please sir, help me out.

1. STAAD SPACE
INPUT FILE: new mohammodi.STD
2. START JOB INFORMATION
3. ENGINEER DATE 08-FEB-16
4. END JOB INFORMATION
5. INPUT WIDTH 79
6. UNIT METER KN
7. JOINT COORDINATES
8. 1 0 0 0; 2 19.812 0 0; 3 4.95301 0 0; 4 9.90602 0 0; 5 14.859 0 0
9. 6 0 7.62002 0; 7 19.812 7.62002 0; 8 9.90602 8.61062 0
10. 9 4.95301 8.11532 0; 10 14.859 8.11532 0; 11 0 0 6.39472
11. 12 19.812 0 6.39472; 16 0 7.62002 6.39472; 17 19.812 7.62002 6.39472
12. 18 9.90602 8.61062 6.39472; 19 4.95301 8.11532 6.39472
13. 20 14.859 8.11532 6.39472; 21 0 0 12.7894; 22 19.812 0 12.7894
14. 26 0 7.62002 12.7894; 27 19.812 7.62002 12.7894
15. 28 9.90602 8.61062 12.7894; 29 4.95301 8.11532 12.7894
16. 30 14.859 8.11532 12.7894; 31 0 0 19.1841; 32 19.812 0 19.1841
17. 36 0 7.62002 19.1841; 37 19.812 7.62002 19.1841
18. 38 9.90602 8.61062 19.1841; 39 4.95301 8.11532 19.1841
19. 40 14.859 8.11532 19.1841; 41 0 0 25.5789; 42 19.812 0 25.5789
20. 46 0 7.62002 25.5789; 47 19.812 7.62002 25.5789
21. 48 9.90602 8.61062 25.5789; 49 4.95301 8.11532 25.5789
22. 50 14.859 8.11532 25.5789; 51 0 0 31.9736; 52 19.812 0 31.9736
23. 56 0 7.62002 31.9736; 57 19.812 7.62002 31.9736
24. 58 9.90602 8.61062 31.9736; 59 4.95301 8.11532 31.9736
25. 60 14.859 8.11532 31.9736; 61 0 0 38.3683; 62 19.812 0 38.3683
26. 66 0 7.62002 38.3683; 67 19.812 7.62002 38.3683
27. 68 9.90602 8.61062 38.3683; 69 4.95301 8.11532 38.3683
28. 70 14.859 8.11532 38.3683; 71 0 0 44.763; 72 19.812 0 44.763
29. 76 0 7.62002 44.763; 77 19.812 7.62002 44.763
30. 78 9.90602 8.61062 44.763; 79 4.95301 8.11532 44.763
31. 80 14.859 8.11532 44.763; 81 0 0 51.1577; 82 19.812 0 51.1577
32. 86 0 7.62002 51.1577; 87 19.812 7.62002 51.1577
33. 88 9.90602 8.61062 51.1577; 89 4.95301 8.11532 51.1577
34. 90 14.859 8.11532 51.1577; 91 0 0 57.5524; 92 19.812 0 57.5524
35. 96 0 7.62002 57.5524; 97 19.812 7.62002 57.5524
36. 98 9.90602 8.61062 57.5524; 99 4.95301 8.11532 57.5524
37. 100 14.859 8.11532 57.5524; 101 0 0 63.9472; 102 19.812 0 63.9472
38. 106 0 7.62002 63.9472; 107 19.812 7.62002 63.9472
STAAD SPACE -- PAGE NO. 2

