurs is called deformation (1), whose locus starts at (FA,Δl) =(1,0) and ends at (0.99668,0.0022188). The slope of this load-deflection curve is slightly negative. After the middle point C of the elastica touches the point constraint H, the deformation pattern initially remains symmetric, called deformation (2). The load-deflection curve of deformation (2) starts at (FA,Δl)=(0.99668,0.0022188) and ends at (3.97314, 0.0026985). It is noted that the lower part of this load-deflection curve up to (2.03268, 0.0023129) is solid and the upper part is dashed. At the point separating the solid and dashed parts, a symmetry-breaking bifurcation occurs and the elastica evolves to a pair of asymmetric deformations 4(a) and 4(b). As the pushing force continues to increase, it is natural to envision that the elastica may evolve to an “M” shape, i.e., there exist two inflection points in each half of the span, called deformation (3). The load-deflection curve corresponding to deformation (3) starts at (FA,Δl)=(3.97314, 0.0026985) and continues beyond the range of Figure 2. The slope of this curve is slightly negative.

At point (FA,Δl)=(2.03268, 0.0023129), the symmetric deformation (2) described previously may bifurcate to a pair of asymmetric deformations 4(a) and 4(b). Both of (4a) and (4b) have one inflection point on each of the half span separated by the point constraint. Both (4a) and (4b) start at (FA,Δl)=(2.03268, 0.0023129), while (4a) ends at (2.03545, 0.0028996) and (4b) ends at (2.02600 0.0028996). The slopes of curves (4a) and (4b) are positive and negative throughout, respectively. Stability analysis later indicates that deformation (4b) is unstable while (4a) is stable. As Δlincreases further, the pair of deformations (4a) and (4b) evolve to a pair of asymmetric deformations (5a) and (5b). Deformation (5a) has two inflection points on the left span and one inflection point on the right span. On the other hand, deformation (5b) has two inflection points on the right span and one inflection point on the left span. The slope of load-deflection curve of (5b) is negative throughout. On the other hand, the curve of (5a) is of convex shape with the top being at point (FA,Δl) =(2.03554, 0.0031711), which is very close to the end of curve of deformation (4a). Deformation (5a) is stable first until the curve reaches the top at (FA,Δl) =(2.03554, 0.0031711). At this critical point, the elastica will jump to another configuration. The load-deflection curves near the symmetry-breaking point are magnified and shown in the inset of Figure 2.

The theoretical load-deflection curves shown in Figure 2 give us a mental picture how the elastica evolves as the pushing force FAincreases. First of all, the elastica remains still when FAis smaller than 1, the Euler buckling load. As soon as FAreaches 1, the elastica jumps to symmetric deformation (2) in contact with the point constraint. As FAincreases, a symmetry-breaking bifurcation occurs and the elastica evolves to asymmetric deformation (4a) first and smoothly to (5a). As FAcontinues to increase up to a certain value, a second jump occurs. Following this jump the elastica will eventually settle to a self-contact configuration. This self-contact configuration requires a length increment Δlover 8, which is well beyond the range of Figure 2. The above scenario has been verified experimentally in Chen and Ro (2010). In the next section we describe the vibration method used to determine the stability of the static deformations.

4. Vibration and stability analyses

4.1. Lagrangian and Eulerian descriptions

As mentioned above, the deformation patterns discussed in Section 3 may not necessarily be stable. If the deformation is unstable, then it can not be realized in practice. In order to study the vibration and stability properties of the elastica, we first derive the equations of motion of a small element ds supported by the point constraint, as shown in Figure 3.

Figure 3.

The free body diagram of a small element ds constrained by the space-fixed point.

The geometrical relations between x, y, and θare

x(s,t)s=cosθ(s,t)E5
y(s,t)s=sinθ(s,t)E6

The balance of moment and forces in the x- and y-directions results in

M(s,t)s=Fx(s,t)sinθ(s,t)Fy(s,t)cosθ(s,t)E7
Fx(s,t)sRx(t)δ(sl1η1(t))=14π22x(s,t)t2E8
Fy(s,t)sRy(t)δ(sl1η1(t))=14π22y(s,t)t2E9

Fx(s,t)and Fy(s,t)are the internal forces in the x- and y-directions. The moment-curvature relation of the Euler-Bernoulli beam model is

θ(s,t)s=4π2M(s,t)E10

The readers are reminded that the functionsx, y, θ, M, Fx, and Fyin Equations (3)-(8) are dimensionless and are all written explicitly in terms of s and t for clarity. These six equations can be called the Lagrangian version of the governing equations because a material element ds at location s is isolated as the free body. s may be called the Lagrangian coordinate of a point on the elastica. It is noted that s=0, l1, and l represent the material points at the left end, the contact point, and the right end, respectively, when the elastica is in equilibrium. During vibration, the elastica may “slide” on the point constraint. As a consequence, the contact point on the elastica may change from s=l1tos=l1+η1, where η1(t)is a small number. This change of contact point is reflected in Equations (6) and (7). Rx(t)and Ry(t)are the x- and y-component forces exerted by the point constraint on the elastica during vibration. δ()is the dimensionless Dirac delta function.

