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2018-09-12

Stiffened Buckling Panels According to EN 1993-1-5, Section 4.5

In SHAPE-THIN, the calculation of stiffened buckling panels can be performed according to Section 4.5 of EN 1993-1-5. For stiffened buckling panels, the effective surfaces due to local buckling of the single panels in the plate and in the stiffeners, as well as the effective surfaces from the entire panel buckling of the stiffened entire panel, have to be considered.

First of all, the effective surfaces of the single panels are determined using the reduction factor according to EN 1993-1-5 [1], Section 4.4 to take into account the buckling of single panels. In the second step, the buckling safety of the entire panel is determined while taking into account buckling behavior similar to one of the buckling members. With the reduction factor of the entire panel buckling, the effective widths of the single panels are reduced again. This results in an effective cross-section that can be handled as belonging to cross-section class 3.

Example

The following example is taken from the Steel Structures Yearbook 2015 [2]. The cross-section consists of an I-beam of which the web is stiffened by rigid transverse stiffeners and a longitudinal stiffener. The transverse stiffeners are arranged at a distance of 3,000 mm to one another and the longitudinal stiffener is welded at a distance of 500 mm from the bottom flange. The welds are neglected. A compression axial force of N_Ed = 4,000 kN acts.

Cross-Section

Material:
S355 J0
f_y = 35.5 kN/cm² (for t ≤ 3 mm and t ≤ 16 mm)
f_y = 34.5 kN/cm² (for t >16 mm and t ≤ 40 mm)
E = 21,000 kN/cm²
G = 8,076.92 kN/cm²
γ_M0 = 1.0

a = 3,000 mm
b₁ = 500 mm
b₂ = 2,500 mm
b_f = 800 mm
b_st = 250 mm
t_w = 15 mm
t_f = 40 mm
t_st = 25 mm
h = 3,080 mm

Gross Cross-Section and Stress Distribution

The stress is calculated as follows:

σ_{1} = σ_{sl} = σ_{2} = \frac{N_{Ed}}{A} = \frac{4, 000}{1, 152.5} = 3.47 kN / cm ²

Formula 1

The gross cross-section and the stress distribution are shown in Figure 02.

Stress Distribution

Cross-Section Classification

During a cross-section classification, an evaluation is performed to ascertain if a buckling design is necessary for the single panels. If the single panel is at least cross-section class 3, local buckling does not govern.

Flange

\begin{array}{l} c_{f} = \frac{b_{f} - t_{w}}{2} = \frac{800 - 15}{2} = 392.5 mm \\ \frac{c_{f}}{t_{f}} = \frac{392.5}{40} = 9.8 \end{array}

Formula 2

The maximum c/t ratio λ_i is determined according to EN 1993-1-1 [3], Table 5.2.

\begin{array}{l} ε = \sqrt{235 / f_{y}} = \sqrt{235 / 345} = 0.825 \\ λ_{1} = 9 \cdot ε = 9 \cdot 0.825 = 7.4 < \frac{c_{f}}{t_{f}} = 9.8 \\ λ_{2} = 10 \cdot ε = 10 \cdot 0.825 = 8.2 < \frac{c_{f}}{t_{f}} = 9.8 \\ λ_{3} = 14 \cdot ε = 14 \cdot 0.825 = 11.6 > \frac{c_{f}}{t_{f}} = 9.8 \end{array}

Formula 3

The flange has to be assigned to cross-section class 3. Local buckling thus does not govern and no reduction of the single panels of the flange is necessary.

