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1

1. Read this First

STAAD/Pro is a suite of inter-related structural software, offeringa complete solution for the professional structural engineer.STAAD/Pro consists of a Core package and several optionalExtension components. You may procure one or more Extensioncomponents along with the STAAD/Pro Core package.

Part-I of this manual describes the following:

• Hardware Requirements• Contents of the STAAD/Pro CD• Installation of STAAD/Pro modules• Copy Protection Device• Running STAAD/Pro

Part II of this manual provides two Tutorials for STAAD/Pro. TheTutorials guide you through the processes of :

• Creating a structural model from scratch, along withLoads, Supports, Member Properties, Analysis/Designspecifications, etc.

• Visualization and verification of the Model geometry• Running STAAD analysis engine to perform Analysis and

Design• Verification of results - both graphically and numerically• Report generation and printing

Part III of this manual describes how various types of structuralproblems can be modeled and solved using STAAD/Pro.

- Getting Started - - Back to STAAD/Pro ->- Getting Started - - Back to STAAD/Pro ->- Getting Started - - Back to STAAD/Pro ->- Getting Started - - Back to STAAD/Pro ->

Part I – System Requirements, Installation and Start-up

Hardware Requirements2

2. Hardware Requirements

The following requirements are suggested minimums. Systems withincreased capacity provide enhanced performance.

• PC with Pentium 90 or higher processor• Graphics card and monitor with 800x600 resolution (1024x768

recommended), 256 color display (16 bit high colorrecommended).

• 16 MB Free RAM (32 MB strongly recommended).• Windows 95/ NT 4.0 or higher operating system. The software

is capable of running in Windows NT 3.51, however, due tosystem limitations, some of the features (such as Animation)may be disabled.

• Sufficient free space on the hard disk to hold the program anddata files. The disk space requirement would vary dependingon the modules you are installing.

• A Multi-media ready system with sound card and speakers isneeded to run the tutorial movies and slide shows.

Note: Additional RAM, Disk space, and Video memory wouldsignificantly enhance the performance of STAAD/Pro modules.

Note: The user must have a basic familiarity with MicrosoftWindows 95/NT systems in order to use the STAAD/Pro software.


Contents of the STAAD/Pro CD 3

3. Contents of the STAAD/Pro CD

The STAAD/Pro CD offers a lot more than just a means ofinstalling the STAAD/Pro.

• A self-running slide-show (preview) describing differentmodules of STAAD/Pro.

• Installation of selected STAAD/Pro components, including theExtension modules.

• Complete STAAD/Pro documentation in Acrobat PDF format.

• Tutorial movies showing how different tasks can beaccomplished in a step-by-step manner.

To start, run SPROCD.EXE located at the root folder of the CD.The SPROCD Title screen appears as shown in Figure 1.1. TheSPROCD Title screen offers several choices such as View Readme,Install Program, etc. In order to access one of these choices, clickon the button located on the left.

The choices offered by the Title screen are described below:

View ReadmeDisplays the contents of the README.TXT file on the CD. Thisfile is a Text file and contains late-breaking information about theprogram. It is recommended that you read this file even beforeinstalling the program.

Install ProgramAllows you to install selected components of STAAD/Pro. TheExtension components are also offered for installation. However,please note that if you install an Extension module, which you havenot purchased, then the module would only work in ademonstration mode.



Contents of the STAAD/Pro CD4

This option is explained in details in the next section.

Figure 1. 1: The SPROCD Title Screen

Run TutorialThis option allows you to run Tutorial movies showing howdifferent tasks may be performed using STAAD/Pro modules. Themovies are created using the Lotus ScreenCam software.

Please note that you need to have a multi-media ready systemincluding Sound card and Speakers to run the Tutorial movies.

A Quick TourThis option displays a self-running slide show describing thephilosophy behind STAAD/Pro as well as different features of theSTAAD/Pro modules.

Install ManualThis option allows you install the on-line manual (created in PDFformat). The software needed to access these manuals, AcrobatReader 3.0, is installed automatically. Please note that by default,only a link is created to the on-line documentation on the CD. Youmay optionally copy the documentation files to your hard drive.ExitExits the SPROCD program.


Contents of the STAAD/Pro CD 5

Copyright Notices:

A Quick Tour is created using the Microsoft Powerpoint software(Copyright (c) Microsoft Corporation). The Powerpoint viewer isdistributed with the CD.

Movies contained in Tutorials and A Quick Tour are created usingLotus ScreenCAM 97 (Copyright Lotus Corp). The LotusScreenCam player is distributed on the CD.

All documentation are created in Adobe Acrobat PDF format usingAcrobat Exchange 3.0 (Copyright (c) Adobe SystemsIncorporated). The Acrobat Reader 3.0 is distributed with the CD.



Installation6

4. Installation

Please see the Readme.Txt file on the CD for late breakinginformation about Installation and related issues. Also, if youreceive a document titled Installation Notes, it would supercedeall other instructions.

Close all applications before installing STAAD/Pro and runSPROCD.EXE from the root folder of the CD. For explanation ofdifferent facilities offered by the SPROCD program, please refer tothe previous section.

Note: In NT systems, you need to log in with administrative rightsbefore installing STAAD/Pro.

To install the STAAD/Pro software, select the Install Programoption. The installation program follows the standard proceduresand is self-explanatory. When prompted, please select theSTAAD/Pro components you wish to install (see Figure 1.2).

Figure 1. 2: Selection of Components to Install


Installation 7

The components shown above are part of the STAAD/Pro Corepackage. Check the components you want to install and leave theothers as blank. Please note that if the Tutorials component ischecked, then the entire tutorial will be copied to the specified harddrive. You may choose to leave this option unchecked, as theTutorial movies are also accessible from the CD using the RunTutorials option from the Title screen.

The next screen asks you to install the STAAD/Pro Extensioncomponents. Please note that if you install an extension componentthat you have not purchased, the particular module will work onlyas a Demonstration version.

Figure 1. 3: Selection of Design Codes for STAAD

If you have selected to install the STAAD component, the dialogbox shown in Figure 1.3 appears. If you have purchased more thanone Design Codes, you may select all of them by clicking on theappropriate boxes. However, the hardware lock or license managermust support the Design codes installed.

If you select multiple Design Codes in the Figure 1.3, then thedialog box shown in Figure 1.4 appears. Here, you specify whichDesign Code will be used as Default. Note that you may also



Installation8

change the Design Code before performing the Analysis andDesign.

Figure 1. 4: Selection of Default Design Code for STAAD

You would need a hardware lock to run STAAD/Pro. During theinstallation process, the Hardware lock driver is automaticallyinstalled.

After the installation is complete, please restart your machine forthe changes to take effect.

Note: If you do not have Adobe Acrobat Reader 3.0 or abovealready installed, the installation process will launch the AcrobatReader installer. In case there is a problem in installing theAcrobat Reader, please first install the Acrobat Reader manuallyby running Setup.Exe program from the \Acrobat folder on the CD.

Note: The icon for accessing the complete On-line documentationis automatically installed in the STAAD/Pro program group.Please note that this icon allows you to access the documentationfrom the CD only. To install the documentation to your hard drive,see Install Manual option described in Section 3 above.


9

5. Copy Protection Device

STAAD/Pro comes with a copy protection device in the form of ahardware lock. This device must be inserted in the parallel port ofyour computer and must remain there during the entire durationthat you are in one of the STAAD/Pro component programs. If anyother device, such as printer cable, hardware lock for othersoftware, etc., is attached to the parallel port, we recommend thatyou attach the STAAD/Pro hardware lock in front of such devices.

The STAAD/Pro hardware lock is configured for the STAAD/Promodules you have purchased. If you install a component that is notsupported by the hardware lock, then that component will beoperable only as a Demonstration version.

The hardware lock driver(s) are automatically installed during theinstallation process. Please note that in Windows NT systems, youmust have administrative rights before installing the program alongwith the hardware lock.



Running STAAD/Pro10

6. Running STAAD/Pro

Select the STAAD/Pro Design Studio icon from the STAAD/Proprogram group. The STAAD/Pro Main screen appears as shownbelow in Figure 1.5.

Figure 1. 5: The STAAD/Pro Main Screen

Click on the name of a specific module to launch the correspondingmodule. For example, click on the word STAAD to launch theSTAAD/Pro Graphical environment. While you work in theSTAAD/Pro Graphical environment, the STAAD/Pro Main Screenhides itself. After you exit the STAAD/Pro Graphical environment,the STAAD/Pro Main Screen reappears. Please note that you maynot start more than one module at the same time from theSTAAD/Pro Main Screen.

For instructions on how to work with the different STAAD/Promodules, please refer to the respective program manuals.


Part -II

Tutorials


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Table of Contents

1. Read This First 1

2. Tutorial Problem 1: 2D Portal Frame 2

2.1 Description of the Tutorial Problem 4

2.2 Starting the Program 5

2.3 Creating a New Structure 6

2.4 Creating the Model using the Command File 8

2.5 The STAAD/Pro Screen 14

2.6 Creating the Model using Graphical Interface 16

2.6.1 Generating the Model Geometry 162.6.2 Specifying Member Properties 172.6.3 Specifying Material Constants 192.6.4 Specifying Member Offsets 202.6.5 Printing Member Information in the Output File 222.6.6 Specifying Supports 242.6.7 Changing Units 272.6.8 Specifying Loads 282.6.9 Specifying Analysis Type 332.6.10 Specifying Post-Analysis Print Commands 342.6.11 Specifying Steel Design Parameters 362.6.12 Printing Section Displacements in the Output File 412.6.13 Saving the Structure File 43

2.7 Performing Analysis/Design 44

2.8 Viewing the Output File 46

2.9 Graphical Post Processing 53

3. Tutorial Problem 2: 3D Factory Structure 63

3.1 Description of the Tutorial Problem 64

3.2 Starting the Program 67

3.3 Creating a New Structure 68


3.4 The STAAD/Pro Screen 70

3.5 Developing the Model Geometry 72

3.6 Assigning Member Properties 88

3.7 Assigning Member Specifications 94

3.8 Specifying Supports for the Structure 97

3.9 Specifying Loads on the Structure 100

3.10 Specifying Analysis Commands 109

3.11 Specifying Design Parameters 112

3.12 Performing Analysis and Design 116

3.13 Viewing The Output File 118

3.14 Verifying and Viewing Results Graphically 128

3.15 Creating Customized Reports 141

3.16 The STAAD/Pro Command File 150

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1

1. Read This First

STAAD/Pro is simple to use and user-friendly. The entire inputdata may be generated either graphically or by typing simpleEnglish language based commands. No prior knowledge of theCommand language is necessary to get started.

This manual presents two tutorials. Chapter 2 explains how a simple2D Portal Frame can be quickly modeled using the STAAD/ProCommand File as well as the STAAD/Pro GUI. This tutorial isrecommended as a Quick Start. The new users should go throughthis tutorial first.

Chapter 3 provides detailed description on how a 3D factorystructure can be developed using the STAAD/Pro GUI. This tutorialexplains advanced modeling and post-processing facilities.

Both the tutorial problems include Analysis/Design specificationsand result verifications.

Please note that the processes of starting the program and creatinga new structure are explained in Chapter 2 only. These processesare the same whether you choose to work in the STAAD/Pro GUI orin the Command File. It is strongly recommended that you gothrough both the tutorials in order to take the maximum advantageof the features offered by STAAD/Pro.


Part II - Tutorials

Tutorial Problem 12

2. Tutorial Problem 1: 2D Portal Frame

This chapter provides a detailed step-by-step tutorial for creating a2D Portal Frame using the STAAD/Pro. For instructions on creatinga new structure, please refer to Sections 2.2 and 2.3.

This tutorial covers the following topics using both Command Fileand the Graphical interfaces:

• Starting the Program• Creating a New Structure• Creating Joints and Members• Specifying Member Properties• Specifying Material Constants• Specifying Member Offsets• Printing Member Information• Specifying Supports• Specifying Loads• Specifying Analysis Type• Specifying Post-Analysis Print Commands• Specifying Steel Design Parameters• Performing Analysis and Design

All STAAD/Pro Input data are stored in a Text file consisting of simple English-likecommand language. This file is called Command File or Input File.

The Command File may be created by two methods:

• Using the Text Editor• Using the Graphical User Interface

Section 2.4 describes creation of the Command File using the STAAD/Pro EDITOR.

The rest of Chapter 2 explain how the same commands may be specified using theSTAAD/Pro GUI.


Tutorial Problem 1 3

• Viewing the Output File• Verifying results on screen – both graphically and Numerically

The Graphical User Interface (GUI) and the Command File areseamlessly integrated. When you access the Command File from theSTAAD/Pro GUI, the Command File reflects all data enteredthrough the GUI. On the other hand, when you modify and save theCommand File, the GUI immediately shows the changes made tothe structure through the Command File.


Part II - Tutorials

Tutorial Problem 14

2.1 Description of the Tutorial Problem

The project is a single bay, single story steel portal frame that willbe analyzed and designed. The figure below shows the structure.

Figure 2. 1

You shall create a Command File for the above problem. Thecommands used in the Command File have been described in thefollowing pages.

An input file called "INTRO.STD" containing the input data for theabove structure has been provided with your distribution.



2.2 Starting the Program

Select the STAAD/Pro Design Studio icon from the STAAD/Proprogram group. The STAAD/Pro Main Screen appears as shownbelow:

Figure 2. 2

Click on the work STAAD located at the center of the graphics. TheSTAAD/Pro Graphical Environment will be invoked.

Please note that the appearance of the STAAD/Pro Main Screenmay change as more components get added to STAAD/Pro.


Part II - Tutorials

Tutorial Problem 16

2.3 Creating a New Structure

To create a new structure, select New from the File menu from thetop menu bar:

Figure 2. 3

In the next two dialog boxes you will specify general informationabout the structure. These dialog boxes are shown below:

Figure 2. 4

Select the structure type (Plane in this case) and enter a Title forthe structure as shown above. Please note that the type of analysisyou may perform later depends on the type of structure you select atthis point. For example, for a Truss-only structure, you will select


Tutorial Problem 1 7the Truss option here. However, if the structure contains any beamor column member, you should select the Space option.