39. 108 9.90602 8.61062 63.9472; 109 4.95301 8.11532 63.9472
40. 110 14.859 8.11532 63.9472; 111 0 0 70.3419; 112 19.812 0 70.3419
41. 113 4.95301 0 70.3419; 114 9.90602 0 70.3419; 115 14.859 0 70.3419
42. 116 0 7.62002 70.3419; 117 19.812 7.62002 70.3419
43. 118 9.90602 8.61062 70.3419; 119 4.95301 8.11532 70.3419
44. 120 14.859 8.11532 70.3419
45. MEMBER INCIDENCES
46. 5 1 6; 6 2 7; 7 4 8; 8 6 9; 9 7 10; 10 9 8; 11 10 8; 12 3 9; 13 5 10
47. 19 6 16; 20 7 17; 21 8 18; 22 9 19; 23 10 20; 24 11 16; 25 12 17
48. 27 16 19; 28 17 20; 29 19 18; 30 20 18; 38 16 26; 39 17 27; 40 18 28
49. 41 19 29; 42 20 30; 43 21 26; 44 22 27; 46 26 29; 47 27 30; 48 29 28
50. 49 30 28; 57 26 36; 58 27 37; 59 28 38; 60 29 39; 61 30 40; 62 31 36
51. 63 32 37; 65 36 39; 66 37 40; 67 39 38; 68 40 38; 76 36 46; 77 37 47
52. 78 38 48; 79 39 49; 80 40 50; 81 41 46; 82 42 47; 84 46 49; 85 47 50
53. 86 49 48; 87 50 48; 95 46 56; 96 47 57; 97 48 58; 98 49 59; 99 50 60
54. 100 51 56; 101 52 57; 103 56 59; 104 57 60; 105 59 58; 106 60 58
55. 114 56 66; 115 57 67; 116 58 68; 117 59 69; 118 60 70; 119 61 66
56. 120 62 67; 122 66 69; 123 67 70; 124 69 68; 125 70 68; 133 66 76
57. 134 67 77; 135 68 78; 136 69 79; 137 70 80; 138 71 76; 139 72 77
58. 141 76 79; 142 77 80; 143 79 78; 144 80 78; 152 76 86; 153 77 87
59. 154 78 88; 155 79 89; 156 80 90; 157 81 86; 158 82 87; 160 86 89
60. 161 87 90; 162 89 88; 163 90 88; 171 86 96; 172 87 97; 173 88 98
61. 174 89 99; 175 90 100; 176 91 96; 177 92 97; 179 96 99; 180 97 100
62. 181 99 98; 182 100 98; 190 96 106; 191 97 107; 192 98 108; 193 99 109
63. 194 100 110; 195 101 106; 196 102 107; 198 106 109; 199 107 110
64. 200 109 108; 201 110 108; 209 106 116; 210 107 117; 211 108 118
65. 212 109 119; 213 110 120; 214 111 116; 215 112 117; 216 114 118
66. 217 116 119; 218 117 120; 219 119 118; 220 120 118; 221 113 119
67. 222 115 120
68. UNIT FEET KIP
69. DEFINE MATERIAL START
70. ISOTROPIC STEEL
71. E 4.176E+006
72. POISSON 0.3
73. DENSITY 0.489024
74. ALPHA 6E-006
75. DAMP 0.03
76. TYPE STEEL
77. STRENGTH FY 5184 FU 8352 RY 1.5 RT 1.2
78. END DEFINE MATERIAL
79. MEMBER PROPERTY AMERICAN
80. 19 TO 23 38 TO 42 57 TO 61 76 TO 80 95 TO 99 114 TO 118 133 TO 137 -
81. 152 TO 156 171 TO 175 190 TO 194 209 TO 213 TABLE ST HSST2X1X0.125
82. UNIT METER KN
83. MEMBER PROPERTY
84. 5 6 214 215 TAPERED 0.5 0.004 0.5 0.175 0.006 0.175 0.006
85. 24 25 43 44 62 63 81 82 100 101 119 120 138 139 157 158 176 177 195 -
86. 196 TAPERED 0.7 0.008 0.7 0.25 0.01 0.25 0.01
87. 8 TO 11 217 TO 220 TAPERED 0.5 0.004 0.5 0.2 0.006 0.2 0.006
88. 27 28 46 47 65 66 84 85 103 104 122 123 141 142 160 161 179 180 198 -
89. 199 TAPERED 0.7 0.01 0.7 0.25 0.012 0.25 0.012
90. 29 30 48 49 67 68 86 87 105 106 124 125 143 144 162 163 181 182 200 -
91. 201 TAPERED 0.7 0.008 0.6 0.2 0.01 0.2 0.01
92. 7 12 13 216 221 222 TAPERED 0.35 0.004 0.5 0.125 0.06 0.125 0.06
93. UNIT FEET KIP
94. CONSTANTS
STAAD SPACE -- PAGE NO. 3

95. BETA 90 MEMB 7 12 13 216 221 222
96. SUPPORTS
97. 1 TO 5 11 12 21 22 31 32 41 42 51 52 61 62 71 72 81 82 91 92 101 102 -
98. 111 TO 115 FIXED
99. MEMBER RELEASE
100. 19 TO 23 38 TO 42 57 TO 61 76 TO 80 95 TO 99 114 TO 118 133 TO 137 -
101. 152 TO 156 171 TO 175 190 TO 194 209 TO 213 START MX MY MZ
102. 19 TO 23 38 TO 42 57 TO 61 76 TO 80 95 TO 99 114 TO 118 133 TO 137 -
103. 152 TO 156 171 TO 175 190 TO 194 209 TO 213 END MX MY MZ
104. UNIT METER KN
105. LOAD 1 LOADTYPE DEAD TITLE DL
106. SELFWEIGHT Y -1 LIST ALL

*** STAAD.Pro ERROR MESSAGE ***
DENSITY NOT PROVIDED. SELFWEIGHT COMMAND IGNORED

107. MEMBER LOAD


*********** END OF THE STAAD.Pro RUN ***********

**** DATE= FEB 8,2016 TIME= 16: 5:45 ****

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Sir,

I am working on aluminium Mullion Profile I need to know how to get the Bending stress value from Staad Pro?

