Linear Buckling Analysis

The problem of linear buckling in finite element analysis is solved by first applying a reference level of loading, f r e f , to the structure.

A linear static analysis is then carried out to obtain stresses which are needed to form the geometric stiffness matrix K σ , corresponding to f r e f . The buckling loads are then calculated by solving an eigenvalue problem:

( Kλ K σ )A=0

Where, K is the stiffness matrix of the structure and λ is the multiplier to the reference load. The solution of the eigenvalue problem generally yields n eigenvalues λ , where n is the number of degrees-of-freedom (in practice, only a subset of eigenvalues is usually calculated). The vector A is the eigenvector corresponding to the eigenvalue.

The eigenvalue problem is solved using a matrix method called the Lanczos method. Not all eigenvalues are required. Only a small number of the lowest eigenvalues are normally calculated for buckling analysis.

The lowest eigenvalue λ α is associated with buckling. The critical or buckling load is:

f α = λ α f r e f

If f r e f is applied to a preloaded structure and STATSUB(PRELOAD) of the referential linear static loadcase points to a nonlinear static analysis, the stiffness matrix K in the buckling eigenvalue problem is the prestressed stiffness matrix used in the referential linear static loadcase. Accordingly, the buckling load f σ is interpreted as a load on the preloaded structure instead of the unloaded structure.


To run a linear buckling analysis, an EIGRL Bulk Data Entry needs to be given because it defines the number of modes to be extracted. The EIGRL card needs to be referenced by a METHOD statement in a SUBCASE in the Subcase Information section. In addition, it is necessary to use a STATSUB card to reference the appropriate referential static loading, f r e f SUBCASE. STATSUB cannot refer to a subcase that uses Inertia Relief.

Buckling analysis will ignore , CELAS1, CELAS2, CMASS1, CMASS2, CONM1, CONM2, CBUSH, CVISC, CDAMP1, CDAMP2, CGAP, CGAPG, PLOTEL, CWELD, CSEAM, CFAST, JOINTG, MPC, and RBE3 elements. These elements can be used in buckling analysis, but they do not contribute to the geometric stiffness matrix, K σ . By default, the contribution from the rigid elements to the geometric stiffness matrix is not included. You have to add PARAM,KGRGD,YES to the Bulk Data Entry section to include the contribution of rigid elements to the geometric stiffness matrix.

The geometric stiffness matrix K σ MathType@MTEF@5@5@+= feaahqart1ev3aqatCvAUfeBSjuyZL2yd9gzLbvyNv2CaerbuLwBLn hiov2DGi1BTfMBaeXatLxBI9gBaebbnrfifHhDYfgasaacH8srps0l bbf9q8WrFfeuY=Hhbbf9v8qqaqFr0xc9pk0xbba9q8WqFfea0=yr0R Yxir=Jbba9q8aq0=yq=He9q8qqQ8frFve9Fve9Ff0dmeaabaqaciGa caGaaeqabaqaaeaadaaakeaacaWHlbWaaSbaaSqaaiabeo8aZbqaba aaaa@347B@ calculation for linear buckling considers the temperature-dependent material updated via TEMP(LOAD) or TEMP(MAT).

In addition, through the EXCLUDE Subcase Information Entry, you may decide to omit the contribution of other elements to the geometric stiffness matrix, effectively allowing you to control which parts of the structure are analyzed for buckling. The excluded properties are only removed from the geometric stiffness matrix, resulting in a buckling analysis with elastic boundary conditions. This means that the excluded properties may still be showing movement in the buckling mode.

Buckling analysis with a referential static loading subcase using inertia relief is not supported by default. In such cases, the stiffness matrix is positive semi-definite and the buckling eigenvalue solution ends in singularity. PARAM,INRELBCK,1 or PARAM,INRELBCK,2 can be used to attempt Buckling Analysis based on inertia relief.

Linear Buckling and Offset Elements

Some one-dimensional and shell elements can use offset to "shift" the element stiffness relative to the location determined by element's nodes. For example, shell elements can be offset from the plane defined by element nodes by means of ZOFFS. In this case all other information, such as material matrices or fiber locations for the calculation of stresses, are given relative to the offset reference plane. Similarly, shell results, such as shell element forces, are output on the offset reference plane.

Offset is applied to all element matrices (stiffness, mass, and geometric stiffness), and to respective element loads (such as gravity). Hence, in principle offset can be used in all types of analysis and optimization, including linear buckling. However, caution is advised when interpreting the results. Without offset, a typical simple structure will bifurcate and loose stability "instantly" at the critical load. With offset, though, the loss of stability is gradual and asymptotically reaches a limit load, as shown below in Figure 1(b):
Figure 1.

In practice then, the structure with offset can reach excessive deformation before the limit load is reached.
Note: More complex structures, such as frames or structures experiencing bending moments, buckle via limit load, even in absence of ZOFFS on the element card.

Furthermore, in a fully nonlinear approach, additional instability points may be present on the limit load path.