STAAD.Pro Help

V. EC3 Belgian NA - Column with Axial Load

Calculate the axial and bending capacities and interaction ratios of a column using the Belgian NA to EC3.

Details

The 5 m tall column as a fixed base and is free to translate and rotate at the top. The column is subject to a 25 kN compressive load and moments of 5 kN·m about the X axis and 10 kN·m about the Z axis. The section is an HD320X127, grade S275 steel.

Validation

Bending Capacity

Moment capacity:

M c k d = W p l y f y γ M 0 = 2,149 ( 10 ) 3 275 1.0 ( 10 ) 6 = 591.0  kN·m

The critical moment is given by:

M c r = C 1 π 2 E I ( k L ) 2 { ( k k w ) 2 I w I + ( k L ) 2 G I t π 2 E I + ( C 2 Z g ) 2 C 2 Z g }
where
C1
=
2.578
C2
=
1.554
π 2 E I y k L 2
=
7,477,200
k k w 2 I w I y
=
22,394
k L 2 G I t π 2 E I y
=
5,934
C2Zg
=
1.554×160 = 248.6

Therefore, Mcr = 1,540.6 kN·m

From the Belgian NA, λLT, 0 = 0.4, β = 0.75

So, λ L T = w y f y M c r = 2,149 × 10 3 × 275 1,540.6 × 10 6 = 0.619

H/b = 320/300 = 1.067 < 2. So, from Table 6.5 of Eurocode 3, αLT = 0.34.

From Cl. 6.3.2.3 of Eurocode3:

ФLT = 0.5[1+αLTLT- λLT, 0) + β× λLT2] = 0.5[1 + 0.34×(0.619 - 0.4) +0.75 × 0.6192] = 0.681

So, χ L T = Ф L T + Ф L T 2 - β λ L T 2 - 1 = 0.908

M B = χ L T w y f y γ M 1 = 0.908 × 2,149 ( 10 ) 3 × 275 1.0 = 536.8  kN·m

Compression Capacity

Critical compressive values:

N cry = π 2 E I y ( k l ) 2 = 7,477  kN
N crz = π 2 E I z ( k l ) 2 = 29,943  kN
λ cy = A × f y N cry = 0.770
λ cz = A × f y N crz = 0.422

Determine χy

h/b = 1.067 < 1.2 and tf = 20.5 mm < 100 mm

So, for y-y axis, use curve "c". Hence, α = 0.49 [Table 6.2, EC3]

So, ф = 0.5[1+α (λ - 0.2) +λ2)] = 0.936

χ y = 1 ф + ф 2 - λ 2 0.681 (governs)

Determine χz

h/b = 1.067 < 1.2 and tf = 20.5 mm < 100 mm

So, for z-z axis, use curve "b". Hence, α = 0.34 [Table 6.2, EC3]

So, ф = 0.5[1+α (λ - 0.2) +λ2)] = 0.627

χ z = 1 ф + ф 2 - λ 2 0.917 (does not govern)

Compression capacity:

χy×NRk = 0.681×7,477 = 3,020.2 kN

Compression ratio: 25 kN / 3,020.2 kN = 0.008

Critical Axial Loads for Flexure and Flexural Torsional Buckling

From NCCI document SN001a-EN-FU:

N c r , T = 1 i 0 2 G I t + π 2 E I w l T 2
where
i o 2
=
i y 2 + i z 2 + y o 2 + z o 2 ; here y0 = z0 = 0

iy = 75.68 mm and iz = 138.23 mm

= 24,835 mm2

N c r , T = 1 24,835 20,500 × 225.1 ( 10 ) 4 2.6 + π 2 205,000 2.069 ( 10 ) 12 5,000 2 = 13,889  kN
N c r , T F = i 0 2 2 ( i y 2 + i z 2 ) N c r , y + N c r , T - N c r , y + N c r , T 2 - 4 N c r , y N c r , T i y 2 + i z 2 i 0 2
= 1 2 24,943 + 13,889 - 24,943 + 13,889 2 - 4 ( 24,943 ) ( 13,889 ) 1 1 = 13,889  kN

Interaction Check

From Annex A, Table A.1 of EC3, the auxiliary terms:

μ z = 1 - N E d N c r z 1 - χ z * N E d N c r z = 0.9999
μ y = 1 - N E d N c r y 1 - χ y * N E d N c r y = 0.9989

χLT = 0.908294

Wz = wplz/welz = 2149/1926 = 1.1158

Wy = wply/wely = 939/615.933 = 1.525 > 1.5, so, wy = 1.5

ψ=1.0

c m z , 0 = 0.79 + 0.21 × 1 + 0.36 1 - 0.33 25 24,942 = 1.0002

Also, c m z , 0 > 1 - N E d N c r , z , OK

c m y , 0 = 0.79 + 0.21 × 1 + 0.36 1 - 0.33 25 7,477 = 1.0008

Also, c my,0 > 1 - N E d N c r , y , OK

Determination of λ0

C1 = 1, C2 = 0

Mcr = 1,606 kN

λ 0 = 2,149 × 10 3 × 275 1,606 × 10 6 = 0.6066
λ 0 , l i m i t = 0.2 C 1 1 - N E d N c r y * 1 - N E d N c r T F 4 = 0.321