Press the Next button. The dialog box shown in Figure 2.5 appears. SelectFoot as the Length Unit and Kilo Pound as the Force Unit. These units canbe changed later.

Figure 2. 5

Press the Next button. The dialog box shown in Figure 2.6 appears. Thisdialog box provides the information of your previous selections. Press theFinish button.

Figure 2. 6


Part II - Tutorials

Tutorial Problem 18

2.4 Creating the Model using the Command File

The STAAD/Pro Command file may be created using the EditCommand File option from the Edit menu. You may also use anystandard Text editor such as Notepad to create the Command File.However, the STAAD/Pro Command File EDITOR offers theadvantage of syntax checking as you type the commands. TheSTAAD/Pro keywords, numeric data, comments, etc. are displayed indistinct colors in the EDITOR.

A typical EDITOR screen is shown below.

Figure 2. 7



In the STAAD/Pro EDITOR, type the lines shown in bold below.The commands may be typed in upper or lower case letters. Usuallythe first three letters of a keyword are all that are needed -- the restof the letters of the word are not required. The required letters areunderlined. (“PLANE” = “PLA” = “plane” = “pla”)

STAAD PLA NE INTRODUCTORY PLANE FRAME PROBLEM

Every STAAD/Pro input file has to begin with the word STAAD .The word PLANE signifies that the structure is a plane frame (inthe XY plane). The remainder of the words are the title of theproblem, which is optional. This command is automaticallygenerated using the information you have provided in Section 2.3.

An asterisk in the first column signifies that the line is a commentline and should not be executed. For example, one could have putthe optional title above on a separate line as follows.

* INTRODUCTORY PLANE FRAME PROBLEM

UNIT KIP FEET

Specify the force and length units for the commands to follow. Thiscommand is automatically generated using the information youhave provided in Section 2.3.

JOINT COORDINATES1 0. 0. ; 2 0. 15. ; 3 20. 15. ; 4 20. 0.

Joint numbers and their corresponding global X and Y coordinatesare provided above. Note that the reason why the Z coordinate isnot provided is because the structure is a plane frame. If this were aspace frame, the Z coordinate would also be required. Semicolons(;) are used as line separators. In other words, data which isnormally put on multiple lines can be put on one line by separatingthem with a semicolon.

MEMBER INCIDENCE1 1 2 ; 2 2 3 ; 3 3 4


Part II - Tutorials

Tutorial Problem 110

The members are defined by the joints to which they are connected.

MEMBER PROPERTY AMERICAN1 3 TABLE ST W12X262 TABLE ST W14X34

Specify the member properties. Section 5.20 of the TechnicalReference Manual provides detailed information on memberproperty specifications.

Members 1 and 3 are assigned a W12X26 designation from thebuilt-in AMERICAN steel table. Member 2 is a W14X34. Sections5.20.1 through 5.20.5 of the Technical Reference Manual explainthe convention for assigning member property names.

UNIT INCHESCONSTANTSE 29000.0 ALL

The length unit is changed to INCHES to facilitate input of themodulus of elasticity (E). Material properties such as E, density,Poisson’s ratio, coefficient of thermal expansion (ALPHA) etc. areprovided following the CONSTANT command. See Section 5.26 ofthe Technical Reference Manual for more information.

MEMBER OFFSET2 START 6.0 0. 0.2 END -6.0 0. 0.

Above commands define that member 2 is eccentrically connectedor OFFSET at its START joint by 6 inches in the global Xdirection, 0.0 and 0.0 in Y and Z directions. The same member isoffset by negative 6.0 inches at its END joint. This command isused to take advantage of the program's capability to generate andredistribute secondary forces for eccentric connections. See Section5.25 of the Technical Reference Manual for more information.

PRINT MEMBER INFORMATION



The above command is self-explanatory. The information that isprinted includes start and end joint numbers (incidence), memberlength, beta angle and member end releases.

SUPPORT1 FIXED ; 4 PINNED

A fixed support is located at joint 1 and a pinned support (fixed fortranslations, released for rotations) at joint 4. More information onthe support specification is available in Section 5.27 of theTechnical Reference Manual.

UNIT FT

The length unit is changed to FEET to facilitate input of loads.

LOADING 1 DEAD + LIVEMEMBER LOAD2 UNI GY -2.5

The above commands identify a loading condition. DEAD + LIVEis an optional title to identify this load case. A UNIformlydistributed MEMBER LOAD of 2.5 kips/ft is acting on member 2 inthe negative global Y direction. Member Load specification isexplained in Section 5.32 of the Technical Reference Manual.

LOADING 2 WIND FROM LEFTJOINT LOAD2 FX 10.

The above commands identify a second load case. This load is aJOINT LOAD. A 10 kip force is acting at joint 2 in the global Xdirection.

LOAD COMBINATION 3 75 PERCENT OF (DL+LL+WL)1 0.75 2 0.75

This command identifies a combination load with an optional title.The second line provides the primary load cases and their factorsused for the load combination.


Part II - Tutorials

Tutorial Problem 112PERFORM ANAL YSIS

This command makes the program proceed with the analysis.Section 5.37 of the Technical Reference Manual offers informationon the various analysis options available.

PRINT MEMBER FORCESPRINT SUPPORT REACTIONS

The above print commands are self-explanatory. The member forcesare in the member local axes while support reactions are in theglobal axes.

PARAMETERSCODE AISCUNL 10.0 ALLDFF 250. MEMB 2BEAM 1.0 ALLTRACK 2.0 ALLLOAD LIS T 1 3SELECT MEMBER 2 3

The above sequence of commands is used to initiate the steel designprocess. The command PARAMETERS is followed by the varioussteel design parameters. Specifications of the AISC ASD CODE areto be followed. ALL members have 10 ft unsupported length for thecompression flange (UNL). UNL is used to compute the allowablecompressive stress in bending. A length to deflection ratio (DFF) of250 is specified to ensure that the deflection of any point onmember 2 does not exceed L/250. The BEAM parameter signifiesthat the forces at a total of 13 points (including the start and endpoints) along the length of the member have to be checked duringthe design. The TRACK parameter controls the level of descriptionof the output, 2.0 being the most detailed. The LOAD LISTcommands lists the load cases to be used in the design. TheSELECT MEMBER command asks the program to come up with themost economical section for members 2 and 3 in the context of theabove analysis.

PRINT SECTION DISPLACEMENT SAV E



This command is used to obtain in a tabular form, thedisplacements at every 12th point along the length of the members.These displacements are known as section displacements. TheSAVE command will create a file which can be used bySTAAD/Pro Graphical Environment to graphically display thesection displacements.

PLOT BENDING FILE

This command will create a file which can be used by theSTAAD/Pro Graphical Environment to graphically display themember force diagrams such as bending moments, shear forces etc.

FINISH

A STAAD run is terminated using the FINISH command. Thiscommand may be placed anywhere in the input file to endprocessing of the file. The user will find that this is particularlyuseful while troubleshooting for input data errors.

Save the file and return to the main screen.

This file may now be analyzed using the menu option Analyze PipeRun Analysis. Select the STAAD Analysis option. After the analysisis complete, you may view the STAAD/Pro Command File using themenu option File Pipe View Pipe Output File Pipe STAAD Output.

For on-screen Post-processing facilities, please refer to Section 2.9.


Part II - Tutorials


2.5 The STAAD/Pro Screen

In order to generate the model graphically, you need to be familiarwith the components of the STAAD/Pro screen. A sample of theSTAAD/Pro screen is shown in Figure 2.8. The screen has fivemajor elements as described below:

Menu barLocated at the top of the screen, the Menu bar gives access to allthe facilities of STAAD/Pro.

ToolbarThe dockable Toolbar gives access to the most frequently usedcommands. You may also create your own customized toolbar.

Figure 2. 8 Data Area

MainWindow

Toolbar

PageControl

Menu bar



Main WindowThis is the largest area at the center of the screen, where the modeland the results are displayed.

Page ControlThe Page Control is a set of tabs that appear on the left-most partof the screen. Each tab on the Page Control allows you to performspecific tasks. The organization of the Pages, from top to bottom,represents the logical sequence of operations, such as, definition ofbeams, specification of member properties, loading, and so on.

Each tab has a name and an icon for easy identification. The nameon the tabs may or may not appear depending on your screenresolution and the size of the STAAD/Pro window. However, theicons on the Page Control tabs always appear.

The Pages in the Page Control area depend on the Mode ofoperation. The Mode of operation may be set from the Mode menufrom the Menu bar.

Data AreaThe right side of the screen is called the Data Area, wheredifferent dialog boxes, tables, list boxes, etc. appear depending onthe type of operation you are performing. For example, when youselect the Geometry | Beam Page, the Data Area contains the Node-Coordinate table and the Member-incidence table. When you are inthe Load Page, the contents of the Data Area changes to display thecurrently assigned Load cases and the icons for different types ofloads.

The icons in the toolbar as well as in the Page Control area offerTooltip help. If you are not sure what a particular icon represents,simply move your mouse on top of the icon and wait a moment. Afloating Tooltip help will identify the icon.


Part II - Tutorials


2.6 Creating the Model using Graphical Interface

This section describes the steps to generate the INTRO.STD fileusing the STAAD/Pro GUI. For every step, the correspondingSTAAD/Pro command is also described.

2.6.1 Generating the Model Geometry

Commands to be generated:

JOINT COORDINATES1 0. 0. ; 2 0. 15. ; 3 20. 15. ; 4 20. 0.MEMBER INCIDENCE1 1 2 , 2 2 3 , 3 3 4

Steps:

1. Select the Geometry | Beam Page. Press the Close button in the SnapNode/Beam dialog box.

2. Enter the Joint Coordinate values from 1 through 4 in the Nodes table,located in the Data as shown in Figure 2.9. As Joint Coordinates areprovided, notice the joints appear as points in the Main Window area.

�� Enter member incidences in the Beams table table, located in the Dataas shown in Figure 2.10. Notice that as Node A and Node B values areprovided, a Member, connecting the two nodes, appears in the WholeStructure window.



Figure 2. 9

2.6.2 Specifying Member Properties


MEMBER PROPERTY AMERICAN1 3 TABLE ST W12X262 TABLE ST W14X34

Steps:

1. Select Members 1 and 3 (vertical members) by holding down the Ctrlkey and clicking on them. The selected members will be highlighted.


Part II - Tutorials

Tutorial Problem 1182. Select Commands | Member Property | Steel Table | American from

the menu as shown in the Figure 2.10.

Figure 2. 10

3. Select W12X26 from the Select Beam list box as shown in Figure 2.11and press the Assign button.

Repeat steps 1 through 3, selecting Member 2 (horizontal member) andW14X34 shape.

Note that while selecting shapes for Members in the American SteelTable dialog box, you may automatically select the Materials forthese shapes. Check the Material box and select the material fromthe list below the Material box.



Figure 2. 11

2.6.3 Specifying Material Constants


CONSTANTSE STEEL ALL

Steps:

1. As noted in Section 2.6.2 above, the Material Constant specificationsare specified along with the specification of Member Properties.However, if needed, the Material Constants may be defined using themenu option Commands | Material Constants.


Part II - Tutorials


2.6.4 Specifying Member Offsets


UNIT INCHESMEMBER OFFSET2 START 6.0 0.0 0.02 END -6.0 0.0 0.0

Steps:

1. Select the Unit icon shown in Figure 2.12 from the toolbar.

Figure 2. 12

2. Select Inch from Length Units as shown in Figure 2.13 andpress OK.

Figure 2. 13

3. Select Member 2 (horizontal member) by clicking on themember.



4. Select the Commands | Member Specifications | Offset menuoption as shown in Figure 2.14.

Figure 2. 14

5. Select the Start radio button and enter 6.0 in the X edit box(Figure 2.15) as the offset in the X-direction. Now press theAssign button.


Part II - Tutorials


Figure 2. 15

6. Repeat steps from 1 through 5, selecting the End radio buttonand providing –6.0 in the X edit box.

2.6.5 Printing Member Information in the OutputFile


PRINT MEMBER INFORMATION ALL

Steps:

1. Select Commands | Pre Analysis Print | Member Information from themenu as shown in Figure 2.16.



Figure 2. 16

2. Press the OK button. This command does not require any further input.

Figure 2. 17


Part II - Tutorials


2.6.6 Specifying Supports



Steps:

1. Select the View | Customize View menu option as shown in Figure 2.18.

Figure 2. 18

2. When the dialog box of Figure 2.19 appears, select the Labels tab andcheck the Node Numbers check box. Press the Ok button. This willshow the Node Numbers on the structure in the graphics window.



Figure 2. 19

3. Select the Nodes Cursor menu option from the Select menu as shown inFigure 2.20 and click on node 1 in the Main Window. Node 1 becomeshighlighted.

Figure 2. 20

4. Select the Commands | Support Specifications | Fixed menu option asshown in Figure 2.21.


Part II - Tutorials


Figure 2. 21

5. Press the Assign button to provide a Fixed support at node 1.

Figure 2. 22

Repeat steps 3 through 5, selecting node 4 and Commands | SupportSpecifications | Pinned from the menu to provide a Pinned support at node4.



2.6.7 Changing Units


UNIT FEET KIP

Steps:

1. Select the Unit icon from the toolbar as shown in Figure 2.23.

Figure 2. 23

2. Select units of Foot and KiloPound as shown in Figure 2.24 andpress OK.

Figure 2. 24


Part II - Tutorials


2.6.8 Specifying Loads


LOADING 1 DEAD + LIVEMEMBER LOAD2 UNI GY -2.5LOADING 2 WIND FROM LEFTJOINT LOAD2 FX 10.LOAD COMBINATION 3 75 PERCENT OF (DL+LL+WL)1 0.75 2 0.75

Steps:

1. Select Commands | Loading | Create New Primary Load from the menuas shown in Figure 2.25.

Figure 2. 25

2. Enter the load case number as 1 and enter Dead + Live as the Load Titleas shown in Figure 2.26 and select OK.



Figure 2. 26

3. To define the member load for member number 2, select the Member 2using the Select | Beams Cursor option from the menu and click on thehorizontal member in the Main Window.