We denote the static solutions of Equations (3)-(8) asxe(s), ye(s), θe(s), Me(s), Fxe(s), andFye(s). It is assumed that these static solutions are known. In the case when contact occurs, the relations betweenFxe, FyeandFA, QAare

Fxe(s)=FA+RxeH(sl1)E11
Fye(s)=QA+RyeH(sl1)E12

H is the Heaviside step function. During vibration, the function Fy(s,t)may be regarded as the superposition of Fye(s)in Equation (10) and a small harmonic perturbation, expressed mathematically as

Fy(s,t)=Fye(s)+[Rye(H(sl1η1)H(sl1))]+E13
[Fyd(sη1)+RydH(sl1η1)]sinωtE14
(11)

A variable with subscript “d” represents a small perturbation of its static counterpart with subscript “e.”

Figure 4 is a graphical interpretation of Equation (11). The solid step lines in Figure 4(a) representFye(s). After sliding occurs the cross-hatched area disappears and the contact point moves from s=l1tos=l1+η1. This shift of the contact point from s=l1to s=l1+η1is represented by the first bracket on the right hand side of Equation (11). Figure 4(b) shows the superposition of reactive point force Rydto the right of the new contact point. This action is represented by the second term in the second bracket on the right hand side of Equation (11). Finally, Figure 4(c) shows the superposition ofF^yd. The step dashed curve in Figure 4(c) represents the final Fy(s,t)in Equation (11).

After defining a new variable εas

ε=sη1,E15

Equation (11) can be rewritten as

F^y(ε,t)=Fye(ε)+
[Fyd(ε)+RydH(εl1)]sinωtE16

whereF^y(ε,t)=Fy(ε+η1,t). Apparently, F^yand Fyare two different functions. It is noted that Fye(ε)is the static solution as obtained from the static analysis, except that the independent variable s is replaced byε. Similarly, the other perturbed functions may be written as

Figure 4.

Schematic diagram to demonstrate the perturbation ofFy(s,t), refer to Equation (11).

F^x(ε,t)=Fxe(ε)+
[Fxd(ε)+RxdH(εl1)]sinωtE17
x^(ε,t)=xe(ε)+xd(ε)sinωtE18
y^(ε,t)=ye(ε)+yd(ε)sinωtE19
θ^(ε,t)=θe(ε)+θd(ε)sinωtE20
M^(ε,t)=Me(ε)+Md(ε)sinωtE21

εdefined in Equation (12) may be called the Eulerian coordinate of a point on the elastica. ε=l1represents the point of the elastica passing through the point constraint at any instance during vibration. It can be a different material point at a different instant. The physical meaning of ε=l1is like fixing a control window at the point constraint. Therefore, we call this type of description an Eulerian one.

By noting thatεs=1, the Lagrangian version of the governing equations (3)-(8) can now be transformed into the Eulerian version as

x^(ε,t)ε=cosθ^(ε,t)E22
y^(ε,t)ε=sinθ^(ε,t)E23
M^(ε,t)ε=F^x(ε,t)sinθ^(ε,t)F^y(ε,t)cosθ^(ε,t)E24
F^x(ε,t)εRx(t)δ(εl1)=14π22x^(ε,t)t2E25
F^y(ε,t)εRy(t)δ(εl1)=14π22y^(ε,t)t2E26
θ^(ε,t)ε=4π2M^(ε,t)E27