λ0 > λ0,limit

aLT = 1 - It/Iz = 0.993

ε z = M Z , E d N E d × A W e l z = 3.350
C m z = C m z , 0 + 1 - C m z , 0 Ɛ Z * a L T 1 + Ɛ Z * a L T = 1.000
C m y = C m y , 0 = 1.001
C m L T = C m z 2 × a L T 1 - N E d N c r y × 1 - N E d N c r T = 0.995 < 1

So, CmLT = 1.0

λmax = the maximum of λy and λz, therefore λmax = λy = 0.7702

b L T = 0.5 a L T λ 0 2 M y E d χ L T × M p l y . R d × M z E d M p l z . R d = 0.5 × 0.993 × 0.6066 2 5 × 10 0.908 × 258.3 × 591 0
η p l = N E d N R k G M 1 = 25 4,436 / 1.0 = 0.0056
C z z = 1 = w z + 1 2 - 1.6 w Z C m z 2 λ m a x - 1.6 w Z C m z 2 λ m a x 2 η p l - b L T = 1 + 1.1158 - 1 2 - 1.6 1.1158 1 2 × 0.7702 - 1.6 1.1158 1 2 × 0.7702 2 0.00564 - 0 1.0

Welz/Wplz = 0.8962 < CZZ. So, CZZ = 1.0

C L T = 10 a L T λ 0 2 5 + λ y 4 × M z , E d C m z × χ L T × M p l z , R d = 0.0127
C z y = 1 + ( w y - 1 ) 2 - 14 C m y 2 × λ m a x 2 w y 5 η p l - C L T = 0.9962

Check C x y > 0.6 W y W z × W e l y W p l y = 0.456 , OK

d L T = 2 a L T λ 0 0.1 + λ y 4 × M z , E d C m z × χ L T × M p l z , R d × M y , E d C m y * M p l y , R d = 2 × 0.9927 0.6066 0.1 + 0.7702 2 × 10 1 × 0.9083 × 591 × 5 1.0008 × 258.3 = 0.00096
C y z = 1 + ( w z - 1 ) 2 - 14 C m z 2 × λ m a x 2 w z 5 η p l - d L T = 0.9981
e L T = 1.7 a L T λ 0 0.1 + λ y 4 × M z , E d C m z × χ L T × M p l z , . R d = 0.0422
C y y = 1 + w y - 1 2 - 1.6 w y C m y 2 × λ m a x - 1.6 w y × C m y 2 × λ m a x 2 η p l - e L T = 1 + 1.5 - 1 2 - 1.6 1.5 1.001 2 × 0.7702 - 1.6 1.5 1.001 2 × 0.7702 2 0.00564 - 0.0422 = 0.9804

Wely/Wply = 0.656 < CZZ. So, CZZ = 0.9804

Interaction factors:

K z z = C m z C m L T μ z 1 - N E d N c r z × 1 C z z = 1.001
K z y = C m y μ z 1 - N E d N c r y × 1 C z y 0.6 W y W z = 0.7012
K y z = C m z C m L T μ y 1 - N E d N c r z × 1 C y z 0.6 W z W y = 0.5185
K y y = C m y μ y 1 - N E d N c r y × 1 C y y = 1.023

Check for Clause 6.3.3-661:

N E d χ Z N R k γ M 1 + K Z Z M z , E d χ L T M z , R k γ M 1 + K z y M y , E d M y , R k γ M 1 = 25 0.9174 × 4,436 + 1.001 10 0.9083 × 591 + 0.7012 5 258.3 = 0.038
N E d χ y N R k γ M 1 + K y z M z , E d χ L T * M z , R k γ M 1 + K y y M y , E d M y , R k γ M 1 = 25 0.6809 × 4,436 + 0.51845 10 0.9083 × 591 + 1.0231 5 258.3 = 0.038

Results

Table 1.
Result Type Reference STAAD.Pro Difference Comments
Moment capacity, Mckd (kN·m) 591.0 591.0 none  
Critical moment, Mcr (kN·m) 1,540.5 1,541.5 negligible  
Bending capacity, MB (kN·m) 536.8 536.8 none  
Critical load for torsional buckling, Ncr,T (kN) 13,889 13,898.0 negligible  
Critical load for torsional-flexural buckling, Ncr,TF 13,889 13,898.0 negligible  
Compression interaction, Cl. 6.3.1.1 0.008 0.008 none  
Bending and compression interaction, Cl 6.3.3-661 0.038 0.038 none  
Bending and compression interaction, Cl. 6.3.3-662 0.038 0.037 negligible  

STAAD.Pro Input

The file C:\Users\Public\Public Documents\STAAD.Pro CONNECT Edition\Samples\ Verification Models\09 Steel Design\Europe\EC3 National Annex\Belgian NA\EC3 Belgian NA - Column with Axial Load.std is typically installed with the program.