4. Select the menu option Commands | Loading | Load Commands |Member | Uniform Force as in Figure 2.27.

Figure 2. 27


Part II - Tutorials

Tutorial Problem 1305. Enter the load intensity (w1) as -2.5. Select the GY option to apply the

load in the global Y direction. Click the Assign button.

Figure 2. 28

6. Now you shall define a Joint Load in a new load case. Repeat step 2and provide a load case number of 2 and WIND FROM LEFT in theTitle edit box.

7. Select Joint 2 by selecting Select | Nodes Cursor from the menu andclicking on the left top joint in the graphics window.

8. Select menu option Commands | Loading | Load Commands | Joint |Joint Load as shown in Figure 2.29.



Figure 2. 29

9. Enter FX as 10 (10 kips) in the Node Loads dialog box. Select Assign.

Figure 2. 30

10. You have finished defining the primary loads. Now you need to definea load combination as 0.75 X (Load 1 + Load 2). Select the Commands| Loading | Load Combination menu option as shown in Figure 2.31.


Part II - Tutorials


Figure 2. 31

11. When the dialog box of Figure 2.32 appears, press the New button.

Figure 2. 32

12. The dialog box of Figure 2.33 appears. Enter the Title as 75 Percent of(DL+LL+WL).

Figure 2. 33


Tutorial Problem 1 3313. Now enter 0.75 in the Factor edit box of the Define Combinations

dialog box (see Figure 2.32). Check the Combine Algebraically checkbox. Select both load cases from the left side list box and press the >button. The Load Cases along with the Combination Factor appear inthe right side list box as shown in Figure 2.32. Press OK.

2.6.9 Specifying Analysis Type


PERFORM ANALYSIS

Steps:

1. Select the Commands | Analysis | Perform Analysis option from themenu.

Figure 2. 34

2. Select the No Print option from the following dialog box and click theOK button.


Part II - Tutorials


Figure 2. 35

2.6.10 Specifying Post-Analysis Print Commands


PRINT MEMBER FORCES ALLPRINT SUPPORT REACTIONS

Steps:

1. Select the Commands | Post-Analysis Print | Member Forces optionfrom the menu as shown in Figure 2.36.



Figure 2. 36

2. Press OK in the dialog box of Figure 2.37 to list All members.

Figure 2. 37

3. Similarly, select Support Reactions from the Commands | Post-Analysis Print menu option. Confirm the selection by choosing Yes (seeFigure 2.38).


Part II - Tutorials


Figure 2. 38

2.6.11 Specifying Steel Design Parameters


LOAD LIST 1 3UNIT INCHES KIPPARAMETERCODE AISCUNL 10 MEMB 2 3BEAM 1 MEMB 2 3TRACK 2 MEMB 2 3SELECT MEMB 2 3

Steps:

1. Select Commands | Loading | Load List from the menu as shown inFigure 2.39.

Figure 2. 39


Tutorial Problem 1 372. From the Load Cases list box on left, double click on 1: DEAD +

LIVE and 3: 75 PERCENT OF (DL+LL+WL) to send them to the LoadList box on right, as shown in Figure 2.40. Press OK.

Figure 2. 40

3. Select Members 2 and 3 by selecting Select | Beams Cursor from themenu and clicking on them in the graphics window while holding downthe control key.

4. Select Commands | Design | Steel Design from the menu as shown inFigure 2.41.

Figure 2. 41

The Design Page is invoked, as shown in Figure 2.42.


Part II - Tutorials


Figure 2. 42

5. Select AISC from the Current Code listbox available at the top of thedata area.

6. Now select the Select Parameters button. The Parameter Selectiondialog box of Figure 2.43 appears.

Figure 2. 43


Tutorial Problem 1 397. Clear all Selected Parameters by clicking the << button. Select Beam,

Track and Unl from the Available Parameters by double clicking eachof them to move them to the Selected Parameters list. Click the OKbutton.

8. Select the Design Parameters button. The Design Parameters dialogbox of Figure 2.44 appears.

Figure 2. 44

9. From the Beam tab, select Beam Parameter (1) then click the Assignbutton. From the Track tab, select Track Parameter (2) then click theAssign button. On the Unl tab, enter an unsupported length of 10.0inches, then click the Assign button. After defining all parameters,click the Close button.

10. Click the Commands button. The Design Commands dialog box ofFigure 2.45 appears.


Part II - Tutorials


Figure 2. 45

11. Go to the Select tab and click the Assign button.



2.6.12 Printing Section Displacements in theOutput File


PRINT SECTION DISPLACEMENT SAVE

Steps:

1. Select Commands | Post-Analysis Print | Section Displacements fromthe menu as in Figure 2.46.

Figure 2. 46

2. In the dialog box of Figure 2.47, check the box associated with Saveand press OK.


Part II - Tutorials


Figure 2. 47



2.6.13 Saving the Structure File


FINISH

Steps:

1. Select the File | Save menu option as shown below. The standard FileSave dialog box appears. Provide a Filename and the directory inwhich the file should be saved.

Figure 2. 48


Part II - Tutorials


2.7 Performing Analysis/Design

The input file (created in using the EDITOR, or createdgraphically) is now ready for analysis and design. During theAnalysis, STAAD/Pro will create an output file with all specifiedresults.

1. Select Analyze | Run Analysis option from the menu as shown in Figure2.49.

Figure 2. 49

2. When the dialog box of Figure 2.50 appears, STAAD Analysis isselected by default. Click the Run Analysis button.

Figure 2. 50

3. When the dialog box of Figure 2.51 appears, press the Execute button.

4. The screen displays the status of the analysis and design. Whenanalysis and design are complete, the program stops and awaits userinput. Press the Done button.



Figure 2. 51


Part II - Tutorials


2.8 Viewing the Output File

During the analysis process, STAAD/Pro creates an Output file.This file provides important information on whether the analysiswere performed properly. For example, if STAAD/Pro encountersan instability problem during the Statics Check, it will be reportedin the Output file.

In order to view the Output file, select File - View - Output File -STAAD Output option from the top menu. The STAAD/Pro outputfile is shown in the next few pages.

The STAAD/Pro Output file is displayed through the STAAD/ProFile Viewer. The viewer allows you to set the text font for theentire file and print the output file to a printer. Use the appropriateFile menu option from the menu bar.

Figure 2. 53

Note: By default, STAAD/Pro echoes the entire Input in the outputfile. Please note that this section of the Output file has beenomitted in this manual.

You may choose not to print the echo of the Input commands in theSTAAD/Pro Output file. Please select Commands - Miscellaneous -Set Echo option from the menu bar and select the Echo Off button.


Tutorial Problem 1 47 ************************************************** * * * STAAD/Pro STAAD-III * * Revision * * Proprietary Program of * * Research Engineers, Inc. * * Date= * * Time= * * * * USER ID: * **************************************************

1. STAAD PLANE INTRODUCTORY PROBLEM 2. UNIT KIP FEET 3. JOINT COORDINATES 4. 1 0. 0. ; 2 0. 15. ; 3 20. 15. ; 4 20. 0. 5. MEMBER INCIDENCE 6. 1 1 2 ; 2 2 3 ; 3 3 4 7. MEMBER PROPERTY AMERICAN 8. 1 3 TABLE ST W12X26 9. 2 TABLE ST W14X34 10. UNIT INCHES 11. CONSTANTS 12. E 29000.0 ALL 13. MEMBER OFFSET 14. 2 START 6.0 0. 0. 15. 2 END -6.0 0. 0. 16. PRINT MEMBER INFORMATION

MEMBER INFORMATION ------------------

MEMBER START END LENGTH BETA JOINT JOINT (INCH) (DEG) RELEASES 1 1 2 180.000 0.00 2 2 3 228.000 0.00 3 3 4 180.000 0.00

************ END OF DATA FROM INTERNAL STORAGE ************

17. SUPPORT 18. 1 FIXED ; 4 PINNED 19. UNIT FT 20. LOADING 1 DEAD + LIVE 21. MEMBER LOAD 22. 2 UNI GY -2.5 23. LOADING 2 WIND FROM LEFT 24. JOINT LOAD 25. 2 FX 10. 26. LOAD COMBINATION 3 27. 1 0.75 2 0.75 28. PERFORM ANALYSIS

P R O B L E M S T A T I S T I C S -----------------------------------

NUMBER OF JOINTS/MEMBER+ELEMENTS/SUPPORTS = 4/ 3/ 2 ORIGINAL/FINAL BAND-WIDTH = 1/ 1 TOTAL PRIMARY LOAD CASES = 2, TOTAL DEGREES OF FREEDOM = 7 SIZE OF STIFFNESS MATRIX = 42 DOUBLE PREC. WORDS REQRD/AVAIL. DISK SPACE = 12.00/ 2047.7 MB, EXMEM = 423.8 MB


Part II - Tutorials

Tutorial Problem 148 29. PRINT MEMBER FORCES

MEMBER END FORCES STRUCTURE TYPE = PLANE ----------------- ALL UNITS ARE -- KIP FEET

MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z 1 1 1 23.23 -3.50 0.00 0.00 0.00 -10.48 2 -23.23 3.50 0.00 0.00 0.00 -42.02 2 1 -4.22 7.68 0.00 0.00 0.00 65.50 2 4.22 -7.68 0.00 0.00 0.00 49.67 3 1 14.25 3.13 0.00 0.00 0.00 41.27 2 -14.25 -3.13 0.00 0.00 0.00 5.74

2 1 2 3.50 23.23 0.00 0.00 0.00 30.40 3 -3.50 24.27 0.00 0.00 0.00 -40.36 2 2 2.32 -4.22 0.00 0.00 0.00 -47.56 3 -2.32 4.22 0.00 0.00 0.00 -32.72 3 2 4.37 14.25 0.00 0.00 0.00 -12.87 3 -4.37 21.37 0.00 0.00 0.00 -54.81

3 1 3 24.27 3.50 0.00 0.00 0.00 52.50 4 -24.27 -3.50 0.00 0.00 0.00 0.00 2 3 4.22 2.32 0.00 0.00 0.00 34.83 4 -4.22 -2.32 0.00 0.00 0.00 0.00 3 3 21.37 4.37 0.00 0.00 0.00 65.49 4 -21.37 -4.37 0.00 0.00 0.00 0.00

************** END OF LATEST ANALYSIS RESULT **************

30. PRINT SUPPORT REACTIONS

SUPPORT REACTIONS -UNIT KIP FEET STRUCTURE TYPE = PLANE -----------------

JOINT LOAD FORCE-X FORCE-Y FORCE-Z MOM-X MOM-Y MOM Z 1 1 3.50 23.23 0.00 0.00 0.00 -10.48 2 -7.68 -4.22 0.00 0.00 0.00 65.50 3 -3.13 14.25 0.00 0.00 0.00 41.27 4 1 -3.50 24.27 0.00 0.00 0.00 0.00 2 -2.32 4.22 0.00 0.00 0.00 0.00 3 -4.37 21.37 0.00 0.00 0.00 0.00


31. PARAMETERS 32. CODE AISC 33. UNL 10.0 ALL 34. DFF 250. MEMB 2 35. BEAM 1.0 ALL 36. TRACK 2.0 ALL 37. LOAD LIST 1 3 38. SELECT MEMBER 2 3



STAAD-III MEMBER SELECTION - (AISC) ***********************************

|--------------------------------------------------------------------------| | Y PROPERTIES | |************* | IN INCH UNIT | | * |=============================| ===|=== ------------ | |MEMBER 2 * | | | AX = 10.00 | | * | ST W14 X34 | | --Z AY = 3.98 | |DESIGN CODE * | | | AZ = 4.09 | | AISC-1989 * =============================== ===|=== SY = 6.91 | | * SZ = 48.64 | | * |<---LENGTH (FT)= 19.00 --->| RY = 1.53 | |************* RZ = 5.83 | | | | 77.4 (KIP-FEET) | |PARAMETER | L1 L1 STRESSES | |IN KIP INCH | L1 IN KIP INCH | |--------------- + -------------| | KL/R-Y= 149.37 | L3 FA = 6.69 | | KL/R-Z= 39.10 + L3 fa = 0.35 | | UNL = 120.00 | L3 L1 FCZ = 21.60 | | CB = 1.00 + FTZ = 21.60 | | CMY = 0.85 | L3 FCY = 27.00 | | CMZ = 0.85 +L1 FTY = 27.00 | | FYLD = 36.00 | L1 L3 fbz = 19.10 | | NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 | | DFF = 250.00 20.3 FV = 14.40 | | dff = 522.27 ABSOLUTE MZ ENVELOPE Fey = 6.69 | | (WITH LOAD NO.) Fez = 97.67 | | | | MAX FORCE/ MOMENT SUMMARY (KIP-FEET) | | ------------------------- | | | | AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z | | | | VALUE 4.4 24.3 0.0 0.0 77.4 | | LOCATION 0.0 19.0 0.0 0.0 9.5 | | LOADING 3 1 0 0 1 | | | |**************************************************************************| |* *| |* DESIGN SUMMARY (KIP-FEET) *| |* -------------- *| |* *| |* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *| | FX MY MZ LOCATION | | ====================================================== | | PASS AISC- H1-3 0.937 1 | | 3.50 C 0.00 -77.43 9.50 | |* *| |**************************************************************************| | | |--------------------------------------------------------------------------|