By substituting Equations (13)-(18), together with the relations

Rx(t)=Rxe+RxdsinωtE28
Ry(t)=Rye+RydsinωtE29
η1(t)=η1dsinωtE30

into Equations (19)-(24) and ignoring the higher-order terms, we arrive at the following linear equations for the six functionsxd(ε), yd(ε), θd(ε), Md(ε), Fxd(ε), andFyd(ε):

dxd(ε)dε=θd(ε)sinθe(ε)E31
dyd(ε)dε=θd(ε)cosθe(ε)E32
dθd(ε)dε=4π2Md(ε)E33
dMd(ε)dε=[Fxe(ε)θd(ε)Fyd(ε)RydH(εl1)]cosθe(ε)E34
+[Fye(ε)θd(ε)+Fxd(ε)+RxdH(εl1)]sinθe(ε)E35
dFxd(ε)dε=14π2ω2[xd(ε)cosθe(ε)η1d]E36
dFyd(ε)dε=14π2ω2[yd(ε)sinθe(ε)η1d]E37
(33)

4.2. Boundary conditions

The exact boundary conditions at the fixed end B are

x(s,t)|s=l=x^(ε,t)|ε=lη1=1E38
y(s,t)|s=l=y^(ε,t)|ε=lη1=0E39
θ(s,t)|s=l=θ^(ε,t)|ε=lη1=0E40

These boundary conditions can be linearized as follows. Take Equation (34) as an example. By using Equation (15), we can rewrite (34) into

xe(ε)|ε=lη1+xd(ε)|ε=lη1sinωt=1E41

Both xe(ε)|ε=lη1and xd(ε)|ε=lη1in Equation (37) can be expanded as a Taylor series with respect toε=l. After ignoring the higher-order terms, Equation (37) can be linearized to

xd(ε)|ε=l=η1dE42

Similarly, the boundary conditions (35)-(36) can be linearized to

yd(ε)|ε=l=0E43
θd(ε)|ε=l=4π2Me(ε)|ε=lη1dE44

The boundary condition at the left end A is more complicated. We denote the material point on the strip right at the opening A of the channel as point A’ when the elastica is in equilibrium, as shown in Figure 5(a). Since the strip is under a constant pushing force at the left end, A’ will retreat into and protrude out of the channel when the elastica vibrates, as shown in Figures 5(b) and 5(c). We denote this small length of movement as

η0(t)=η0dsinωtE45

Figure 5.

The boundary conditions at the opening A of the feeding channel. (a) In equilibrium position, the material point A’ coincides with point A. When the elastica vibrates, the material point A’ (b) retreats in and (c) protrudes out of the channel.

The condition of zero slope at opening A requires that

θ(s,t)|s=η0=θ^(ε,t)|ε=η0η1=0E46

Following the similar linearization procedure as at point B, we can linearize boundary condition (42) to the form

θd(ε)|ε=0=4π2Me(ε)|ε=0(η0dη1d)E47

Similarly, we can derive

xd(ε)|ε=0=(η0dη1d)E48
yd(ε)|ε=0=0E49
Fxd(ε)|ε=0=0E50

Finally, Equations (43) and (44) may be combined as

θd(ε)|ε=0=4π2Me(ε)|ε=0xd(ε)|ε=0E51

The three equations (45)-(47) are the linearized boundary conditions at point A.

4.3. Constraint equations

When contact occurs, it is required that the elastica always passes through the point constraint. Mathematically, this condition can be written as

x(s,t)|s=l1+η1=x^(ε,t)|ε=l1=0.5E52
y(s,t)|s=l1+η1=y^(ε,t)|ε=l1=hE53

After using Equations (15)-(16), Equations (48)-(49) can be rewritten as

xd(ε)|ε=l1=0E54
yd(ε)|ε=l1=0E55

We also require that the dynamic reactive force must be always normal to the elastica at the point constraint, or mathematically,

Rxcosθ^(ε,t)+Rysinθ^(ε,t)=0at
ε=l1E56

After using Equations (17), (25)-(26) and neglecting higher-order terms, Equation (52) can be linearized to

[Ryeθd(ε)+Rxd]cosθe(ε)+[Rxeθd(ε)+Ryd]sinθe(ε)=0at
ε=l1E57

Equations (50), (51), and (53) are the three constraint equations.

4.4. Solution method

In summary, the six linearized differential equations (28)-(33), six boundary conditions (38)-(40), (45)-(47), and three constraint equations (50)-(51) and (53) admit nontrivial solutions only when ωis equal to an eigenvalue of the system of equations. The unknowns to be found are the six functionsxd(ε), yd(ε), θd(ε), Md(ε), Fxd(ε), Fyd(ε), the amplitude of sliding at the point constraintη1d, and the two dynamic constraint reactions RxdandRyd. It is noted that ωin Equations (32)-(33) only appears in the form ofω2. Therefore, if the characteristic value ω2is positive, the corresponding mode is stable with natural frequencyω. On the other hand, the equilibrium configuration is unstable if ω2is negative.