Web

\begin{array}{l} c_{1} = b_{1} - \frac{t_{st}}{2} = 500 - \frac{25}{2} = 487.5 mm \\ \frac{c_{1}}{t_{w}} = \frac{487.5}{15} = 32.5 \end{array}

Formula 4

The maximum c/t ratio λ_i is determined according to [3], Table 5.2.

\begin{array}{l} ε = \sqrt{235 / f_{y}} = \sqrt{235 / 355} = 0.814 \\ λ_{1} = 33 \cdot ε = 33 \cdot 0.814 = 26.8 < \frac{c_{1}}{t_{w}} = 32.5 \\ λ_{2} = 38 \cdot ε = 38 \cdot 0.814 = 30.9 < \frac{c_{1}}{t_{w}} = 32.5 \\ λ_{3} = 42 \cdot ε = 42 \cdot 0.814 = 34.2 > \frac{c_{1}}{t_{w}} = 32.5 \end{array}

Formula 5

The single panel 1 has to be assigned to cross-section class 3. Local buckling thus does not govern and no reduction of the single panels of the flange is necessary.

\begin{array}{l} c_{2} = b_{2} - \frac{t_{st}}{2} = 2, 500 - \frac{25}{2} = 2, 487.5 mm \\ \frac{c_{2}}{t_{w}} = \frac{2, 487.5}{15} = 165.8 \end{array}

Formula 6

The maximum c/t ratio λ_i is determined according to [3], Table 5.2.

\begin{array}{l} ε = \sqrt{235 / f_{y}} = \sqrt{235 / 355} = 0.814 \\ λ_{1} = 33 \cdot ε = 33 \cdot 0.814 = 26.8 < \frac{c_{2}}{t_{w}} = 165.8 \\ λ_{2} = 38 \cdot ε = 38 \cdot 0.814 = 30.9 < \frac{c_{2}}{t_{w}} = 165.8 \\ λ_{3} = 42 \cdot ε = 42 \cdot 0.814 = 34.2 < \frac{c_{2}}{t_{w}} = 165.8 \end{array}

Formula 7

The single panel 2 has to be assigned to cross-section class 4. Local buckling thus governs for this single panel and a reduction of this single panel is necessary.

Stiffener

\begin{array}{l} b_{st} = 250 mm \\ \frac{b_{st}}{t_{st}} = \frac{250}{25} = 10 \end{array}

Formula 8

The maximum c/t ratio λ_i is determined according to [3], Table 5.2.

\begin{array}{l} ε = \sqrt{235 / f_{y}} = \sqrt{235 / 345} = 0.825 \\ λ_{1} = 9 \cdot ε = 9 \cdot 0.825 = 7.4 < \frac{b_{st}}{t_{st}} = 10 \\ λ_{2} = 10 \cdot ε = 10 \cdot 0.825 = 8.2 < \frac{b_{st}}{t_{st}} = 10 \\ λ_{3} = 14 \cdot ε = 14 \cdot 0.825 = 11.6 > \frac{b_{st}}{t_{st}} = 10 \end{array}

Formula 9

The web has to be assigned to cross-section class 3. Local buckling thus does not govern and no reduction of this single panel is necessary.

Effective Widths

The single panel 1 is assigned to cross-section class 3 so that local buckling does not govern. The effective cross-section values correspond to the gross cross-section values. According to [1], Table 4.1, this results in the following effective widths:

\begin{array}{l} b_{1, eff} = c_{1} = 487.5 mm \\ b_{1, edge, eff} = b_{1, edge} = 0.5 \cdot c_{1} = 0.5 \cdot 487.5 = 243.8 mm \\ b_{1, \inf, eff} = b_{1, \inf} = 0.5 \cdot c_{1} = 0.5 \cdot 487.5 = 243.8 mm \end{array}

Formula 10

The single panel 2 is assigned to cross-section class 4 so that local buckling does not govern. The effective widths of the single panel 2 have to be determined according to [1], Section 4.4.