Part II - Tutorials


STAAD-III MEMBER SELECTION - (AISC) ***********************************

|--------------------------------------------------------------------------| | Y PROPERTIES | |************* | IN INCH UNIT | | * |=============================| ===|=== ------------ | |MEMBER 3 * | | | AX = 10.00 | | * | ST W14 X34 | | --Z AY = 3.98 | |DESIGN CODE * | | | AZ = 4.09 | | AISC-1989 * =============================== ===|=== SY = 6.91 | | * SZ = 48.64 | | * |<---LENGTH (FT)= 15.00 --->| RY = 1.53 | |************* RZ = 5.83 | | | | 65.5 (KIP-FEET) | |PARAMETER |L3 STRESSES | |IN KIP INCH | L3 L3 IN KIP INCH | |--------------- + L3 -------------| | KL/R-Y= 117.92 | L3 FA = 10.58 | | KL/R-Z= 30.87 + L3 fa = 2.14 | | UNL = 120.00 | L3 FCZ = 21.60 | | CB = 1.00 + FTZ = 21.60 | | CMY = 0.85 | L3 L3 FCY = 27.00 | | CMZ = 0.85 + L3 FTY = 27.00 | | FYLD = 36.00 | L1 fbz = 16.16 | | NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 | | DFF = 0.00 -3.6 FV = 14.40 | | dff = 0.00 ABSOLUTE MZ ENVELOPE Fey = 10.74 | | (WITH LOAD NO.) Fez = 156.71 | | | | MAX FORCE/ MOMENT SUMMARY (KIP-FEET) | | ------------------------- | | | | AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z | | | | VALUE 24.3 4.4 0.0 0.0 65.5 | | LOCATION 0.0 0.0 0.0 0.0 0.0 | | LOADING 1 3 0 0 3 | | | |**************************************************************************| |* *| |* DESIGN SUMMARY (KIP-FEET) *| |* -------------- *| |* *| |* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *| | FX MY MZ LOCATION | | ====================================================== | | PASS AISC- H1-2 0.847 3 | | 21.37 C 0.00 65.49 0.00 | |* *| |**************************************************************************| | | |--------------------------------------------------------------------------|


Tutorial Problem 1 51 39. PRINT SECTION DISPLACEMENT SAVE

MEMBER SECTION DISPLACEMENTS ---------------------------- UNIT =INCHES FOR FPS AND CM FOR METRICS/SI SYSTEM

MEMB LOAD GLOBAL X,Y,Z DISPL FROM START TO END JOINTS AT 1/12TH PTS 1 1 0.0000 0.0000 0.0000 -0.0033 -0.0016 0.0000 -0.0095 -0.0031 0.0000 -0.0164 -0.0047 0.0000 -0.0221 -0.0063 0.0000 -0.0246 -0.0079 0.0000 -0.0220 -0.0094 0.0000 -0.0121 -0.0110 0.0000 0.0070 -0.0126 0.0000 0.0373 -0.0141 0.0000 0.0807 -0.0157 0.0000 0.1393 -0.0173 0.0000 0.2151 -0.0188 0.0000

3 0.0000 0.0000 0.0000 0.0103 -0.0010 0.0000 0.0376 -0.0019 0.0000 0.0802 -0.0029 0.0000 0.1362 -0.0039 0.0000 0.2039 -0.0048 0.0000 0.2816 -0.0058 0.0000 0.3673 -0.0067 0.0000 0.4593 -0.0077 0.0000 0.5559 -0.0087 0.0000 0.6552 -0.0096 0.0000 0.7555 -0.0106 0.0000 0.8550 -0.0116 0.0000

MAX LOCAL DISP = 0.15230 AT 75.00 LOAD 3 L/DISP= 1181

2 1 0.2151 -0.0188 0.0000 0.2149 -0.1311 0.0000 0.2147 -0.2424 0.0000 0.2145 -0.3408 0.0000 0.2142 -0.4168 0.0000 0.2140 -0.4641 0.0000 0.2138 -0.4788 0.0000 0.2135 -0.4600 0.0000 0.2133 -0.4093 0.0000 0.2131 -0.3313 0.0000 0.2128 -0.2333 0.0000 0.2126 -0.1252 0.0000 0.2124 -0.0197 0.0000

3 0.8550 -0.0116 0.0000 0.8547 -0.1299 0.0000 0.8544 -0.2340 0.0000 0.8541 -0.3170 0.0000 0.8538 -0.3744 0.0000 0.8536 -0.4033 0.0000 0.8533 -0.4031 0.0000 0.8530 -0.3753 0.0000 0.8527 -0.3235 0.0000 0.8524 -0.2531 0.0000 0.8521 -0.1718 0.0000 0.8518 -0.0893 0.0000 0.8515 -0.0173 0.0000


3 1 0.2124 -0.0197 0.0000 0.2452 -0.0181 0.0000 0.2648 -0.0164 0.0000 0.2725 -0.0148 0.0000 0.2694 -0.0131 0.0000 0.2567 -0.0115 0.0000 0.2356 -0.0098 0.0000 0.2073 -0.0082 0.0000 0.1730 -0.0066 0.0000 0.1340 -0.0049 0.0000 0.0913 -0.0033 0.0000 0.0463 -0.0016 0.0000 0.0000 0.0000 0.0000


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3 0.8515 -0.0173 0.0000 0.8436 -0.0159 0.0000 0.8192 -0.0145 0.0000 0.7799 -0.0130 0.0000 0.7271 -0.0116 0.0000 0.6624 -0.0101 0.0000 0.5872 -0.0087 0.0000 0.5030 -0.0072 0.0000 0.4114 -0.0058 0.0000 0.3138 -0.0043 0.0000 0.2117 -0.0029 0.0000 0.1066 -0.0014 0.0000 0.0000 0.0000 0.0000


************ END OF SECT DISPL RESULTS ***********

40. FINISH

*************** END OF STAAD-III ***************



2.9 Graphical Post Processing

STAAD/Pro offers extensive result verification and visualizationfacilities. These facilities are accessed from the Post ProcessingMode. For this tutorial problem, you shall perform the followingtasks:

• Annotate the structure with different labels• Create Bending Moment Diagram on screen• Display the Dimensions on the structure• Display Loads on the structure

For information on generating Customized Reports, please refer to theTutorial Problem 2, described in Chapter 3.

The Post Processing mode is used to verify the analysis and design resultsand generate reports. The Post Processing mode is invoked from the Modemenu as shown in Figure 2.54.

Figure 2. 54

Select the Post Processing option from the Mode menu.

The Results Setup dialog box (shown in Figure 2.55) appears. Select theload cases for which to display the results. For our case, select all LoadCases. Then click OK.


Part II - Tutorials


Figure 2. 55

Notice the tabbed Page Control bar and the menu bar change to offer thepost processing functions.

You shall now annotate the view of the structure displayed in the MainWindow area. Select the Symbols and Labels icon from the toolbar.

Figure 2. 56

From the Labels tab of the Diagrams dialog box (see Figure 2.57), selectNode Numbers, Beam Numbers, Property References and Supports. Selectthe OK button to see the changes.



Figure 2. 57

Figure 2.58 shows the structure with the annotations.


Part II - Tutorials


Figure 2. 58

Using the Front View icon from the toolbar, change the view of thestructure to the XY plane.

Figure 2. 59



Figure 2. 60

You shall now display the bending moment diagrams on the structure.Select the Results menu. Then select the Bending Moment option to viewthe bending moment diagrams on the model. From the same menu, deselectDeflection and Section Displacement options.


Part II - Tutorials


Figure 2. 61

You can display the Bending Moment values on the diagram as well. Todisplay the values of the bending moments at the ends and midpoints of themembers, select the View Values option from the Results menu. The dialogbox of Figure 2.62 appears.



Figure 2. 62

From the Range tab, select All members.

From the Beam Results tab, select the Ends and Midpoint checkboxes underthe Bending group. Click the Annotate button and notice that the valuesappear on the structure. Click the Close button to close the dialog box.

Maximize the Whole Structure window to get a better view. Figure 2.63shows the bending moment diagrams on the structure.


Part II - Tutorials


Figure 2. 63

Now let us display the bending moment diagrams for load case 2. Selectthe Symbols and Labels icon from the toolbar. Select the Results tab.Choose Load Case 2: WIND FROM LEFT from the Load case list box asshown in Figure 2.64. Click the OK button.



Figure 2. 64

You shall now display the structure with dimensions as well as appliedloads. Select the Symbols and Labels icon from the toolbar. From theResults tab, deselect Bending zz and select the Loads checkbox. Select loadcase 1: DEAD + LIVE from the Load Case list box. Click OK. Nowdisplay the dimension the members using the Dimension icon.


Part II - Tutorials


Figure 2. 65

You may save the screenshot by clicking on the Take Picture icon. Thispicture may be included in custom reports. See Chapter 3 for tutorial ongenerating custom reports.

For detailed information on the Post Processing features, please refer to thePost Processing section in the STAAD/Pro Graphical Environmentmanual.



3. Tutorial Problem 2: 3D Factory Structure (using STAAD/Pro GUI)

This chapter provides a detailed step-by-step tutorial for creating a3D Factory Structure using the STAAD/Pro GUI. At the end of thischapter, the corresponding STAAD/Pro Command File is explained.The tutorial covers the following topics:

• Starting the Program• Creating a New Structure• Using Grids to add members• Changing view orientations• Displaying Node/Member numbers (Labels) on the structure• Controlling font/color for the Labels• Breaking or Splitting Members• Selecting multiple members• Creating portions of structure by Mirroring• Copying the 2D structure to form a 3D structure (Translational

Repeat)• Deleting members• Rotating the structure on screen• Assigning Member Properties• Assigning Member Specification• Specifying Supports – Pinned, Roller (Fixed But)• Specifying Loads – including Load Combinations• Specifying Analysis Commands• Specifying Steel Design Parameters• Performing Analysis and Design• Viewing the Output File• Verifying results on screen – both graphically and Numerically• Taking Picture of the screen to be included in reports• Creating and viewing Custom report


Part II - Tutorials


3.1 Description of the Tutorial Problem

This tutorial guides you through a simple project that demonstratesthe logical flow from structural modeling to analysis to resultverification and report generation. The tutorial also explains thecommands in the STAAD/Pro Command File. The STAAD/ProCommand File and the Graphical User Interface (GUI) areseamlessly integrated. Any addition or modification made throughthe GUI is automatically reflected in the Command File as you savethe structure. On the other hand, any change made in the CommandFile is reflected in the Graphical Interface.

After completing this tutorial, you may explore the many otherfeatures of the program. The tutorial problem is a 3D factorystructure as shown below.

Figure 2. 66



The dimensions of the structure are shown in Figures 2.67 and 2.68in front and side elevation views. Also, all the structural membersare identified with tags (such as "Bottom Chord") which will beused in the tutorial to refer to them.

Figure 2. 67


Part II - Tutorials


Figure 2. 68



3.2 Starting the Program

Select the STAAD/Pro Design Studio icon from the STAAD/Proprogram group. The STAAD/Pro Main Screen appears as shownbelow:

Figure 2. 69

Click on the work STAAD located at the center of the graphics. TheSTAAD/Pro Graphical Environment will be invoked.

Please note that the appearance of the STAAD/Pro Main Screenmay change as more components get added to STAAD/Pro.


Part II - Tutorials


3.3 Creating a New Structure

To create a new structure, select New from the File menu from thetop menu bar:

Figure 2. 70

In the next two dialog boxes you will specify general informationabout the structure. These dialog boxes are shown below:

Figure 2. 71

Select the structure type (Space in this case) and enter a Title forthe structure as shown above. Please note that the type of analysisyou may perform later depends on the type of structure you select atthis point. For example, for a Truss-only structure, you will selectthe Truss option here. However, if the structure contains any beamor column member, you should select the Space option.



Figure 2. 72

The Step 2 dialog box allows you to specify the units of Length andForce. Please note that at any point later, you may change theseunits.

Now the following message box appears:

Figure 2. 73

Click Finish to complete setting up of the new structure.


Part II - Tutorials


3.4 The STAAD/Pro Screen

A sample of the STAAD/Pro screen is shown in Figure 2.74. Thescreen has five major elements as described below:

Menu barLocated at the top of the screen, the Menu bar gives access to allthe facilities of STAAD/Pro.

ToolbarThe dockable Toolbar gives access to the most frequently usedcommands. You may also create your own customized toolbar.

Main WindowThis is the largest area at the center of the screen, where the modeland the results are displayed.

Figure 2. 74Data Area

MainWindow

Toolbar

PageControl

Menu bar



Page ControlThe Page Control is a set of tabs that appear on the left-most partof the screen. Each tab on the Page Control allows you to performspecific tasks. The organization of the Pages, from top to bottom,represents the logical sequence of operations, such as, definition ofbeams, specification of member properties, loading, and so on.

Each tab has a name and an icon for easy identification. The nameon the tabs may or may not appear depending on your screenresolution and the size of the STAAD/Pro window. However, theicons on the Page Control tabs always appear.

The Pages in the Page Control area depend on the Mode ofoperation. The Mode of operation may be set from the Mode menufrom the Menu bar.

Data AreaThe right side of the screen is called the Data Area, wheredifferent dialog boxes, tables, list boxes, etc. appear depending onthe type of operation you are performing. For example, when youselect the Geometry | Beam Page, the Data Area contains the Node-Coordinate table and the Member-incidence table. When you are inthe Load Page, the contents of the Data Area changes to display thecurrently assigned Load cases and the icons for different types ofloads.The icons in the toolbar as well as in the Page Control area offerTooltip help. If you are not sure what a particular icon represents,simply move your mouse on top of the icon and wait a moment. Afloating Tooltip help will identify the icon.


Part II - Tutorials


3.5 Developing the Model Geometry

The factory shade in our Tutorial project is a 3D structurecomprised of several identical 2D structures, connected along the Zdirection. You can take advantage of this fact by modeling a simple2D portal frame and then making multiple copies of it to form thebays along the length of the structure. The dimension of the desired2D portal is shown in Figures 2.67 and 2.68 earlier.

First, you have to set up a reference grid for creating the joints andmembers. From the Geometry menu, select Snap/Grid Node PipeBeam option. The Snap Node/Beam dialog box appears:

Figure 2. 75

Click on the X-Y button in the Plane button group. In theConstruction Lines group, set X to 30 and Y to 24. This will createa grid in the X-Y plane. The grid will be 30 ft wide in X and 24 fthigh in Y (vertical) direction. The grid spacing is 1 ft (the default).Note that the Snap Node/Beam button is selected (depressed). Thismeans that you may start adding nodes and beams right away by

Setting upGrids



clicking on grid intersections. When you want to get out of thismode (of adding the nodes and beams), simply click on this buttononce more.

