V. EC3 Belgian NA - Tee Section
Calculate the bending capacity of a beam using an Tee section subject to a uniformly distributed load and varying end moments per the Belgian NA to EC3.
Details
The section is an Indian INST100 with fy = 300 MPa. The member is a 5 m, simply-supported span under a 2 kN/m uniform load. The left support has a -5.0 kN·m moment applied and the right support has a 2.5 kN·m moment applied.
Validation
Moment capacity:
The critical moment is given by:
Therefore,
Results
Result Type | Reference | STAAD.Pro | Difference | Comments |
---|---|---|---|---|
Moment capacity, Mckd (kN·m) | 13.7 | 13.7 | none | |
Critical moment, Mcr (kN·m) | 21.5 | 21.5 | none |
STAAD.Pro Input
The file C:\Users\Public\Public Documents\STAAD.Pro 2024\Samples \Verification Models\09 Steel Design\Europe\EC3 Belgian NA - Tee Section.std is typically installed with the program.
The following design parameters are used:
- The Belgian NA is specified using
NA 8
- Simply-supported span:
CMN 1.0
- Varying end moments and a uniformly distributed load:
CMM 7
- The values of
C1 1.0
,C2 1.0
, andC3 1.0
are specifiedNote: Since these parameters are specified,MU
is not specified as it would be ignored in favor of the direct coefficient specifications. Refer to D5.B.10.2 Clause 6.3.2.2 –Elastic critical moment andimperfection factors for LTB checks for additional details.
STAAD PLANE
START JOB INFORMATION
ENGINEER DATE 20-Apr-20
END JOB INFORMATION
INPUT WIDTH 79
UNIT METER KN
JOINT COORDINATES
1 0 0 0; 2 5 0 0;
MEMBER INCIDENCES
1 1 2;
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
MEMBER PROPERTY INDIAN
1 TABLE ST ISNT100
*1 TABLE ST ISNT150
CONSTANTS
MATERIAL STEEL ALL
SUPPORTS
1 2 PINNED
LOAD 1 LOADTYPE None TITLE LOAD CASE 1
JOINT LOAD
2 MZ 2.5
1 MZ -5
MEMBER LOAD
1 UNI GY -2
PERFORM ANALYSIS
PRINT MEMBER PROPERTIES ALL
PARAMETER 1
CODE EN 1993-1-1:2005
NA 8
CMM 7 ALL
C1 1 ALL
C2 1 ALL
C3 1 ALL
CMN 1 ALL
PY 300000 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 V1.14 BS_EC3_2005/1
STAAD PLANE -- PAGE NO. 4
ALL UNITS ARE - KN METE (UNLESS OTHERWISE Noted)
MEMBER TABLE RESULT/ CRITICAL COND/ RATIO/ LOADING/
FX MY MZ LOCATION
=======================================================================
* 1 ST ISNT100 (INDIAN SECTIONS)
FAIL EC-6.3.2 LTB 1.263 1
0.00 0.00 -10.03 2.08
=======================================================================
MATERIAL DATA
Grade of steel = USER
Modulus of elasticity = 205 kN/mm2
Design Strength (py) = 300 N/mm2
SECTION PROPERTIES (units - cm)
Member Length = 500.00
Gross Area = 19.20 Net Area = 19.20
z-axis y-axis
Moment of inertia : 180.000 79.600
Plastic modulus : 45.500 26.600
Elastic modulus : 25.210 15.920
Shear Area : 13.333 10.900
Radius of gyration : 3.062 2.036
Effective Length : 500.000 500.000
DESIGN DATA (units - kN,m) EUROCODE NO.3 /2005
Section Class : CLASS 1
Squash Load : 576.00
Axial force/Squash load : 0.000
GM0 : 1.00 GM1 : 1.00 GM2 : 1.25
z-axis y-axis
Slenderness ratio (KL/r) : 163.3 245.6
Compression Capacity : 116.5 55.1
Tension Capacity : 497.7 497.7
Moment Capacity : 13.7 8.0
Reduced Moment Capacity : 13.7 8.0
Shear Capacity : 230.9 188.8
BUCKLING CALCULATIONS (units - kN,m)
Lateral Torsional Buckling Moment MB = 7.9
co-efficients C1 & K : C1 =1.000 K =1.0, Effective Length= 5.000
Lateral Torsional Buckling Curve : Curve d
Elastic Critical Moment for LTB, Mcr = 21.5
Compression buckling curves: z-z: Curve c y-y: Curve c
Critical Load For Torsional Buckling, NcrT = 4275.7
Critical Load For Torsional-Flexural Buckling, NcrTF = 64.4
STAAD PLANE -- PAGE NO. 5
CRITICAL LOADS FOR EACH CLAUSE CHECK (units- kN,m):
CLAUSE RATIO LOAD FX VY VZ MZ MY
EC-6.2.5 0.735 1 0.0 0.3 0.0 -10.0 0.0
EC-6.2.6-(Y) 0.029 1 0.0 5.5 0.0 2.5 0.0
EC-6.3.2 LTB 1.263 1 0.0 0.3 0.0 -10.0 0.0
Torsion has not been considered in the design.
_________________________
************** END OF TABULATED RESULT OF DESIGN **************