A shooting method is used to solve for the characteristic valueω2. Since the linear vibration mode shape is independent of the amplitude, we can setMd(ε)|ε=0=1. After guessing six variablesxd(ε)|ε=0, Fyd(ε)|ε=0, Rxd, Ryd, η1d, andω2, we can integrate the homogeneous equations (28)-(33) like an initial value problem all the way from ε=0toε=l. The three boundary conditions (38)-(40) at ε=land the three constraint equations (50)-(51) and (53) at ε=l1are used to check the accuracy of the guesses. If the guesses are not satisfactory, a new set of guesses is adopted. The stability of the deformations in Figure 2 is determined in this manner. It is noted that sometimes the term Md(ε)|ε=0of a mode shape happens to be zero. In such a case, the assumption Md(ε)|ε=0=1will yield no solution. When this situation occurs, a different variable is set as 1 in the shooting method; for instance, xd(ε)|ε=0=1.

Figure 6 shows the ω2of the first two modes as functions of the end force FAfor deformation (2). The ω2of the first mode becomes negative when FAreaches 2.03268, at which the symmetry-breaking bifurcation occurs. It is noted that the ω2of the second mode becomes negative when ω2reaches 3.97314. This happens to be the point at which deformation (3) begins to appear.

Figure 6.

Formula: Eqn192.wmf>of the first two modes as functions of the end force FA for deformation (2).

The first two mode shapes when FA=1.5 are depicted in Figure 7. The solid and dashed curves represent the static and the vibrating mode shapes of the constrained elastica, respectively. The first mode (a) is asymmetric and the second mode (b) is symmetric. To examine whether sliding at the contact point occurs we examine the values of FAand η0dof each mode. For the asymmetric mode we found that the ratio η1d/η0dis approximately 1:400. This means that during vibration the protruding and retreating of the elastica at the channel opening A is negligible compared to the sliding at the contact point. In other words, the elastica length within the domain of interest is almost constant during vibration. This can also be observed from Figure 7(a). For the symmetric mode, we found that the ratio η1d/η0dis approximately 2:1. Therefore, sliding at the contact point still occurs. From Figure 7(b) we can observe that the lengths of the elastica on both sides of the point constraint increase (or decrease during the other half of the period) the same amount. Since the elastica is inextensible, the protruding η1dat the channel opening has to be twice the amount of the sliding η0dat the contact point. It is noted that a vibration analysis of a constrained structure will cause an erroneous result if sliding at the constraint is neglected.

Figure 7.

The first two mode shapes of the constrained elastica when η1d=1.5.

It is noted that the geometric conditions (50)-(51) at the point constraint are exact. Therefore, the vibrating elastica always passes through the point constraint no matter how large the vibration amplitude is. On the other hand, the boundary conditions at points A and B used in the calculation have been linearized from the exact boundary conditions. Therefore, the mode shapes do not necessarily satisfy the exact boundary conditions at points A and B. This may become obvious when the amplitude of vibration is increased dramatically.

Figures 8(a) and 8(b) show the lowestFA, i.e., ω2, as a function of the length increment ω12for deformations (4a) and (5a), respectively. Δlof deformation (4a) is always positive. On the other hand, ω12of deformation (5a) becomes negative when ω12reaches 0.0031711. This is the point at which the load-deflection locus of deformation (5a) reaches its top in Figure 2. The mode shapes of deformations (4a) and (5a) are also depicted in the graphs. Similarly, the Δlof deformations (4b) and (5b) are plotted in Figures 9(a) and 9(b). Since ω12is always negative along the loci of deformations (4b) and (5b), we conclude that deformations (4b) and (5b) are unstable. From these stability analyses, it is concluded that after the symmetry-breaking bifurcation of deformation (2), the elastica branches to deformation 4(a) and continue to deform along locus (5a). After the ω12reaches 0.0031711, the elastica will jump to a remote self-contact configuration beyond the range of Figure 2.

Figure 8.

Formula: Eqn214.wmf>as a function of the length increment ω12 for deformations (a) (4a) and (b) (5a). The Δl of deformation (5a) becomes negative when ω12 reaches 0.0031711.

Figure 9.

Formula: Eqn218.wmf>as a function of the length increment Δl for deformations (a) (4b) and (b) (5b). The ω12 of deformations (4b) and (5b) is always negative.

5. Analysis of an imperfect system

The point constraint H in Figure 1 is at the middle between the two ends A and B. In practice, it is very difficult to place the point constraint accurately at the center. Instead, it is almost inevitable that the point constraint may be off the center somewhat. Figure 10 shows the configuration when the point constraint H (black dot) is at a distance Δlto the left of the ideal center (open circle). If the point constraint is on the right, ω12is considered to be negative.