And I need to know the Permissible Bending stress of Aluminium?

Help me

I want to know if staad pro.  can check for fatigue for crane girders and if he can how can I do this check

I am designing an octagonal tapered tubular pole which requires the use of the ASCE solver. Staad gives a utilization ratio/unity check result but it does not change when the yield strength of the material is changed - for example I get the same result using steel with yield strengths of 36ksi and 50ksi. I'd expect the results to differ when using a higher yield strength steel. Also no load case is specified in the results as the critical case. The output file lists only a ratio and a "pass" or "fail" for the prismatic members. What is the ratio calculation based on when using this solver?

Thanks for any insight.

I have large axial force on beam with a regular bolted support clip angle connection, it failed on prying action, and when I switch to both sided welled clip angle connection, there is no checking on prying action and bending on clip angle.  Can you tell me why?

For a flat roof that lays in the XZ plane:  I would normally assign one of the nodes in the center of the roof  as the master and slave all of the other roof nodes in the XZ direction.

Would this methodology still be applicable for a pitched gable roof (slope = 5 degrees)?  It does not seem correct to only assign one master node and slave all of the other roof nodes when the roof is not flat.  It also does not seem correct to use the XZ slave direction because the roof is sloped so it is technically not in the global XZ plane. 

How can I properly model the roof diaphragm for a pitched gable roof?  Should I have two master nodes, one for each side of the gable roof?  Would I still use the XZ slave direction?

Any insight that can be offered would be greatly appreciated!! 

Dear RAM team,

From the linear analysis we get a predicted crack width (for the relevant load combination) based on the code formulation. And one of the things RAM does is to reinforce according to the code to keep that crack width.

When we run the Load History processor it develops a material nonlinear analysis where it iteratively cracks the slab until convergence is reached. Do we have access to the information about that real cracks against those predicted in the linear analysis?

-------------

Another question. We want to assess the crack width generated by shrinkage and temperature change. Is there a way to obtain it with RAM similar to CIRIA C660 guidelines?

Thanks, you are the best.

Just FYI, when you run a design on a structure that uses open-web steel joists in RAM Elements 13.4.0.164, you may get a status message like the screenshot below indicating that Elements has designed the joists to a different design method than what was selected. In my case, the structure was designed for AISC ASD 2010, and it said the joists were being design for 2005 LRFD. This appears to be only a reporting typo. The allowable loads in the steel joist report matched the SJI ASD load tables, not the higher LRFD tables, in my case anyway. Thanks.

I have an existing roof truss with double angles.  Most of the double angles are SLBB.  The truss is modeled in the X-Y plane and all of the double angles have the local 3-3 axis perpendicular to the truss.  The top and bottom chords are modeled as continuous members. All of my loads are gravity loads -Y.

Why does the Ram Analysis and Design reports show values other than zero for M22 and show zero for M33 moments?  Isn't this backward?  There should be no out-of-plane moments.

Will STAAD.Pro optimize composite steel beams?  I was initially designing my floor as non-composite and using STAAD.Pro to optimize the steel member sizes.  Now, I need to check what the steel member sizes would be if I had a composite deck.  I've never tried to optimize composite steel beams in STAAD.pro before so I am unsure.

Thanks for any insight you can offer, it is greatly appreciated!!!

Is it possible to model a cap plate connection with more than 4 bolts?  I have a condition where a w-shape beam continues and cantilevers an HSS column.  The connection is failing on prying action.  Or, is it possible to introduce full depth stiffeners to help with the prying?

Thanks!

I have a 6-story braced frame building with offset floors.  When analyzed, a few frame shears decrease in force from 3rd floor to 2nd floor which causes a negative change in frame shear.  What causes the decrease in force to happen?  Do other frames attract more load due to stiffness?  Is the decrease in force a result of higher modes?

If this shear reversal is acceptable, how is the diaphragm analyzed?  Is there a large spike in shear at the reversal location?

Please see the attached PDF for clarification.