The stress distribution in the single panel 2 is uniform. This results in a stress ratio of ψ = 1 and, according to Table 4.1, in a buckling value of k_σ= 4.0. According to [1], Section 4.4(2), the result for the slenderness ratio λ_p2 is:

${\bar{λ}}_{p 2} = \frac{\frac{c_{2}}{t_{w}}}{28.4 \cdot ε \cdot \sqrt{k_{σ}}} = \frac{165.8}{28.4 \cdot 0.814 \cdot \sqrt{4}} = 3.588$ Formula 12	$> 0.5 \sqrt{0.085 - 0.055 \cdot ψ}$ Formula 13
	$> 0.5 \sqrt{0.085 - 0.055 \cdot 1} = 0.673$ Formula 14

The local reduction factor ρ is determined according to [1], Equation (4.2):

ρ_{2} = \frac{{\bar{λ}}_{p 2} - 0.055 \cdot (3 ψ)}{{\bar{λ}}_{p 2}^{2}} = \frac{3.588 - 0.055 \cdot (3 1)}{3 . 588^{2}} = 0.262 < 1

Formula 15

The effective widths of the single panel 2, taking into account the local buckling, are calculated according to [1], Table 4.1:

\begin{array}{l} b_{2, eff} = ρ_{2} \cdot c_{2} = 0.262 \cdot 2, 487.5 = 650.7 mm \\ b_{2, edge, eff} = 0.5 \cdot b_{2, eff} = 0.5 \cdot 650.7 = 325.4 mm \\ b_{2, \sup, eff} = 0.5 \cdot b_{2, eff} = 0.5 \cdot 650.7 = 325.4 mm \end{array}

Formula 16

The widths of the gross cross-section result in:

\begin{array}{l} b_{2, edge} = 0.5 \cdot c_{2} = 0.5 \cdot 2, 487.5 = 1, 243.8 mm \\ b_{2, \sup} = 0.5 \cdot c_{2} = 0.5 \cdot 2, 487.5 = 1, 243.8 mm \end{array}

Formula 17

Slab-Like Behavior

The elastic critical buckling stress of the stiffness σcr,sl is calculated according to [1], Annex A.2.2. The effective length of the stiffness a_c has to be calculated first:

a_{c} = 4.33 \cdot \sqrt[4]{\frac{I_{sl, 1} \cdot b_{1}^{2} \cdot b_{2}^{2}}{t^{3} \cdot b}} = 4.33 \cdot \sqrt[4]{\frac{11, 900 \cdot 50^{2} \cdot 250^{2}}{1 . 5^{3} \cdot (50 250)}} = 896.4 cm > a = 300 cm

Formula 18

The elastic critical buckling stress of the stiffness σ_cr,sl results in a < a_c in:

\begin{array}{l} σ_{cr, sl} = \frac{π^{2} \cdot E \cdot I_{sl, 1}}{A_{sl, 1} \cdot a^{2}} + \frac{E \cdot t^{3} \cdot b \cdot a^{2}}{4 \cdot π^{2} \cdot (1 - ν^{2}) \cdot A_{sl, 1} \cdot b_{1}^{2} \cdot b_{2}^{2}} für a < a_{c} \\ σ_{cr, sl} = \frac{π^{2} \cdot 21.000 \cdot 11.900}{289, 4 \cdot 300^{2}} + \frac{21.000 \cdot 1, 5^{3} \cdot (50 250) \cdot 300^{2}}{4 \cdot π^{2} \cdot (1 - 0, 3^{2}) \cdot 289, 4 \cdot 50^{2} \cdot 250^{2}} = 95, 9 kN / {cm}^{2} \end{array}

Formula 19

I_sl,1 and A_sl,1 represent here the second moment of area of the gross cross-section and the gross cross-section area of the equivalent compression member according to [1]; A.2.1(2) for buckling perpendicular to the plate plane as well as b₁ and b₂ describe the distances of the stiffeners to the longitudinal edges (b₁ + b₂ = b).

The stress distribution is uniform. Therefore, the elastic plate buckling stress σ_cr,p corresponds to the critical buckling stress σ_cr,sl.