Figure 10.

The point constraint H (black dot) is at a distance Δl to the left of the ideal center (open circle). If H is on the right, δHis considered to be negative.

In Figure 11 we describe the change of the load-deflection relation when δHis increased from 0 (ideal case) to 0.01 and 0.05. The height h remains to be 0.03. Focus is placed on how the offset affects the symmetry-breaking bifurcation when deformation (2) branches into asymmetric deformations 4(a) and 4(b) in Figure 2. It is observed that the sharp corner at the bifurcation point degenerates into two smooth curves, called deformations 6(a) and 6(b) in Figure 11. Both deformations 6(a) and 6(b) are asymmetric. The tops of deformation 6(a) and 6(b) are to the left and right, respectively, of the point constraint H. Deformation 6(b) is always unstable. Deformation 6(a) for δH=0.01, on the other hand, is stable before point (δH,δH)=(1.974, 0.00552). Figure 12 shows the δHalong the locus of deformation 6(a) when FA=0.01. It is shown that Δlbecomes negative when ω12=0.00552. For a larger δH=0.05, deformation 6(b) is stable throughout the range in Figure 11.

Inspecting Figure 11 reveals something unusual about the degeneration of the symmetry-breaking bifurcation due to the offset of the point constraint. For the ideal case with ω2=0, part of upper branch (deformations 4(a) and (5a)) is stable until it reaches a maximum. On the other hand, the lower branch (deformations 4(b) and (5b)) is always unstable. When Δlincreases from 0 to 0.01, part of the lower branch is stable until it reaches a maximum at δH=0.00552. On the other hand, the upper branch is always unstable. It is not clear how the load-deflection curves evolve as δHvaries.

Figure 11.

Load-deflection curves for h=0.03 and δH=0 (ideal case), 0.01, and 0.05, respectively. The solid and dashed curves represent stable and unstable deformations, respectively.

Figure 12.

Formula: Eqn240.wmf>Δlof the first mode as functions of δH for deformation (6) in Figure 11.

In order to answer this question, we plot the load-deflection curves when δHvaries with smaller increment. Figure 13(a) shows the load-deflection curves when ω2=0, , andΔl, respectively. For the case when δH=0, part of the upper branch is stable, while the whole lower branch is unstable, as in the inset of Figure 2. When δHincreases by a small amount, the load-deflection curves degenerates into two branches veering away from each other. When 5×105=2×104, the stable range on the upper branch shrinks. When δHcontinues to increase toδH, the stable range on the upper branch disappears altogether. For the lower branch, there exists a limit point. The locus with positive slope before the limit point is stable.

Figure 13.

Load-deflection curves for (a)5×10−5 =0, 2×10−4, andδH; (b) −5×10−5=0, −2×10−4, andδH, respectively. The solid and dashed curves represent stable and unstable deformations, respectively.

Figure 13(b) shows another scenario when δHvaries from 0 to5×105, andδH. It is observed that for a negative2×104, the sharp corner degenerates into two smooth curves crossing each other. The one emerging from the lower part has a stable range which ends at the peak of the curve. The other curve emerging from the top is unstable all the way.

6. Conclusions

In this chapter we introduce a vibration method which is suitable to analyze the stability of a constrained elastica. A planar elastica constrained by a space-fixed point constraint is used to demonstrate the method. Generally speaking, static analysis allows one to find all the possible equilibrium configurations of a constrained elastica. In order to predict how the elastica behaves in reality, the stability of these equilibrium configurations needs to be determined. The key of the vibration method is to take into account the sliding between the elastica and the unilateral constraint during vibration. In order to accomplish this, Eulerian coordinates are defined to specify the positions of the material points on the elastica. After transforming the governing equations and the boundary conditions from the Lagrangian description to the Eulerian one, the natural frequencies and the vibration mode shapes of the constrained elastica can be calculated. The vibration method is applied to an elastica constrained by a point constraint in this chapter. The same principles can be extended to other similar problems as well, for instance; multiple point constraints (Chen et al., 2010) and plane constraints (Ro et al., 2010).

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Jen-San Chen and Wei-Chia Ro (August 1st 2012). Vibration Method in Stability Analysis of Planar Constrained Elastica, Advances in Computational Stability Analysis, Safa Bozkurt Coskun, IntechOpen, DOI: 10.5772/45806. Available from:

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