At this stage, also switch to the Elevation view (X-Y plane) in theMain Window. Click on the X-Y elevation icon from the toolbar:

Figure 2. 76

Click at the origin (0,0,0) to create the first node there. Then movevertically upward and click at the (0,16,0) point. Note that thestatus bar located at the bottom of the window continuously updatesthe X, Y, and Z coordinates of the current cursor position:

Figure 2. 77

Note that you have just created two nodes joined by a beammember. In the same way, click on the following points to createnodes and automatically join successive nodes by beam members:

(15,24,0), (30, 16,0), and (30,0,0)

Click on the Snap Node/Beam button on the Snap Node/Beamdialog box to stop adding nodes and members. The structure nowlooks like the following:

ElevationView

AddingMembersGraphically


Part II - Tutorials


Figure 2. 78

Switch to the Geometry | Beam Page now by clicking on the Beamicon from the Page Control area (the second from top). Two tables,Nodes (showing Node-Coordinates) and Beams (showing member-incidences and properties) appear in the Data area on the right.

Figure 2. 79



You can add members using the Beams table also. On Beam no 5(currently blank) type 2 as Node A and 4 as Node B. You will noticethat in the Main Window, a member (horizontal) has been addedbetween nodes 2 and 4.

Figure 2. 80

Now bring back the Grids once more. As before, from the Geometrymenu, select the Snap/Grid Node → Beam option. Set the plane toX-Y and grid extents to 30 and 24 ft for X and Y directionsrespectively. At this point, also turn on the Node and Beam numberdisplay. Click the right mouse button on any blank area of the MainWindow. From the pop-up menu, select Labels. The followingdialog box appears:

AddingMembersUsing Tables


Part II - Tutorials


Figure 2. 81

As shown, turn on the Node Numbers and Beam Numbers byclicking on these check boxes. Click OK to close the dialog box.The screen looks like the following:

DisplayingNode/BeamNumbers



Figure 2. 82

You may increase the font size for the beam labels to make thesemore legible. From the View menu, select Options and then selectthe Beam Label tab:

Figure 2. 83

ControllingFonts forLabels


Part II - Tutorials


Figure 2. 84

This dialog box lets you control the style of beam label display, therelative position (alignment) with respect to the beam, Fonts, etc.Click on the Fonts button and select size 10.

Figure 2. 85



Close the Options dialog box. Note that the beam label sizes haveincreased.

Let us now complete the 2D portal frame. Insert a node in themiddle of the Top Chord member, 2. To do this, select the InsertNode option from the Geometry menu and click on member 2. Thefollowing dialog box appears:

Figure 2. 86

Click on the Add Mid Point button. A new node number (6 here)appears on the diagram. The value of n (number of divisions) is setto 2. The dialog box also shows you the start and the end nodes aswell as the total length of the beam. You may also add a new pointor divide the beam into n equal sections using this facility.

SplittingBeam byInsertingNodes


Part II - Tutorials


Figure 2. 87

After the node is created, the previous beam (2) is automaticallysplit into two beams (2 and 6) (see above). Next, on the SnapNode/Beam dialog box, check the box Snap to existing nodes too.This allows you to select an existing node for creating additionalmembers. Click on the Snap Node/Beam button to add membersnow. First, hold down the Control key and click on the newlycreated node, 6. (Control+Click allows you to select the startingnode for adding a member. Not pressing the Control key will causea new beam to be added from the last selected node to the currentnode.) Now, with the help of the coordinate display on the statusbar, select the second point as (11, 16, 0). Click on the topmostnode (3) to finish. Close the Snap Node/Beam dialog box.



Figure 2. 88

Next, you are going to create the remaining Transverse Trussmembers by mirroring the newly created Transverse Truss members(8 and 9) (see figure above). The plane of the mirror is the verticalY-Z plane passing through the topmost point (node 3). First selectthe members 8 and 9. From the Select menu, select the BeamsCursor option. This allows you to select only the beams, ignoringall other entities on screen. Click on the members 8 and 9 whileholding the Ctrl key. Note that these members are drawn in a thickline to indicate that they are selected.

After selecting the members, from the Geometry menu, select theMirror option. The following dialog box appears:

Mirroring


Part II - Tutorials


Figure 2. 89

Set the Mirror Plane Direction to Y-Z and set the Generate Modeto Copy. Next, enter the Distance to Origin as 15 ft (as node 3 is at15 ft distance from the origin). Click OK to see that the membershave been mirrored.

Now, you shall insert a node at the middle of each of the verticalcolumn members (1 and 4). These nodes would be useful to connectthe future bays in the Z direction forming the Bottom LongitudinalBeams. Use the Geometry-Insert Node command and use the AddMid Point button to add a node in the middle of members 1 and 4.The structure now looks like the following:



Figure 2. 90

Next, you shall copy this 2D portal frame 5 times at 25 ft distancein the Z direction and connect these portals to form 5 bays of thefactory shade. Switch to Isometric view by clicking on the toolbarshown in Figure 2.91:

Figure 2. 91

Select all members by window selection (i.e., Click at a point onthe top-left corner of the main window. Hold and drag the mouse tocreate a window that will encompass the entire frame. Release themouse at the right-bottom corner). Next, from the Geometry menuselect Translational Repeat. The following dialog box appears:

Transla-tionalRepeat


Part II - Tutorials


Figure 2. 92

Set the Global Direction to Z, the Default Step Spacing to 25 andno. of steps to 5. Check the Link Step box – this automaticallyconnects the successive bays. Note that you may change the spacingfor any individual "Step" using the Step-Spacing table.

Following is the result of the Translational Repeat command afterthe Node and Beam Labels are switched off.

Figure 2. 93



Note that the base nodes are also connected. However, we need notdelete these members individually. You can display the structure inside view (Y-Z plane) and delete the base members for all bayssimultaneously. Click on the Side view icon on the toolbar:

Figure 2. 94

Use window selection to select all members connecting the base(bottom) nodes. The structure with the selected members is shownbelow:

Figure 2. 95

Press the Delete key to delete the selected members. Note that eventhe members behind the visible members have been selected. Thusthe warning message shows that 10 beams are about to be deleted:

Figure 2. 96

Select OK. Now the entire factory shade outline is generated.

Note: You may use the Open Base check box in the 3D Repeatdialog box (Figure 2.92) to join the 2D structures without joining

DeletingMembers


Part II - Tutorials


the bases. This option was not chosen in this tutorial to show howthe Delete Member facility work.

You need to add the cross-bracings in the longitudinal direction onthe central bay (between the 3rd and 4th frames) as shown in thefigure below:

Figure 2. 97

This can be very easily done by using the Snap/Grid Nodes optionas explained before. At this point, you need to rotate the structureon screen to add the bracings on the other side of the structure.

STAAD/Pro offers several ways of rotating the structure on screen.The rotation icons on the toolbar may be used to rotate the structureLeft or Right about the vertical (Y) axis.

Figure 2. 98

You may also simply press the Left and Right arrow keys to rotatethe structure. Another way would be to use the Orientation facility.

RotatingStructureon Screen



Right-click on a blank portion of the Main Window and select theOrientation option from the pop-up menu (or select the View PipeOrientation option). The following dialog box appears:

Figure 2. 99

Add or subtract 180 from the existing Rotation angle value (in thiscase, the previous angle of 330 is replaced by 150). Click Applyand then close the Orientations dialog box. The structure hasrotated by 180 degrees.

Figure 2. 100

Now add the rest of the longitudinal bracings to finish the geometryof the model.


Part II - Tutorials


3.6 Assigning Member Properties

Member cross-sectional properties are assigned using the PropertyPage. For the tutorial problem, let us assign the member propertiesas noted below. Please note that all sections given below are takenfrom the American Steel tables.

All Vertical Columns W24x68Bottom Chords Back-to-back Double Angle

(L20x20x4) with a spacing of 1.5inch in between.

All Perimeter Beams Single Channel (C10x15)Bottom Rafters Tee section, cut from wide flange

W10x30.Top Rafters Pipe section S10Top Chords Angle section (L25x25x4)Transverse Trusses Angle section (L25x25x4)Longitudinal Bracings Angle section (L25x25x4)

To assign any member cross-sectional properties you need to followthese basic steps:

i) Select the Property Page.

ii) Select the members.

iii) From the Property dialog box (shown in Figure 2.101), selectthe Database button.

iv) Select the Steel table from the Select Country dialog box(Figure 2.102). For this tutorial, always select the Steel table asAmerican.

v) From the American Steel Table, select the tab for the type ofsection you need (see Figure 2.103). If you select other countrycodes, these tabs would change to show the steel sections forthe respective country. Select the required steel section. Ifrequires, specify additional parameters (Composite Section,Double Angle, etc.).



Also in Figure 2.103, note that you may select the memberproperty along with the material. When the Material checkboxis checked, the member is assigned the material selected fromthe associated drop down list.

Experienced STAAD users, may note that this is equivalent tothe Constant specification in the STAAD/Pro Command File.

vi) Click on the Assign button to assign the property to the selectedmembers.

Figure 2. 101

Figure 2. 102


Part II - Tutorials


Figure 2. 103

Note that the procedure of assigning Steel sections for differentstructural elements is the same, steps (i) through (vi) as discussedbefore. The only difference is in step (ii) (selection of themembers) and step (vi) (selection of steel sections).

To select the vertical column members, switch to the Front viewand select members by Window as shown in Figure 2.104. With themembers selected, switch to Isometric view (Figure 2.106). Clickon the Longitudinal Bracing members to deselect them. Now followsteps (iii) through (vi) to assign the W24x68 section to the selectedmembers.



Figure 2. 104

Figure 2. 105


Part II - Tutorials


Figure 2. 106

Note that this member property has been added to the structure witha Property Tag, 1. In case the structure has more W24x68 members,you may simply assign this property (Tag) to those members, too.

For the Bottom Chords, to specify a double angle, select theangle section L20204 from the Select Angle list box. Now selectthe radio button labeled LD and specify SP (Space betweenangles) as 1.5.



Figure 2. 107

In a similar manner, specify the sectional properties for theremaining members.


Part II - Tutorials


3.7 Assigning Member Specifications

The Transverse Truss members at the roof of the structure need tobe identified since these members are able to carry axial loads only.The Spec Page allows you to specify selected members as Trussmembers.

Select the Spec Page. The Specifications dialog box appears in theData Area as shown below.

Figure 2. 108

This dialog box allows you to input specific structural conditions ofMembers (Truss, Cable, Tension-Only, Releases etc.), Member end-conditions (e.g. Master/Slave), and Plate specifications such asElement Release.

Select the Truss members using window selection.. Hold down theControl key as you make the successive windows. The selectedmembers are shown below in Figure 2.109:



Figure 2. 109

Switch to Isometric view to visually confirm that the desiredmembers are selected (Figure 2.110). Select the Beam... button inthe Specifications dialog box. Click on the Truss tab and then clickon the Assign button to specify the selected members as Trussmembers.


Part II - Tutorials


Figure 2. 110



3.8 Specifying Supports for the Structure

For the factory shade structure, you shall define all base joints onleft (at X=0, Y=0) to be Pinned supported and all base joints onright (at X=30, Y=0) to be Roller supported with releases intranslational X, and rotational X, Y, and Z directions.

Click on the Support Page button. Switch to Front view. The cursorchanges to the Node cursor for selection of nodes. Select a smallwindow around the bottom-left (base) node. From the Supportsdialog box (Figure 2.111), click on the Add button. Note thatcurrently a No support specification exists which may be used toremove a support from a node.

Figure 2. 111


Part II - Tutorials


Figure 2. 112

Select the Pinned tab and click Assign to assign Pinned supports tothe selected nodes. The Pinned support icon appears on thestructure.

In a similar fashion, select all base nodes at right (at X=30). . Fromthe Supports dialog box (Figure 2.111), click on the Add button.Select the Fixed But tab. Check boxes under the Release group forFX, MX, MY, and MZ (Figure 2.113). Click on the Assign buttonto assign the support to selected nodes.



Figure 2. 113

The Supports dialog box now displays the supports just added tothe structure (Figure 2.114). Each type of support is marked with asupport number. Any of these supports may now be assigned to anyother nodes on the structure without going through the supportcreation process.

Figure 2. 114


Part II - Tutorials


3.9 Specifying Loads on the Structure

The following loads will be applied on the structure:

Load Case 1 Selfweight

Load Case 2 Dead Load 10 Kips, acting vertically downwardon the nodes of the transverse trusses, includingthe topmost nodes.

Load Case 3 Wind Load from Left acting in positive Xdirection.Interior nodes along the Top Perimeter beam:10KipsExterior nodes along the Top Perimeter beam:5KipsInterior nodes along the Purlin: 3.5 KipsExterior nodes along the Purlin: 1.75 KipsInterior nodes along the Top Rafter: 2 KipsExterior nodes along the Top Rafter: 1 Kip

Load Case 4 Combination Load case 1.1 x Selfweight+ 1.4 x Dead Load+ 1.5 x Wind Load

Loads are assigned using the Load Page.

Load Case 1: Selfweight

When you select the Load Page from the Page Control Area, thefollowing dialog box appears:



Figure 2. 115

This dialog box allows you to specify a Load Case for which youwant to input the loads. You may either define a new load case orselect an existing one. In the above dialog box, only the CreateNew Primary Load Case option is active. This is because no LoadCase has been defined for the structure yet.

A Load Case is identified by a Load Case Number and an optionalTitle. In the dialog box in Figure 2.115, accept the default LoadCase Number, 1, and enter the Load Case Title as Selfweight. TheLoads dialog box appears in the Data Area as shown below;

Figure 2. 116


Part II - Tutorials


Click on the Selfweight button and the following dialog box willappear:

Figure 2. 117

Select the Direction as Y to indicate that the Selfweight will act asin the global Y direction. Enter the Factor as -1 to indicate that theSelfweight will act vertically downwards (negative global Ydirection).

The Selfweight load is now applied to the structure. The Loadsdialog box now shows the Selfweight load just applied:

Figure 2. 118



Load Case 2: Dead Load

Click on the Primary button to define a new Primary Load Case.The Set Active Load Case dialog box appears as shown below:

Figure 2. 119

Enter the Load Case Number as 2 and the Title as Dead Load.Switch to Front view using the appropriate Toolbar icon:

Select the Nodes Cursor option from the Select menu. This allowsyou to select only nodes from the Structure. Using Windowselection, select the nodes as shown below:


Part II - Tutorials


Figure 2. 120

Click on the Node ... button. The Node Loads dialog box appears(Figure 2.121). Select the Node tab and enter the value for Fy as -10. This indicates that the Nodal Load of 10 Kips will act verticallydownward (in the negative global Y direction). Click the Assignbutton to assign the loads.