σ_{cr, p} = σ_{cr, sl} = 95.9 kN / {cm}^{2}

Formula 20

Gross Cross-Section Equivalent Compression Member

The gross cross-section area A_c of the longitudinally stiffened plate panel is calculated as follows, without taking into account the edge plates supported by an adjacent plate component and the effective cross-section area A_c,eff,loc,p of the area described above:

A_{c} = (b_{1, \inf} + b_{2, \sup} + t_{st}) \cdot t_{w} + b_{st} \cdot t_{st} = (24, 38 + 124, 38 + 2, 5) \cdot 1, 5 + 25 \cdot 2, 5 = 289, 4 {cm}^{2}

Formula 21

The stiffness belongs to cross-section class 3, so the effective cross-section area of the stiffness corresponds to the gross cross-section area of the stiffness.

A_{c, eff, loc, p} = (b_{1, \inf, eff} + b_{2, \sup, eff} + t_{st}) \cdot t_{w} + b_{st, eff} \cdot t_{st} = (24, 38 + 32, 54 + 2, 5) \cdot 1, 5 + 25 \cdot 2, 5 = 151, 6 {cm}^{2}

Formula 22

The cross-section values are shown in Figure 04.

Gross and Effective Cross-Section Due to Local Buckling

The reduction factor β_a,c,p is calculated according to [1], Section 4.5.2 as follows:

\begin{array}{l} β_{a, c, p} = \frac{A_{c, eff, loc, p}}{A_{c}} \\ β_{a, c, p} = \frac{151.6}{289.4} = 0.524 \end{array}

Formula 23

The global slenderness λ_p of the stiffened plate according to [1], Equation (4.7), results in:

${\bar{λ}}_{p} = \sqrt{\frac{β_{a, c, p} \cdot f_{y}}{σ_{cr, p}}} = \sqrt{\frac{0.524 \cdot 35.5}{95.9}} = 0.440$ Formula 25	$< 0.5 \sqrt{0.085 - 0.055 \cdot ψ}$ Formula 26
	$< 0.5 \sqrt{0.085 - 0.055 \cdot 1} = 0.673$ Formula 27

According to [1], 4.4(2), the slenderness ratio λ_p is smaller than the limit value 0.673. Therefore, no reduction due to slab behavior is necessary; for example, ρ_p = 1.0.

Plate Buckling Behavior

The elastic critical buckling stress σ_cr,c is determined according to [1], Section 4.5.3(3). First of all, the buckling stress σ_cr,c,sl of the stiffener, which is positioned at the maximum loaded compression edge, is determined according to [1], Equation (4.9).

σ_{cr, c, sl} = \frac{π^{2} \cdot E \cdot I_{sl}}{A_{sl} \cdot a^{2}} = \frac{π^{2} \cdot 21, 000 \cdot 11, 900}{289.4 \cdot 300^{2}} = 94.7 kN / {cm}^{2}

Formula 28

The stress distribution is uniform. Therefore, the elastic critical buckling stress σ_cr,c corresponds to the elastic buckling stress σ_cr,c,sl of the stiffener, which is positioned at the maximum loaded compression edge.

σ_cr,c = σ_cr,c,sl = 94.7 kN/cm²

The reduction factor β_a,c,c is calculated according to [1], Section 4.5.3(4) as follows:

β_{a, c, c} = \frac{A_{sl, eff}}{A_{sl}} = \frac{151.6}{289.4} = 0.524

Formula 29

The slenderness ratio λcof the equivalent compression member according to [1], Equation (4.11), results in:

{\bar{λ}}_{c} = \sqrt{\frac{β_{a, c, c} \cdot f_{y}}{σ_{cr, c}}} = \sqrt{\frac{0.524 \cdot 35.5}{94.7}} = 0.443

Formula 31

According to [1], Section 4.5.3(5), the radius of gyration i is calculated as follows:

i = \sqrt{\frac{I_{sl}}{A_{sl}}} = \sqrt{\frac{11, 900}{289.4}} = 6.41 cm

Formula 32

The distance e is the greater of the two distances according to [1], Figure A.1; for example, either the distance e₁ of the single stiffener, adjusted between the center of gravity and considered independently of the plate, without the effective width to the centroidal axis of the stiffened plate panel, or the distance e₂ of the centroidal axis of the stiffened plate panel to the middle plane of the plate. The distances are shown in Figure 05.