(Please visit the site to view this file)

Hi there. I have only just started to use RAM structural system. I have built a model in RAM Modeler. When running the data check I get a number of warnings and errors. Some appear to be able to be resolved simply, while others I am not sure how to go about. A snapshot is shown below. I have also attached the file 'Pala model 2_'. 

After numerous failed attempts, I would appreciate any tips, or detailed procedures to fix the warnings and errors. 

Regards

Tasleem

Hello!

I am using Ram SS for the analysis and design of the building and am fairly new to the software. The issue i have here is i am getting higher drifts  than expected for the structure.  i have modeled the slab as a semi rigid diaphragm and for this particular building wind forces do govern the lateral analysis. The wind loads are user defined loads and when viewing the applied forces on the plan  for the wind case i realized the wind load is higher along the edge. I have not applied any eccentricity for this case as i wanted to see the uniform distribution of the forces to nodal point of semi rigid diaphragm  on the windward edge. 

Load case is with force in X direction, WF 100% LF 0%, Ey=0. Please see the screenshot below of the applied load. This is the program calculated windward edge . Can we manually define the windward edge?

Any suggestions would be helpful.

Thanks,
Adi

(Please visit the site to view this file)Hi,

I am looking at a simple frame model and puzzled about the effective length and elastic critical moment from the design output.

A column is split into several sections but the effective length is defined using the LY and LZ commands. In the output file, I can see that the defined effective length is used for slenderness ratio and compression capacity. But in the section of "Buckling calculation", the effective length changes back to the distance between the start and end nodes (analytical beam length). I also find that the calculated elastic critical moment for LTB increases when the analytical beam length is reduced. This seems not logical to me.

Can anyone help on this matter? The command file is attached as a text file.

Cheers,

XGU

Good morning Bentley Community,

I am working on this model for spring hangers. when I run the program it tells me I didn't add density for some members. I went back, added density, and still tells me density has not been added and self weight will no be taken into consideration. I am wondering what I am doing wrong here. you can probably help with this issue. see code attached

STAAD SPACE
START JOB INFORMATION
ENGINEER DATE 09-Feb-16
JOB NAME XXX Spring Support
JOB CLIENT XXX
JOB NO 137051.01
JOB REV 0
ENGINEER NAME EGC
CHECKER NAME CLL
END JOB INFORMATION
INPUT WIDTH 79
UNIT FEET KIP
JOINT COORDINATES
       1 0 0 0
       2 0 8.5 0
       3 0 8.5 -0.208
       4 0 8.5 0.208
       5 10 0 0
       6 10 8.5 0
       7 10 8.5 -0.208
       8 10 8.5 0.208
       9 20 0 0
      10 20 8.5 0
      11 20 8.5 -0.208
      12 20 8.5 0.208
      13 5 8.5 -0.208
      14 5 8.5 0.208
      15 15 8.5 -0.208
      16 15 8.5 0.208
      17 5 8.5 0
      18 15 8.5 0
MEMBER INCIDENCES
       1         1         2
       2         3         2
       3         2         4
       4         5         6
       5         7         6
       6         6         8
       7         9        10
       8        11        10
       9        10        12
      10         3        13
      11         4        14
      12         7        15
      13         8        16
      14        13         7
      15        14         8
      16        15        11
      17        16        12
      18        13        17
      19        17        14
      20        15        18
      21        18        16
DEFINE MATERIAL START
ISOTROPIC STEEL
E 4.176e+006
POISSON 0.3
DENSITY 0.489024
ALPHA 6e-006
DAMP 0.03
END DEFINE MATERIAL
MEMBER PROPERTY AMERICAN
1 4 7 TABLE ST W8X31
2 3 5 6 8 TO 17 TABLE ST C10X15
CONSTANTS
BETA 180 MEMB 10 12 14 16
SUPPORTS
1 5 9 PINNED
MEMBER OFFSET
16 17 END 0.333 0 0
1 4 7 END 0 -0.4167 0
10 11 START -0.333 0 0
***LOAD CASES***
LOAD 1 LOADTYPE Dead  TITLE SELFWEIGHT
SELFWEIGHT Y -1
LOAD 2 LOADTYPE Dead  TITLE WEST SUPPORT
JOINT LOAD
17 FY -10.407
LOAD 3 LOADTYPE Dead  TITLE EAST SUPPORT
JOINT LOAD
18 FY -11.848
LOAD 4 LOADTYPE Wind  TITLE WIND LOAD X - DIRECTION
JOINT LOAD
2 6 10 FX 0.2
LOAD 5 LOADTYPE Wind  TITLE WIND LOAD Z - DIRECTION
JOINT LOAD
2 6 10 FZ 0.2
LOAD 6 LOADTYPE Ice  TITLE ICE LOAD
MEMBER LOAD
1 TO 21 UNI GY -0.05
***LRFD LOAD COMBINATIONS***
LOAD COMB 10 1.4D
1 1.4 2 1.4 3 1.4
LOAD COMB 11 1.2D+0.5S
1 1.2 2 1.2 3 1.2 6 0.5
LOAD COMB 12 1.2D+1.6S+0.5WX
1 1.2 2 1.2 3 1.2 6 1.6 4 0.5
LOAD COMB 13 1.2D+1.6S+0.5WZ
1 1.2 2 1.2 3 1.2 6 1.6 5 0.5
PERFORM ANALYSIS PRINT ALL
PRINT ANALYSIS RESULTS
PARAMETER 1
CODE AISC UNIFIED 2010
PERFORM ANALYSIS PRINT ALL
FINISH