Figure 2. 121

Switch to Isometric view to visually confirm that the loads havebeen applied to all the appropriate joints.

Figure 2. 122


Part II - Tutorials


Load Case 3: Wind From Left

Create a Primary Load Case with Number as 3 and Title as WindLoad. Follow the same procedure as described in Load Case 2 forthis.

In the Isometric or Side view, use cursor to assign the Wind Loadsas described at the beginning of this section. For all the Loadsunder this Load Case, use the Node ... button from the Loads dialogbox, as the wind loads will be treated as nodal loads. After theloads are assigned, the Loads dialog box should look like thefollowing figure.

Figure 2. 123

Load Case 4: Load Combination

To define a Load Combination, click on the Combine button fromthe Load dialog box (See Figure 2.123). The Define Combinationsdialog box appears. Click on the New button. The New Combinationdialog box appears as shown below (Figure 2.124). Enter a Title forthe Load Combination as shown below.



Figure 2. 124

In the Define Combinations dialog box, enter the Factor under thePrimary Load Cases group as 1.1. Check the Combine Algebraicallycheck box. Highlight the first load case (Selfweight) and click onthe > button (see Figure 2.125). These data indicate that you areadding the Selfweight Load Case with a multiplication factor of 1.1and that the load combination results would be obtained byalgebraic summation of the results for individual load cases.

Figure 2. 125

In a similar manner, add Dead Load (Load Case Number 2) with afactor of 1.4 and Wind Load (Load Case Number 3) with a factor of1.5. At this point, the Define Combinations dialog box should looklike the following figure (Figure 2.126).


Part II - Tutorials


Figure 2. 126

Click OK to complete the Load Combination specification.



3.10 Specifying Analysis Commands

In order to perform Analysis and/or Design in STAAD/Pro, youneed to specify the type of Analysis to be performed. At the sametime, you may specify the post-analysis results which you want toinclude in the Output (.ANL) file. The facilities of the Commandsmenu are used for these purposes.

From the Commands menu, select Analysis and then the PerformAnalysis option. The following dialog box appears:

Figure 2. 127

Figure 2.127 shows optional outputs which may be printed whilethe analysis is performed. Select Statics Check as shown above.

Next, you are going to specify several post-analysis results to beprinted in the Output file as described below

Support Reactions For all supports.Member Forces For the following members (see Figure

2.128):

All columns, Truss, and bottom chordmembers on the 4th portal frame from theorigin (at Z=75 ft).


Part II - Tutorials


All bottom chords at the outermost portalframe (at Z=125 ft).

Figure 2. 128

To include the Support Reactions results in Post Analysis Print,select the Commands menu, Post Analysis Results and then SupportReactions. A dialog box appears for confirmation. Click Yes toconfirm.

For Member Force specifications, you first need to select themembers on the 4th portal frame. You may use the Range optionfrom the Select menu to specify a Z range for selecting all entitiesparallel to the XY plane.First, change the units to Ft-Kips using the Set Current Units optionfrom the Tools menu. Next, select the Range option from the Selectmenu. The following dialog box appears:



Figure 2. 129

Specify the Z range as 74 and 76 feet, as the 4th portal frame lies atZ=75 ft. Note that the desired members have been highlighted. Nowselect the exterior bottom chords by holding down the Control keyand clicking on them. With these members selected, selectCommands - Post Analysis Print - Member Forces option. Thefollowing dialog box appears;

Figure 2. 130

Click on the To Selection button and click OK.


Part II - Tutorials


3.11 Specifying Design Parameters

Now, you need to specify the Design Parameters to perform CodeCheck as per AISC Steel code for two column members on the 4thportal frame. The members are shown highlighted in Figure 2.131.

Figure 2. 131

Select the desired members as shown above. Select the Design |Steel tab from the Page Control area. The Steel Design dialog boxappears as shown in Figure 2.132. Select AISC from the CurrentCode listbox.



Figure 2. 132

Click the Select Parameters button. Clear all Selected Parametersby clicking the << button. Select Beam, Ky, Kz, Track and Unl.Your selection should appear as shown in Figure 2.133. Click OK.


Part II - Tutorials


Figure 2. 133

Now we must define these parameters. Click the DefineParameters button. The Design Parameters dialog box of Figure2.134 appears.

Figure 2. 134

In the Beam tab, select the Beam parameter as 1. This ensures thatthe beam members will be designed for two end points as well aseleven intermediate sections. Click Assign.



In the Ky tab, enter a value of 1.5. Click Assign.

In the Kz tab, enter a value of 1.5. Click Assign.

In the Track tab, select a value of 2.0. The TRACK parametercontrols the extent of details in the design output. Click Assign.

In the Unl tab, enter a value of 16 feet. Click Assign.

When all parameters have been defined, click the Close button.

Now select the Commands button. The dialog box that appears isshown in Figure 2.135. This dialog box offers various designrelated commands. Select the Check Code tab, then click the Assignbutton.

Figure 2. 135


Part II - Tutorials


3.12 Performing Analysis and Design

STAAD/Pro performs Analysis and Design simultaneously. In orderto perform Analysis and Design, select the Run Analysis optionfrom the Analysis menu.

If the structure has not been saved after the last change was made,you should save the structure first by using the Save command fromthe File menu.

When you select the Run Analysis option from the Analysis menu,the following dialog box appears:

Figure 2. 136

You may select STAAD Analysis or STARDYNE AdvancedAnalysis engines. The STARDYNE Analysis is suitable foradvanced problems including Buckling/Post-buckling Analysis,Modal Extraction in different methods, etc. The STAAD DesignCode tab is used to select the Design Code to be used, if you haveinstalled multiple Design Codes.

For the Tutorial problem, you shall use the STAAD Analysis option.Click on this button and press Run Analysis.



Click on the Run Analysis button again to start the Analysis andDesign process. As the Analysis progresses, several messagesappear on screen as shown in Figure 2.137. After the analysis iscomplete, a Done button appears. Click on this button to completethe Analysis and Design.

Figure 2. 137


Part II - Tutorials


3.13 Viewing The Output File

During the analysis process, STAAD/Pro creates an Output file.This file provides important information on whether the analysiswere performed properly. For example, if STAAD/Pro encountersan instability problem during the Statics Check, it will be reportedin the Output file.

In order to view the Output file, select File Pipe View Pipe OutputFile Pipe STAAD Output option from the top menu. TheSTAAD/Pro output file is shown in the next few pages.

The STAAD/Pro Output file is displayed through the STAAD/ProFile Viewer. The viewer allows you to set the text font for theentire file and print the output file to a printer. Use the appropriateFile menu option from the menu bar.

Figure 2. 138

Note: By default, STAAD/Pro echoes the entire Input in the outputfile. Please note that this section of the Output file has beenomitted in this manual.

You may choose not to print the echo of the Input commands in theSTAAD/Pro Output file. Please select Commands PipeMiscellaneous Pipe Set Echo option from the menu bar and selectthe Echo Off button.



************************************************** * * * STAAD/Pro STAAD-III * * Revision 1.5 * * Proprietary Program of * * RESEARCH ENGINEERS, Inc. * * Date= * * Time= * * * * USER ID: Authorized User * **************************************************

1. STAAD SPACE TUTORIAL PROBLEM 2. START JOB INFORMATION 3. ENGINEER DATE 4. END JOB INFORMATION 5. INPUT WIDTH 79 6. UNIT INCHES KIP 7. JOINT COORDINATES 8. 1 0.000 0.000 0.000 9. 2 0.000 192.000 0.000

Rest of the Input related commands are omitted here



***TOTAL APPLIED LOAD ( KIP INCH ) SUMMARY (LOADING 1 ) SUMMATION FORCE-X = 0.00 SUMMATION FORCE-Y = -45.44 SUMMATION FORCE-Z = 0.00

SUMMATION OF MOMENTS AROUND THE ORIGIN- MX= 34079.05 MY= 0.00 MZ= -8178.97

***TOTAL APPLIED LOAD ( KIP INCH ) SUMMARY (LOADING 2 ) SUMMATION FORCE-X = 0.00 SUMMATION FORCE-Y = -300.00 SUMMATION FORCE-Z = 0.00



Part II - Tutorials

Tutorial Problem 2120 ***TOTAL APPLIED LOAD ( KIP INCH ) SUMMARY (LOADING 3 ) SUMMATION FORCE-X = 77.50 SUMMATION FORCE-Y = 0.00 SUMMATION FORCE-Z = 0.00


++ Processing Element Stiffness Matrix. 14:24:56 ++ Processing Global Stiffness Matrix. 14:24:56 ++ Processing Triangular Factorization. 14:24:56 ++ Calculating Joint Displacements. 14:24:56 ++ Calculating Member Forces. 14:24:56

***TOTAL REACTION ( KIP INCH ) SUMMARY

LOADING 1

SUM-X= 0.00 SUM-Y= 45.44 SUM-Z= 0.00

SUMMATION OF MOMENTS AROUND ORIGIN-

MX= -34079.05 MY= -0.03 MZ= 8178.97

LOADING 2

SUM-X= 0.00 SUM-Y= 300.00 SUM-Z= 0.00


MX= -224999.95 MY= -0.07 MZ= 54000.00

LOADING 3

SUM-X= -77.47 SUM-Y= 0.00 SUM-Z= 0.00


MX= -3.84 MY= -58085.68 MZ= 16680.00



Tutorial Problem 2 121 SUPPORT REACTIONS -UNIT KIP FEET STRUCTURE TYPE = SPACE

JOINT LOAD FORCE-X FORCE-Y FORCE-Z MOM-X MOM-Y MOM Z

1 1 0.00 1.99 0.03 0.00 0.00 0.00 2 0.00 25.00 0.01 0.00 0.00 0.00 3 -12.56 -7.51 0.04 0.00 0.00 0.00 4 -18.84 25.93 0.10 0.00 0.00 0.00 12 1 0.00 2.93 0.00 0.00 0.00 0.00 2 0.00 25.00 0.01 0.00 0.00 0.00 3 -12.97 -7.72 0.02 0.00 0.00 0.00 4 -19.46 26.65 0.04 0.00 0.00 0.00 23 1 0.00 6.44 0.30 0.00 0.00 0.00 2 0.00 25.00 0.72 0.00 0.00 0.00 3 -13.21 -7.95 -1.68 0.00 0.00 0.00 4 -19.82 30.16 -1.18 0.00 0.00 0.00 34 1 0.00 6.44 -0.30 0.00 0.00 0.00 2 0.00 25.00 -0.72 0.00 0.00 0.00 3 -13.20 -7.93 1.68 0.00 0.00 0.00 4 -19.80 30.18 1.18 0.00 0.00 0.00 45 1 0.00 2.93 0.00 0.00 0.00 0.00 2 0.00 25.00 -0.01 0.00 0.00 0.00 3 -12.97 -7.72 -0.02 0.00 0.00 0.00 4 -19.46 26.65 -0.04 0.00 0.00 0.00 56 1 0.00 1.99 -0.03 0.00 0.00 0.00 2 0.00 25.00 -0.01 0.00 0.00 0.00 3 -12.54 -7.50 -0.04 0.00 0.00 0.00 4 -18.82 25.93 -0.10 0.00 0.00 0.00 5 1 0.00 1.99 0.03 0.00 0.00 0.00 2 0.00 25.00 0.01 0.00 0.00 0.00 3 0.00 7.52 -0.04 0.00 0.00 0.00 4 0.00 48.46 -0.01 0.00 0.00 0.00 16 1 0.00 2.93 0.00 0.00 0.00 0.00 2 0.00 25.00 0.01 0.00 0.00 0.00 3 0.00 7.71 -0.02 0.00 0.00 0.00 4 0.00 49.80 -0.03 0.00 0.00 0.00 27 1 0.00 6.44 0.30 0.00 0.00 0.00 2 0.00 25.00 0.72 0.00 0.00 0.00 3 0.00 7.94 1.72 0.00 0.00 0.00 4 0.00 53.98 3.92 0.00 0.00 0.00 38 1 0.00 6.44 -0.30 0.00 0.00 0.00 2 0.00 25.00 -0.72 0.00 0.00 0.00 3 0.00 7.94 -1.72 0.00 0.00 0.00 4 0.00 53.98 -3.92 0.00 0.00 0.00 49 1 0.00 2.93 0.00 0.00 0.00 0.00 2 0.00 25.00 -0.01 0.00 0.00 0.00 3 0.00 7.71 0.02 0.00 0.00 0.00 4 0.00 49.80 0.03 0.00 0.00 0.00 60 1 0.00 1.99 -0.03 0.00 0.00 0.00 2 0.00 25.00 -0.01 0.00 0.00 0.00 3 0.00 7.52 0.04 0.00 0.00 0.00 4 0.00 48.46 0.01 0.00 0.00 0.00


Part II - Tutorials


MEMBER END FORCES STRUCTURE TYPE = SPACE

ALL UNITS ARE -- KIP FEET

MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z

80 1 34 5.53 0.00 -0.25 0.00 1.02 0.00 43 -4.98 0.00 0.25 0.00 1.00 0.00 2 34 24.75 0.00 -0.04 0.00 0.20 0.00 43 -24.75 0.00 0.04 0.00 0.15 0.00 3 34 -7.39 13.17 -0.01 0.00 0.04 -0.01 43 7.39 -13.17 0.01 0.00 0.06 105.42 4 34 29.64 19.76 -0.36 0.00 1.48 -0.01 43 -29.04 -19.76 0.36 0.00 1.41 158.13

81 1 35 1.99 0.01 0.00 0.00 0.01 -0.01 39 -1.97 0.02 0.00 0.00 0.00 -0.03 2 35 53.08 0.02 0.00 0.00 0.00 0.03 39 -53.08 -0.02 0.00 0.00 0.00 0.11 3 35 38.32 -10.81 0.25 0.00 -0.72 -72.54 39 -38.32 10.81 -0.25 0.00 -1.39 -19.34 4 35 133.97 -16.18 0.37 0.00 -1.07 -108.78 39 -133.95 16.21 -0.37 0.00 -2.08 -28.90