Equivalent Compression Member and Stiffener: Distances e1, e2

e = max (e₁, e₂) = max (10.39 cm, 2.86 cm) = 10.39 cm

The imperfection factor αe is determined, according to [1], Equation (4.12) with α = 0.49, for open stiffener cross-sections as follows:

α_{e} = α \frac{0.09}{i / e} = 0.49 \frac{0.09}{6.41 / 10.39} = 0.636

Formula 33

The reduction factor χ_c is determined according to [3], 6.3.1.2:

\begin{array}{l} ϕ = 0.5 \cdot (1.0 α_{e} \cdot ({\bar{λ}}_{c} - 0.2) {\bar{λ}}_{c}^{2}) = 0.5 \cdot (1.0 0.636 \cdot (0.443 - 0.2) 0 . 443^{2}) = 0.675 \\ χ_{c} = \frac{1}{ϕ \sqrt{ϕ^{2} - {\bar{λ}}_{c}^{2}}} = \frac{1}{0.675 \sqrt{0 . 675^{2} - 0 . 443^{2}}} = 0.844 < 1 \end{array}

Formula 34

Interaction Between Plate Buckling and Slab Behavior

The structural behavior of the entire panel is determined with the factor ξ, according to [1], Section 4.5.4(1):

\begin{array}{l} ξ = \frac{σ_{cr, p}}{σ_{cr, c}} - 1 but 0 \leq ξ \leq 1 \\ ξ = \frac{95.9}{94.7} - 1 = 0.013 \end{array}

Formula 35

The final reduction factor ρc is determined with the interaction equation according to [1], Equation (4.13):

ρ_{c} = (ρ_{p} - χ_{c}) \cdot ξ \cdot (2 - ξ) + χ_{c} = (1 - 0, 844) \cdot 0, 013 \cdot (2 - 0, 013) + 0, 844 = 0, 848

Formula 36

Effective Cross-Section Values

The effective surface of the compression zone A_c,eff of the stiffened plate panel is calculated according to [1], Equation (4.5):

A_{c, eff} = ρ_{c} \cdot A_{c, eff, loc, p} + \sum b_{edge, eff} \cdot t = 0, 848 \cdot 151, 6 24, 38 \cdot 1, 5 + 32, 54 \cdot 1, 5 = 214, 1 cm ²

Formula 37

The effective cross-section area A_eff results in:

A_{eff} = A_{c, eff} + 2 \cdot b_{f} \cdot t_{f} = 214, 1 + 2 \cdot 80 \cdot 4 = 854, 1 cm ²

Formula 38

Effective Cross-Section Due to Local and Global Buckling

Design of the Stiffened Panel

The centroidal axes of the gross cross-section and of the effective cross-section do not coincide, so additional acting bending moments due to the displacement of the centroidal axis of the effective cross-section related to the centroidal axis of the gross cross-section have to be considered here. These additional bending moments are calculated as follows:

\begin{array}{l} e_{y} = 0.82 - 0.72 = 0.10 cm \\ e_{z} = 164.97 - 157.42 = 7.55 cm \\ M_{y} = N \cdot e_{z} = 4, 000 \cdot 7.55 = 30, 202.4 kNcm \\ M_{z} = N \cdot e_{y} = - 4, 000 \cdot 0.10 = - 414.3 kNcm \\ M_{u} = 30, 203.7 KNcm \\ M_{v} = - 306.4 KNcm \end{array}

Formula 39

The maximum stress results in:

σ_{eff} = \frac{N}{A_{eff}} + \frac{M_{u} \cdot e_{v}}{I_{u, eff}} - \frac{M_{v} \cdot e_{u}}{I_{v, eff}} = \frac{4.000}{854, 1} + \frac{30.203, 7 \cdot 165, 12}{17.466.764} - \frac{- 306, 4 \cdot 40, 23}{352.626} = 5, 01 kN / cm ²

Formula 40

The design is performed according to [1], Equation (4.15) as follows:

