DNV Plate Buckling (1995)

DNV Plate Buckling (1995) verifies the structural stability for each structural member (plate) according to the Plate Buckling DNV released July, 1995.

DNV CN30 1995

To add DNV CN30/1995 standard execute Standard - DNV Plate Buckling (1995) from main menu. Alternatively use Standard context menu:

DNV 95_add

Stress Safety Factor - critical buckling stresses are divided on safety factor.

Thickness Factor - increases each plate thickness (e.g. 1.1 increase on 10%) and decreases stresses;

Calculations are performed for each element with converted stresses (into plate direction) or Plate Average Stresses and using Plate dimensions.

Stress on Element - what stress to check.

Average - average stress among element point of interests.

Min Midplane - minimum midplane stress (Stop + Sbottom / 2), without bending.

Use Absolute Shear for Plate Average - used only together with plate average option and means that absolute shear is used for plate averaging:

With Absolute Shear option, higher shear stress is used for checking, that makes verification more conservative.

Formulas of Plate Buckling DNV CN30/1995 standard use Yield Stress from materials. It is important to set this value for each material. Standard check if all Yield Stress is not equal to zero:

If count > 0 then press to edit Yield Stress:

Plate Buckling Check is calculated on Sections. With help of Panel Finder tool it is possible to automatically recognize Section and Plates with their dimensions.

Calculations is performed for each element with converted stresses into plate direction and using Plate dimensions. Then results in the table are presented for Plate (worst Buckling State Limit.

By default, All Sections included into selection but can be changed by pressing . If sections were not recognized press to run Panel Finder tool.

Check is passed if Ultimate Strength Limit ≤1 and Buckling State Limit ≤1.

Calculation approach

For individual loads and loads sets, plate buckling is calculated basing on the formulas using stresses from the load. For Load Group, plate buckling is calculated as an envelope. Load Group items are calculated using formulas and then min/max/abs is found. Load Group contains the worst values for each parameter and gives a possibility to check the highest Ultimate Strength and Buckling State Limits for all items at once.

Ultimate Strength Limit and Buckling State Limit depend on the plate results (stresses) and the plate dimensions (length, width and thickness).

Plate buckling check includes various options for stresses to be checked:

Note:for x and y direction only compression (negative) stresses is used in the calculations. Positive stress is ignored and set 0. For shear (xy) direction positive and negative stresses are used.

Stress Conversion. Plate buckling check requires to verify stresses into the plate direction (direction of longest plate edge). Element Sx stress will be translated into plate length direction, element Sy into the width direction.

Conversion of stresses is done automatically in plate buckling check. For average option the first stresses are averaged and afterwards translated. For MinMidplane option midplane stresses are translated and then minimum values are taken.

Dimensions. Results depend on the plate dimensions and direction. It is important to understand how Panel Finder performs the recognition. Length is considered to be the longest edge of the plate and width is the longest perpendicular to the longest edge:

Plate Thickness. Calculations are performed on every element and thickness is taken directly from each element. It is possible to set the thickness manually, in this case, the element thickness will be ignored and user-defined thickness will be used.

Example: Plate with 2 properties 0.01 and 0.02 thicknesses. The left picture displays property labels with property thicknesses and the right presents plate buckling plot of thickness parameter:

Formulas

The characteristic buckling resistance for serviceability check may be taken as:

= reduced slenderness.

= characteristic material resistance.

= reduced slenderness.

= for shear stress.

= elastic buckling resistance.

= yield stress.

= equivalent reduced slenderness.

= equivalent stress according to Von Mises.

= elastic buckling resistance.

= normal compressive stress ( in the table "The buckling coefficient C" below); normal tensile stress may be set equal to zero.

= shear stress.

The buckling coefficient C
Non-uniform compression
Pure bending C=24
Pure shear
Non-uniform compression
Non-uniform compression

The usage factor for plate elements checked according to the serviceability criterion may be taken:

The maximum allowable value of the usage factor, , is defined in the DNV standard rules.

The plate buckling analysis described above may, in addition to being a serviceability check, be used to obtain sound plate dimensions relative to the stiffener dimensions.

If, however, plate buckling does not represent a serviceability problem (excessive deformation and/or fatigue loading) the ultimate capacity of the plate may be determined like in formulas below.

The characteristic buckling resistance for ultimate check of plate panels between stiffeners may be taken as:

The usage factor for plate elements between stiffeners, calculated with respect to the ultimate capacity may be determined as:

where is the equivalent stress according to von Mises, as defined above.

The elastic buckling resistance of plate panels with aspect ration not less than one, is given by:

C = buckling coefficient depending on:

For more detailed information, C may be taken from the table "The buckling coefficient C" above. It is assumed that all edges are simply supported.