82 1 36 1.69 0.01 0.00 0.00 0.00 0.02 41 -1.71 0.02 0.00 0.00 0.00 -0.03 2 36 46.32 0.02 0.00 0.00 0.00 0.05 41 -46.32 -0.02 0.00 0.00 0.00 0.11 3 36 15.34 -0.83 0.14 0.00 -0.12 -5.27 41 -15.34 0.83 -0.14 0.00 -1.09 -1.81 4 36 89.72 -1.21 0.21 0.00 -0.18 -7.81 41 -89.74 1.24 -0.21 0.00 -1.64 -2.60

83 1 37 2.22 0.00 0.22 0.00 -0.89 0.00 44 -2.77 0.00 -0.22 0.00 -0.90 0.00 2 37 24.90 0.00 -0.04 0.00 0.18 0.00 44 -24.90 0.00 0.04 0.00 0.12 0.00 3 37 8.74 0.06 0.06 0.00 -0.23 0.22 44 -8.74 -0.06 -0.06 0.00 -0.28 0.26 4 37 50.40 0.09 0.29 0.01 -1.07 0.33 44 -51.00 -0.09 -0.29 -0.01 -1.24 0.38

85 1 39 1.71 0.02 0.00 0.00 0.00 0.03 36 -1.69 0.01 0.00 0.00 0.00 -0.02 2 39 46.32 -0.02 0.00 0.00 0.00 -0.11 36 -46.32 0.02 0.00 0.00 0.00 -0.05 3 39 37.59 2.89 0.14 0.00 -1.10 19.33 36 -37.59 -2.89 -0.14 0.00 -0.12 5.27 4 39 123.12 4.33 0.21 0.00 -1.64 28.87 36 -123.10 -4.30 -0.21 0.00 -0.18 7.81






89 1 41 1.97 0.02 0.00 0.00 0.00 0.03 37 -1.99 0.01 0.00 0.00 -0.01 0.01 2 41 53.08 -0.02 0.00 0.00 0.00 -0.11 37 -53.08 0.02 0.00 0.00 0.00 -0.03 3 41 15.43 0.46 0.26 0.00 -1.42 1.81 37 -15.43 -0.46 -0.26 0.00 -0.77 2.06 4 41 99.62 0.68 0.39 0.00 -2.13 2.60 37 -99.64 -0.65 -0.39 0.00 -1.16 3.07

93 1 43 2.77 0.00 -0.22 0.00 0.90 0.00 35 -2.22 0.00 0.22 0.00 0.89 0.00 2 43 24.90 0.00 0.04 0.00 -0.12 0.00 35 -24.90 0.00 -0.04 0.00 -0.18 0.00 3 43 -8.71 13.20 0.06 0.00 -0.27 -105.55 35 8.71 -13.20 -0.06 0.00 -0.22 211.10 4 43 24.84 19.79 -0.10 0.01 0.42 -158.32 35 -24.24 -19.79 0.10 -0.01 0.40 316.64

94 1 44 4.98 0.00 0.25 0.00 -1.00 0.00 38 -5.53 0.00 -0.25 0.00 -1.02 0.00 2 44 24.75 0.00 0.04 0.00 -0.15 0.00 38 -24.75 0.00 -0.04 0.00 -0.20 0.00 3 44 7.38 -0.03 -0.01 0.01 0.07 -0.21 38 -7.38 0.03 0.01 -0.01 0.05 0.16 4 44 51.20 -0.04 0.32 0.01 -1.21 -0.32 38 -51.80 0.04 -0.32 -0.01 -1.35 0.24

136 1 57 -0.92 0.03 0.00 0.00 -0.02 0.01 62 0.92 0.04 0.00 0.00 -0.01 -0.06 2 57 -46.82 0.01 0.00 0.00 0.00 -0.03 62 46.82 -0.01 0.00 0.00 0.00 0.12 3 57 -44.19 -15.62 0.97 0.00 -4.37 -131.97 62 44.19 15.62 -0.97 0.00 -6.29 -39.83 4 57 -132.86 -23.38 1.46 0.00 -6.58 -198.00 62 132.86 23.46 -1.46 0.00 -9.44 -59.64

138 1 62 -0.61 0.03 0.00 0.00 0.00 0.06 64 0.61 0.03 0.00 0.00 0.00 -0.06 2 62 -32.49 0.00 0.00 0.00 0.00 -0.12 64 32.49 0.00 0.00 0.00 0.00 0.12 3 62 -17.29 6.09 2.71 0.00 -10.84 39.85 64 17.29 -6.09 -2.71 0.00 -10.81 8.89 4 62 -72.09 9.17 4.06 0.00 -16.26 59.67 64 72.09 -9.11 -4.06 0.00 -16.21 13.44


Part II - Tutorials





142 1 64 -0.92 0.04 0.00 0.00 0.01 0.06 59 0.92 0.03 0.00 0.00 0.02 -0.01

2 64 -46.82 -0.01 0.00 0.00 0.00 -0.12 59 46.82 0.01 0.00 0.00 0.00 0.03 3 64 -13.72 -0.97 1.00 0.00 -6.38 -8.89 59 13.72 0.97 -1.00 0.00 -4.64 -1.78 4 64 -87.14 -1.42 1.50 0.00 -9.56 -13.44 59 87.14 1.50 -1.50 0.00 -6.94 -2.64



Tutorial Problem 2 125 STAAD-III CODE CHECKING - (AISC) *********************** |--------------------------------------------------------------------------| | Y PROPERTIES | |************* | IN INCH UNIT | | * |=============================| ===|=== ------------ | |MEMBER 83 * | | | AX = 20.10 | | * | ST W24 X68 | | --Z AY = 9.85 | |DESIGN CODE * | | | AZ = 6.99 | | AISC-1989 * =============================== ===|=== SY = 15.71 | | * SZ = 154.24 | | * |<---LENGTH (FT)= 8.00 --->| RY = 1.87 | |************* RZ = 9.54 | | | | 0.4 (KIP-FEET) | |PARAMETER | L4 STRESSES | |IN KIP INCH |L4 IN KIP INCH | |--------------- + L4 -------------| | KL/R-Y= 76.94 | L4 L4 FA = 15.69 | | KL/R-Z= 15.09 + L4 fa = 2.54 | | UNL = 192.00 | L4 FCZ = 17.86 | | CB = 1.00 + L4 L4 FTZ = 21.60 | | CMY = 0.85 | L4 FCY = 27.00 | | CMZ = 0.85 + FTY = 27.00 | | FYLD = 36.00 | L4 fbz = 0.03 | | NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.95 | | DFF = 0.00 0.0 FV = 14.40 | | dff = 0.00 ABSOLUTE MZ ENVELOPE Fey = 25.22 | | (WITH LOAD NO.) Fez = 655.66 | | | | MAX FORCE/ MOMENT SUMMARY (KIP-FEET) | | ------------------------- | | | | AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z | | | | VALUE 51.0 0.1 0.3 1.2 0.4 | | LOCATION 8.0 0.0 0.0 8.0 8.0 | | LOADING 4 4 4 4 4 | | | |**************************************************************************| |* *| |* DESIGN SUMMARY (KIP-FEET) *| |* -------------- *| |* *| |* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *| | FX MY MZ LOCATION | | ====================================================== | | PASS AISC- H1-1 0.196 4 | | 51.00 C 1.24 -0.38 8.00 | |* *| |**************************************************************************| | | |--------------------------------------------------------------------------|


Part II - Tutorials


STAAD-III CODE CHECKING - (AISC) ***********************

|--------------------------------------------------------------------------| | Y PROPERTIES | |************* | IN INCH UNIT | | * |=============================| ===|=== ------------ | |MEMBER 93 * | | | AX = 20.10 | | * | ST W24 X68 | | --Z AY = 9.85 | |DESIGN CODE * | | | AZ = 6.99 | | AISC-1989 * =============================== ===|=== SY = 15.71 | | * SZ = 154.24 | | * |<---LENGTH (FT)= 8.00 --->| RY = 1.87 | |************* RZ = 9.54 | | | | 316.6 (KIP-FEET) | |PARAMETER | L4 STRESSES | |IN KIP INCH | L4 L4 IN KIP INCH | |--------------- + L4 -------------| | KL/R-Y= 76.94 | L4 FA = 15.69 | | KL/R-Z= 15.09 + L4 fa = 1.21 | | UNL = 192.00 | L4 FCZ = 17.86 | | CB = 1.00 + FTZ = 21.60 | | CMY = 0.85 | L4 L4 FCY = 27.00 | | CMZ = 0.85 + L4 FTY = 27.00 | | FYLD = 36.00 |L4 fbz = 24.64 | | NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.31 | | DFF = 0.00 149.5 FV = 14.40 | | dff = 0.00 ABSOLUTE MZ ENVELOPE Fey = 25.22 | | (WITH LOAD NO.) Fez = 655.66 | | | | MAX FORCE/ MOMENT SUMMARY (KIP-FEET) | | ------------------------- | | | | AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z | | | | VALUE 24.9 19.8 0.2 0.9 316.6 | | LOCATION 0.0 0.0 0.0 0.0 8.0 | | LOADING 2 4 1 1 4 | | | |**************************************************************************| |* *| |* DESIGN SUMMARY (KIP-FEET) *| |* -------------- *| |* *| |* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *| | FX MY MZ LOCATION | | ====================================================== | | FAIL AISC- H1-3 1.468 4 | | 24.24 C -0.40 -316.64 8.00 | |* *| |**************************************************************************| | | |--------------------------------------------------------------------------| *************** END OF STAAD-III ***************



From the .ANL file, you can see that member 93 (the columnfacing the wind) has failed in bending, even though a large wideflange cross-section (W24x68) was assigned to all columns.

The reason of this failure may be attributed to the large span of theportal frames and the large unsupported length of the column. Tocorrect this problem you may add K bracings connecting thecolumns to the bottom chords of the portal frames. However, this isleft as an exercise for you.


Part II - Tutorials


3.14 Verifying and Viewing Results Graphically

STAAD/Pro offers extensive result verification and visualizationfacilities. These facilities are accessed from the Post ProcessingMode. For the tutorial problem, you shall verify the followingresults:

Bending Momentdiagram about local Zaxis

For all members on the 4thPortal frame from origin (atZ=75 feet).

Displacement diagram For the above members.

The results shall be verified graphically as well as numerically.

You shall also Take Picture of the graphical results in order toinclude them in a custom report, as explained in the next section.

Select the Post Processing option from the Modes menu to accessthe Post Processing Mode. For the first time when you access thisMode after opening the structure file, a Results Setup dialog boxappears:

Figure 2. 139



This dialog box allows you to select the Load Cases, Mode Shapenumbers, and the structural elements to be included in the resultstables. For the Tutorial problem, in the Load tab, highlight theLoad Case number 4 (Load Combination) and click on the > button.Click OK to proceed.

Note that the Page tabs have changed in the left side of the screen.To view the Bending results, click on the Beam | Forces Page. Thescreen will look like the following:

Figure 2. 140

The Main Window area of the screen displays the Bending Momentdiagram superimposed on the members for Load Case 4.

Note: In order to view other force diagrams, such as Shear Forcediagram, select the menu option View | Customize View | Resultstab and select the type of force to view.

In the Data Area of the screen, a Support Reactions table and aBeam End Forces table appear.


Part II - Tutorials


The All tab of the Support Reactions table displays the reactions forall supports in all six DOFs for each selected Load Case. Forexplanation of other tabs, please refer to the GraphicalEnvironment manual.

The All tab of the Beam End Forces table displays the forces andmoments at the end nodes of each beam for each selected LoadCase. For explanation of other tabs, please refer to the GraphicalEnvironment manual.

Displaying results for all members simultaneously makes it difficultto view the results for the required members. In order to get acleaner diagram, you shall now create a new view window with theselected members and verify the graphical results using the newview window.

To select all members on the 4th Portal Frame from the origin (atZ=75ft), select the Range option from the Select menu. This optionallows you to select all members lying between two imaginaryplanes (called Clipping Planes). The Clipping Planes must beparallel to one of the orthogonal planes (XY, YZ, or XZ).Accordingly, select the XY option from the Range sub-menu, as theportal frame of choice lies parallel to the XY plane.

Now the following dialog box appears where you have to specifythe distances of the Clipping Planes from the origin (see Figure2.141).

Figure 2. 141

As the 4th Portal Frame lies at a distance of Z=75 feet from theorigin, specify the Z Minimum as 74 feet and Z Maximum as 76feet. Note that all relevant members are highlighted. To create a



new view with the selected members, use the New View... optionfrom the View menu. In the following dialog box, specify that a newWindow should be created with the selected members (see Figure2.142), and click OK.

Figure 2. 142

A new view window appears on the screen with the selectedmembers as shown below:

Figure 2. 143


Part II - Tutorials


You may now save this view with a name. From the View menu, useView Management | Save View option and save the view as 4thPortal. See Figure 2.144.

Figure 2. 144

In the 4th Portal view, right click on any blank area of the screenand select labels from the pop-up menu. Turn on the Beam andNode Labels by checking the appropriate check boxes. The viewWindow now looks like Figure 2.145.



Figure 2. 145

To turn on the display of the Bending Moment values, select themenu option Results | View Value.


Part II - Tutorials


Figure 2. 146

In the Ranges tab, select All to display values for all members.Select the Beam Results tab. Check the Maximum box under theBending group. This option will display only the maximum bendingmoment values.

Figure 2. 147



Click the Annotate button and then click Close. The 4th Portalwindow now looks like Figure 2.148.

Figure 2. 148

In case the displayed BMD values are too small and you want toincrease the size, you may use the menu option View | Options.Select the Annotation tab (see Figure 2.149). Click on the Fontbutton to set the font style, size, and color for the annotated texts.


Part II - Tutorials


Figure 2. 149

You may now use the Take Picture icon from the toolbar to take apicture of the graphics screen for including it in anyreport. Enter a caption for the picture as shownbelow:

Figure 2. 150

To view the Nodal Displacement results, click on the Displacementtab. The displacement diagram of the whole structure is displayedin the Main Window area. In the data area, the Node Displacementstable and the Beam Relative Displacement Details table aredisplayed.