η_{1} = \frac{σ_{eff}}{\frac{f_{y}}{γ_{M 0}}} = \frac{5.01}{\frac{34.5}{1.0}} = 0.15

Formula 41

Torsional Buckling Design

According to [1], Section 9.2.1(8) the following criterion has to be fulfilled in general to avoid torsional buckling of stiffeners with open cross-sections:

\begin{array}{l} η_{1} = \frac{5.3 \cdot f_{y} \cdot I_{p}}{E \cdot I_{S t . V e n}} \leq 1 \\ η_{1} = \frac{5.3 \cdot 34.5 \cdot 13, 053}{21, 000 \cdot 122} = 0.93 \leq 1 \end{array}

Formula 42

I_p and I_St.Ven describe the polar moment of inertia and the St. Venant moment of inertia of the stiffness cross-section alone (without plate), calculated around the connection point to the plate.

If the warping stiffness is considered, the critical torsional buckling stress σ_cr has to be determined first. It is calculated according to [4], Equation (2.119) and Equation (2.120) as follows:

\begin{array}{l} σ_{cr 1} = \frac{1}{I_{p}} \cdot (\frac{π^{2} \cdot E \cdot I_{ω}}{l^{2}} + G \cdot I_{St . Ven}) für l < L_{cr} \\ σ_{cr 2} = \frac{1}{I_{p}} \cdot (2 \cdot \sqrt{C_{θ} \cdot E \cdot I_{ω}} + G \cdot I_{St . Ven}) für l > L_{cr} \end{array}

Formula 43

The stiffness has a warping constant of I_ω = 0 cm⁶. The critical torsional buckling stress σ_cr is thus simplified to:

\begin{array}{l} σ_{cr 1} = σ_{cr 2} = \frac{1}{I_{p}} \cdot G \cdot I_{S t . V e n} \\ σ_{cr 1} = σ_{cr 2} = \frac{1}{13, 053} \cdot 8, 077 \cdot 122 = 75.5 kN / cm ² \end{array}

Formula 44

I_p and I_St.Ven describe the polar moment of inertia and the St. Venant moment of inertia of the stiffness cross-section alone (without plate), calculated around the connection point to the plate.

According to [1], Section 9.2.1(9), the criterion in 9.2.1(8) or the following criterion has to be generally considered, when taking into account the warping stiffness:

\begin{array}{l} η_{2} = \frac{θ \cdot f_{y}}{σ_{cr 1}} \leq 1 \\ η_{3} = \frac{θ \cdot f_{y}}{σ_{cr 2}} \leq 1 \end{array}

Formula 45

With a factor to ensure the elastic behavior according to cross-section class 3 according to [5] of θ = 2 f for stiffeners with low warping stiffness (for example, flat bar or bulb flat steel), the result is:

η_{2} = η_{3} = \frac{2 \cdot 34.5}{75.5} = 0.91 \leq 1

Formula 46

The torsional buckling design is thus fulfilled.

SHAPE-THIN

In SHAPE-THIN, the calculation of stiffened buckling panels can be performed according to [1], Section 4.5. The control panel "c/t parts and effective cross-section properties" has to be activated in the general data. Afterwards, "EN 1993-1-1 and EN 1993-1-5" has to be selected in the calculation parameters; the control panel titled "Effective cross-section according to EN 1993-1-5, Section 4.5" has to be selected as well. The determination of the effective widths should be carried out in an iterative process according to [1], Section 4.4(3). In this example, only one iteration has to be used for the calculation so that only one iteration will also appear in SHAPE-THIN (see Figure 07).

Calculation Parameters

The elements of the cross-section have to be entered first. The c/t parts are generally generated automatically from the geometric conditions; however, they can be created as user-defined in Table "1.7 Cross-Section Parts for the Classification According to EN 1993-1" (see Figure 08) or the corresponding dialog box.

Cross-Section Parts for Classification

The stiffeners can then be defined in Table "1.8 Stiffeners" or in the corresponding dialog box (see Figure 09).