The following design parameters are used:

  • The Belgian NA is specified using NA 8
  • Fixed support: CMM 2.0
  • Fixed base and free at other end: CMN 0.7
  • The value of C2 1.554 is specified
STAAD SPACE
START JOB INFORMATION
ENGINEER DATE 19-Apr-20
END JOB INFORMATION
INPUT WIDTH 79
UNIT METER KN
JOINT COORDINATES
1 0 0 0; 2 0 5 0;
MEMBER INCIDENCES
1 1 2;
MEMBER PROPERTY EUROPEAN
1 TABLE ST HD320X127
DEFINE MATERIAL START
ISOTROPIC STEEL
E 2.05e+08
POISSON 0.3
DENSITY 76.8195
ALPHA 1.2e-05
DAMP 0.03
END DEFINE MATERIAL
CONSTANTS
MATERIAL STEEL ALL
SUPPORTS
1 FIXED
LOAD 1 LOADTYPE None  TITLE LOAD CASE 1
JOINT LOAD
2 FY -25 MX 5 MZ 10
PERFORM ANALYSIS
PARAMETER 1
CODE EN 1993-1-1:2005
NA 8
CMM 2 ALL
C2 1.554 ALL
FU 295000 ALL
PY 275000 ALL
CMN 0.7 ALL
TRACK 2 ALL
CHECK CODE ALL
FINISH

STAAD.Pro Output

                         STAAD.PRO CODE CHECKING - NBN EN 1993-1-1:2005
                         ********************************************
                         NATIONAL ANNEX - NBN EN 1993-1-1 ANB : 2018
 PROGRAM CODE REVISION V1.13 BS_EC3_2005/1
      STAAD SPACE                                              -- PAGE NO.    3
 ALL UNITS ARE - KN   METE (UNLESS OTHERWISE Noted)
 MEMBER     TABLE       RESULT/   CRITICAL COND/     RATIO/     LOADING/
                          FX            MY             MZ       LOCATION
 =======================================================================
       1 ST   HD320X127   (EUROPEAN SECTIONS)
                           PASS     EC-6.3.3-661       0.038         1                                                        
                       25.00 C          5.00         -10.00        0.00
 =======================================================================
   MATERIAL DATA                
      Grade of steel           =  USER          
      Modulus of elasticity    =  205 kN/mm2  
      Design Strength  (py)    =  275  N/mm2                         
   SECTION PROPERTIES (units - cm)
      Member Length =    500.00
      Gross Area =  161.30          Net Area =  161.30
                                      z-axis          y-axis
      Moment of inertia        :    30820.004        9239.001
      Plastic modulus          :     2149.000         939.100
      Elastic modulus          :     1926.250         615.933
      Shear Area               :       81.998          51.728
      Radius of gyration       :       13.823           7.568
      Effective Length         :      500.000         500.000
   DESIGN DATA (units - kN,m)   EUROCODE NO.3 /2005
      Section Class            :   CLASS 1     
      Squash Load              :   4435.75
      Axial force/Squash load  :     0.006
      GM0 :  1.00          GM1 :  1.00          GM2 :  1.25
                                      z-axis          y-axis
      Slenderness ratio (KL/r) :         36.2           66.1
      Compression Capacity     :       4078.2         3045.5
      Tension Capacity         :       3426.0         3426.0
      Moment Capacity          :        591.0          258.3
      Reduced Moment Capacity  :        591.0          258.3
      Shear Capacity           :       1301.9          821.3
   BUCKLING CALCULATIONS (units - kN,m)
      Lateral Torsional Buckling Moment       MB =  536.8
      co-efficients C1 & K : C1 =2.578 K =1.0, Effective Length= 5.000
      Lateral Torsional Buckling Curve : Curve b 
      Elastic Critical Moment for LTB,               Mcr   =  1541.5
      Compression buckling curves:     z-z:  Curve b   y-y:  Curve c
      Critical Load For Torsional Buckling,          NcrT  = 13898.0
      Critical Load For Torsional-Flexural Buckling, NcrTF = 13898.0
      STAAD SPACE                                              -- PAGE NO.    4
 ALL UNITS ARE - KN   METE (UNLESS OTHERWISE Noted)
 MEMBER     TABLE       RESULT/   CRITICAL COND/     RATIO/     LOADING/
                          FX            MY             MZ       LOCATION
 =======================================================================
   CRITICAL LOADS FOR EACH CLAUSE CHECK (units- kN,m):
    CLAUSE        RATIO  LOAD     FX       VY      VZ      MZ      MY   
   EC-6.3.1.1     0.008     1    25.0      0.0     0.0   -10.0     5.0
   EC-6.2.9.1     0.020     1    25.0      0.0     0.0   -10.0     5.0
   EC-6.3.3-661   0.038     1    25.0      0.0     0.0   -10.0     5.0
   EC-6.3.3-662   0.037     1    25.0      0.0     0.0   -10.0     5.0
   EC-6.3.2 LTB   0.019     1    25.0      0.0     0.0   -10.0     5.0
    Torsion and deflections have not been considered in the design.
                        _________________________