Thanks

Ernesto Costa

Hello everyone,

I am a new user for STAAD. I am doing a p-delta analysis to a tent structure, whose structural components include steel tubing frame and steel tension cables. I used REPEAT LOAD for the load combinations. Previously, the result of load combinations have abrupt change in the steel design code from analysis of a single primary load with identical loads. The results are not converging with the increase of # of iterations.

Then I learned that I have to reset the stiffness matrix by using "CHANGE" command after running p-delta analysis to each of the load combinations. Now the steel design result is the same as that by analysis of a single identical primary load. However, the result of steel design code only have record of the very last load cases, that is the 33rd one. The program was able to obtain other result such as displacement, reaction forces and beam forces for all of the load cases. 

I am wondering if there is method to retrieve the steel design ratio compliance result after each run of the load case. Otherwise I have to separate the analysis into a total of 33 load cases. I am posting my load analysis code here:

LOAD 8 LOADTYPE None TITLE LOAD COMBINATION 1
REPEAT LOAD
1 1.25 2 1.5 6 0.4

PDELTA 1 ANALYSIS PRINT ALL
PARAMETER 2
CODE CANADIAN
TRACK 2 MEMB ALL
PARAMETER 3
CODE CANADIAN
FYLD 355 ALL
CHECK CODE AL

CHANGE

LOAD 9 LOADTYPE None TITLE LOAD COMBINATION 2
REPEAT LOAD
1 1.25 2 1.5 7 0.4

PDELTA 1 ANALYSIS PRINT ALL
PARAMETER 2
CODE CANADIAN
TRACK 2 MEMB ALL
PARAMETER 3
CODE CANADIAN
FYLD 355 ALL
CHECK CODE AL

CHANGE

.....

.....

LOAD 33 LOADTYPE None TITLE LOAD COMBINATION 10
REPEAT LOAD
1 1.25 2 1.5 
PDELTA 1 ANALYSIS PRINT ALL
PARAMETER 2
CODE CANADIAN
TRACK 2 MEMB ALL
PARAMETER 3
CODE CANADIAN
FYLD 355 ALL
CHECK CODE ALL
FINISH

Thanks a lot!

Hi,

In STAAD, buckling analysis is not working for us. For that query we were suggested to buy advance license tool for STAAD. After we bought the advance license tool also it is not working for us. In the pre processor we used to input the command perform buckling analysis, no of iterations and buckling shapes post print. After analysing, in the post-processing page we are not getting that buckling page tab (Refer below). Tell some remedies how to fix this problem. Step by step procedure with screen shot or pdf files for doing buckling analysis in STAAD will be helpful for us. Awaiting for your reply.

Sir,

i'm having doubts in I-value which is taken from AutoCAD horizontal Members. I did the analysis using Principal Moments Value taken from AutoCAD Region.

I used Space Frame in Analysis, it is Intermediate section in windows.

So I need to confirm whether my analysis is correct or I need to change the value from that. If any changes please let me know. And another I couldn't able to find the values for stress in that Analysis,(Please visit the site to view this file)it shows zero for all values . (Please visit the site to view this file)(Please visit the site to view this file)

Help me 

Thanks in advance 

Dear All

I am using SS-5 version of STAAD Pro V8i. When I am trying to update the member property of any member using section database through GUI, it is not replicated in the in put editor file even when i saved the file. At the same time, it is showing in GUI. When i try to run analysis, error report comes saying member is not provided with property. This is happening when i am selecting a new property from section database through GUI. I have attached the file. Can you pls check and help?

Regards

Murali(Please visit the site to view this file)