Stiffeners

Moreover, the stiffened panel has to be specified in Table "1.9 Stiffened Panels" (see Figure 10) or the corresponding dialog box. The elements of the stiffened panel have to be selected and the transverse stiffener distance a has to be entered. If no transverse stiffener distance is defined, the value a = 10,000 mm will be applied for the calculation. The stiffeners located in the stiffened panel are identified automatically. The stiffened panel has to be supported at its start and end, which means that a support is needed here.

Buckling Panels

The results of the effective cross-section can be viewed with the [Effective Widths" button.

Results

Author

Ms. von Bloh provides technical support for our customers and is responsible for the development of the SHAPE‑THIN program as well as steel and aluminum structures.

Links

Structural Analysis Software for Steel Structures

References

EC 3. (2009). Eurocode 3: Design of Steel Structures – Part 1-5: Plattenförmige Bauteile. Beuth Verlag GmbH, Berlin, 2010.
Beg, D.; Kuhlmann, U.; Davaine, L.; Braun, B.: Design of Plated Structures. Eurocode 3: Design of Steel Structures. Part 1-5 Design of Plated Structures. Berlin: Ernst & Sohn, 2011
Kuhlmann, U.: Stahlbau-Kalender 2015 - Eurocode 3 - Grundnorm, Leichtbau. Berlin: Ernst & Sohn, 2015
Johansson, B.; Maquoi, R.; Sedlacek, G.; Müller, C.; Beg, D.: Commentary and Worked Examples to EN 1993-1-5, Plated Structural Elements. Luxemburg: Office for Official Publications of the European Communities, 2007
EC 3. (2009). Eurocode 3: Bemessung und Konstruktion von Stahlbauten − Teil 1-1: General rules and rules for buildings. (2010). Berlin: Beuth Verlag GmbH

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In the "Edit Section" dialog box, you can display the buckling shapes of the Finite Strip Method (FSM) as a 3D graphic.

Steel Design | Seismic Force-Resisting System Design Overview

Design of five types of seismic force-resisting systems (SFRS) includes Special Moment Frame (SMF), Intermediate Moment Frame (IMF), Ordinary Moment Frame (OMF), Ordinary Concentrically Braced Frame (OCBF), and Special Concentrically Braced Frame (SCBF)
Ductility check of the width-to thickness ratios for webs and flanges
Calculation of the required strength and stiffness for stability bracing of beams
Calculation of the maximum spacing for stability bracing of beams
Calculation of the required strength at hinge locations for stability bracing of beams
Calculation of the column required strength with the option to neglect all bending moments, shear, and torsion for overstrength limit state
Design check of column and brace slenderness ratios

Seismic in Steel Design Add-on | Results

The seismic design result is categorized into two sections: member requirements and connection requirements.

The "Seismic Requirements" include the Required Flexural Strength and the Required Shear Strength of the beam-to-column connection for moment frames. They are listed in the ‘Moment Frame Connection by Member’ tab. For braced frames, the Required Connection Tensile Strength and the Required Connection Compressive Strength of the brace are listed in the ‘Brace Connection by Member’ tab.

The program provides the performed design checks in tables. The design check details clearly display the formulas and references to the standard.

Feature 002733 | AISC 341-16 Seismic Design for Steel Members

In the Concrete Design provides an option to perform seismic design according to AISC 341-16 for steel members.

Five SFRS types (Seismic Force-Resisting Systems) are available for this.

Frequently Asked Questions (FAQ)

What is the difference between SHAPE‑THIN 9 and SHAPE‑THIN 8?

Is it possible to model cold-formed sections in SHAPE‑THIN 8 and design them in RF‑/STEEL Cold-Formed Sections?

After a few days of operation, the activated softlock license, student license, or trial version cannot be run due to a license problem. On some computers, the message "Virtual machine detected" appears.

Why?

During the calculation, I get a warning that some elements are connected to the buckling panel, but are not defined like stiffeners (see Image 01). What should I do?

I have received an error message saying that my license is already activated. What can I do?

How do I define a plastic hinge in RFEM 6?

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