You may need to adjust the scale of plotting of the displacements.To do this, select the View | Customize View | Scales tab andmodify the Displacement scale factor as needed.

Figure 2. 151

The Main Window now shows the displacement diagram as shownin Figure 2.152.


Part II - Tutorials


Figure 2. 152

Capture this diagram using the Take Picture icon and enter aCaption as shown below:

Figure 2. 153

The Node Displacements table as shown below displays the nodaldisplacements of all (or selected) nodes in all six DOFs. For anexplanation of the Summary tab, please refer to the GraphicalEnvironment manual.



Figure 2. 154

The Beam Relative Displacement Details table (Figure 2.155)displays the displacements of the members at end nodes as well assection displacements at intermediate points. The members aredivided into a specified number of equal parts. For explanation ofthe Max Displacements tab, please refer to the GraphicalEnvironment manual.


Part II - Tutorials


Figure 2. 155



3.15 Creating Customized Reports

STAAD/Pro offers extensive report generation facilities. You mayselect the modeling data as well as the post-analysis result data tobe included in the report. The results may be printed for selectedLoad Cases, selected Mode Shapes, and selected structuralelements. You may include any "snapshot" or picture of the screen,taken using the Take Picture toolbar icon. Other customizableparameters include the font size, title block, headers, footers, etc.

The Report Setup utility may be accessed using theReports Page or the Report Setup toolbar icon. In bothcases the following dialog box appears:

Figure 2. 156

Different tabs of this dialog box offers different options. The Itemstab lists all available data which may be included in the report.Note that the items under the Selected list are the ones which havebeen selected by default.


Part II - Tutorials


Available items are classified into four categories: Input, Output,Pictures and Reports. In our report, we want to show JobInformation, Node Displacement Summary, Beam Max Moments,Picture 1 and Picture 2.

Job Information is already selected by default.

From the Available listbox, select Output. From the availableoutput items, select Node Displacement Summary and Beam MaxMoments.

Then select Pictures from the Available listbox and select Picture 1and Picture 2.

When all items have been selected, the Report Setup dialog boxshould appear as shown in Figure 2.157.

Figure 2. 157

The Report Detail Increments check box at the bottom indicates thenumber of segments into which a member would be divided forprinting sectional displacements, forces, etc.

Click on the Load Cases tab to select the Load Cases to be includedin the report. Click on the >> button to include all Load Cases. TheGrouping buttons indicate whether the report data will be grouped



by Node/Beam numbers or by Load Case number. In the first case,all Load Case results will appear under a particular Node or Beam.In the second case, results for all Nodes or Beam for a particularLoad Case will appear together.

Figure 2. 158

Click on the Picture Album tab to visually identify the picturestaken earlier. Figure 2.159 displays the Picture 1 as stored by theprogram.

Figure 2. 159


Part II - Tutorials


The Options tab lets you include Header, Footer, Page Numbers,Table Grids, fonts for Column Heading and Table data, etc. asshown below:

Figure 2. 160

The Name and Logo tab allows you to enter the Company Name andLogo. Click on the blank area and type the name and address of thecompany. Click on the Font button in the Text group and adjust thefont to be Arial 12 Pt Bold. Click on the Right radio button in theAlignment group under Text to right-align the company name.



Figure 2. 161

Click OK to finish or click Print to print the report. However, it isalways a good idea to first preview the report before printing it.

To preview the report just created, select the PrintPreview icon from the Toolbar. The first two and the lasttwo pages of the report are shown in subsequent Figures2.162 through 2.165.

The buttons on the top of the Print Preview screen are explainedbelow:

Print Print the report (or part of it)Next Page/Prev Page View the next page or the previous page of

the reportTwo Page/One Page View two pages or one page at a time on

screen.Zoom In/Zoom Out Self explanatoryClose Close the preview window


Part II - Tutorials


Figure 2. 162



Figure 2. 163


Part II - Tutorials


Figure 2. 164



Figure 2. 165


Part II - Tutorials


3.16 The STAAD/Pro Command File

The STAAD/Pro Command File (also called the Input file) providesan alternative way to specify the Input data, Analysis/DesignCommands, and post-analysis outputs. The Command File is a Textfile which contains simple English Language commands. You maychoose to use the Graphical User Interface, the Command File, ormix and match both facilities.

The Command File and the facilities to access the Command Fileare explained in details in Chapter 3. The following portion of thissection explains the Command File generated for the Tutorialproblem 1. Please note that the Command File created in your casemay be slightly different from what is described next.

The lines shown in bold below indicate the commands in theCommand File. The commands may be typed in upper or lower caseletters. Usually the first three letters of a keyword are all that areneeded – the rest of the letters of the word are not required. Therequired letters are underlined. (“PLANE” = “PLA” = “plane” =“pla”)

STAAD SPACE TUTORIAL PROBLEM

Every Command File has to begin with the word STAAD . The wordSPACE signifies that the structure is a space structure. Theremainder of the words are the title of the problem, which isoptional.

Note : An asterisk in the first column signifies that the line is acomment line and should not be executed. For example, one couldhave put the optional title above on a separate line as follows.

* TUTORIAL FACTORY SPACE FRAME PROBLEM

UNIT KIP FEET



Specify the force and length units for the commands to follow.

JOINT COORDINATES1 0. 0. 0.; 2 0. 16. 0. ; 3 15. 24. 0. ; 4 30. 16. 0.5 30. 0. 0.; 6 7.5 20. 0. ; 7 11. 16. 0. ; 8 22.5 20. 0.(Rest of the Joint coordinates follows)

Joint numbers and their corresponding global X, Y, and Zcoordinates are provided above. Note that if the structure is a planeframe, the Z coordinate would not be required. Semicolons (;) areused as line separators. In other words, data which is normally puton multiple lines can be put on one line by separating them with asemicolon.

Note: You may also use the Repeat command in the STAAD/ProCommand File to create repetitive portion of the Factory structure.However, this command may generate a different set of Nodecoordinates and Member incidences.

MEMBER INCIDENCE1 1 10 ; 2 2 6 ; 3 3 84 4 11 ; 5 2 7 ; 6 6 3(Rest of the Member Incidences follows)

The members are defined by the joints to which they are connected.

MEMBER PROPERTY AMERICAN1 4 14 TO 16 20 27 30 40 TO 43 54 57 67 68 80 83 93 94-106 109 119 120 132 135 145 TO 150 TABLE ST W24X68

5 7 11 31 33 37 58 60 64 84 86 90 110 112 116 136 138 -142 TABLE LD L20204 SP 1.5

17 19 25 26 44 46 52 53 70 72 78 79 96 98 104 105 122 -124 130 131 TABLE ST C10X15

21 TO 24 48 TO 51 74 TO 77 100 TO 103 126 TO -129 TABLE T W10X30

18 45 71 97 123 TABLE ST PIPS10(Rest of the Member Properties follows)


Part II - Tutorials


Specify the member properties for the appropriate set of members.A range of members may specified by using the TO keyword.Section 5.20 of the Technical Reference Manual provides detailedinformation on member property specifications. Please note that the"-" character at the end a line indicates that the command incontinued in the next line.

UNIT INCHESCONSTANTSE 29000 ALL(Rest of the Member Constants follows)

The length unit is changed to INCHES to facilitate input of themodulus of elasticity (E). Material properties such as E, density,Poisson’s ratio, coefficient of thermal expansion (ALPHA) etc. areprovided following the CONSTANT command. See Section 5.26 ofthe Technical Reference Manual for more information.

SUPPORT1 12 23 34 45 56 PINNED5 16 27 38 49 60 FIXED BUT FX MX MY MZ

Pinned supports (fixed for translations, released for rotations) arelocated at joints 1, 12, 23, 34, 45, 56. Roller supports with releasesin linear X and rotational X, Y, and Z are located at joints 5, 16,27, 38, 49, and 60. More information on the support specification isavailable in Section 5.27 of the Technical Reference Manual.

MEMBER TRUSS8 9 12 13 34 35 38 39 61 62 65 66 87 88 91 92 113 -114 117 118 139 140 143 144

The above members are specified as Truss members.

LOAD 1 SELFWEIGHTSELFWEIGHT Y -1

The above commands identify a loading condition. The wordSELFWEIGHT after LOAD 1 is an optional title to identify thisload case. The next line specifies that the self-weight of every



member be applied as a Uniformly Distributed Load acting in thenegative global Y direction. The Member Load specification isexplained in detail in Section 5.32 of the Technical ReferenceManual.

LOAD 2 DEAD LOADJOINT LOA D3 6 TO 9 14 17 TO 20 25 28 TO 31 36 39 TO 42 47 -50 TO 53 58 61 TO 64 FY -10

The above commands identify a second load case. This load is aJOINT LOAD. A 10 kip force is acting at joint 2 in the -ve globalY direction on the specified nodes.

LOAD 3 WIND LOADJOINT LOA D13 24 35 46 FX 102 57 FX 517 28 39 50 FX 3.56 61 FX 1.7514 25 36 47 FX 23 58 FX 1

The above commands identify a third load case. This load is aJOINT LOAD caused by wind in +ve global X direction. The windcauses different joints to experience different load values.

LOAD COM B 4 LOAD COMBINATION1 1.1 2 1.4 3 1.5

This command identifies a combination load with an optional title.The second line provides the primary load cases and their factorsused for the load combination.

PERFORM ANALYSIS PRINT STATICS CHECK

This command makes the program proceed with the analysis. AStatics check is performed simultaneously. Section 5.37 of theTechnical Reference Manual offers information on the variousanalysis options available.


Part II - Tutorials

Tutorial Problem 2154PRINT SUPPORT REACTIONPRINT MEMBER FORCES LIST 80 TO 83 -85 89 93 94 136 138 142

The above print commands are self-explanatory. The member forcesare in the member local axes while support reactions are in theglobal axes. The member forces are printed for the specifiedmembers only.

UNIT KIP FEET

The unit is changed to facilitate Design parameter specification.

PARAMETERCODE AISCKY 1.5 MEMB 83 93KZ 1.5 MEMB 83 93UNL 16 MEMB 83 93BEAM 1 MEM B 83 93TRACK 2 MEM B 83 93CHECK CODE MEMB 83 93

The above set of commands is used to initiate the steel designprocess for members 83 and 93. The command PARAMETERS isfollowed by the various steel design parameters. Specifications ofthe AISC ASD CODE are to be followed. The specified membershave 16 ft unsupported length for the compression flange (UNL).UNL is used to compute the allowable compressive stress inbending. The BEAM parameter signifies that the forces at a total of13 points (including the start and end points) along the length ofthe member have to be checked during the design. The TRACKparameter controls the level of description of the output, 2.0 beingthe most detailed. The CHECK CODE command asks the programto check whether the sections assigned for members 83 and 93 aresafe as per the AISC Code.

FINISH

A STAAD run is terminated using the FINISH command. Thiscommand may be placed anywhere in the input file to end



processing of the file. You will find that this is particularly usefulwhile troubleshooting for input data errors.


Part II - Tutorials



PART–III

APPLICATION EXAMPLES


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Read This First

This example manual is designed in such a way that a user will beable to find an appropriate example to represent his/her real lifeproblem. All the input needed is explained line by line to facilitatethe understanding of the STAAD/Pro command language.

Although a user can prepare input through the STAAD/ProGraphical User Interface (GUI), it is extremely useful tounderstand the language of the input for the following reasons:

1) STAAD/Pro is a very large and comprehensive structuralengineering software. Knowledge of the STAAD/Pro languagecan be very useful in utilizing the enormous facilities availablein the program.

The Graphical User Interface can be used to generate the inputfile for even the most complex of structures. However, with theknowledge of the command language and syntax of the inputdata, the user can alter the input file with ease.

2) The input file represents the user's thought about what he/shewants to analyze or design. With the knowledge of theSTAAD/Pro command language, the user or any other personcan verify the accuracy of the work.

All the commands are explained in Section 5 of the STAAD/ProTechnical Reference Manual. Users are urged to refer to thatmanual for a better understanding of the language.

In addition to the examples provided in this manual, STAAD/Prodocumentation also includes an extensive Verification Manual.


Description of Example Problems

1) Example problem No. 1 - Plane frame with steel design. Afterone analysis, member selection is requested. Since the membersizes change during the member selection, another analysis isdone which is followed by final code checking to verify thatthe final sizes meet the code requirements based on the latestanalysis results.

2) Example problem No. 2 - A floor structure (bound by globalX-Z axis) made up of steel beams is subjected to area load (i.e.load/area of floor). Forces at intermediate section points (i.e.forces/moments at points between the incident joints) areobtained and are used in the steel design.

3) Example problem No. 3 - A portal frame type steel structure issitting on a concrete footing. The soil is to be considered as anelastic foundation.

4) Example problem No. 4 - This example is a typical case of aload-dependent structure where the structural conditionchanges for different load cases. In this example, differentbracing members are made inactive for different load cases.This is done to prevent these members from carrying anycompressive forces.

5) Example problem No. 5 - This example demonstrates theapplication of support displacement load (commonly known assinking support) on a space frame structure.

6) Example problem No. 6 - An example of prestress load in aplane frame structure. The example also covers the effect of theprestress load during the application of the load (known in theprogram as PRESTRESS load) and the effect after the load isapplied (known in the program as POSTSTRESS load).

7) Example problem No. 7 - This example illustrates modellingof structures with OFFSET connections. Offset connectionsarise when the center lines of the connected members do notintersect at the connection point. The connection eccentricity ismodeled through specification of MEMBER OFFSETS.


8) Example problem No. 8 - Concrete design is performed onsome members of a space frame structure. Design includescomputation of reinforcement for beams and columns.Secondary moments on the columns are obtained through themeans of a P-Delta analysis.

9) Example problem No. 9 - A space frame structure in thisexample consists of frame members and finite elements. Thefinite element part is used to model floor flat plates and a shearwall. Design of an element is performed.

10) Example problem No. 10 - A tank structure is modeled withfour-noded plate elements. Water pressure from inside is usedas loading for the tank. Reinforcement calculations have beendone for some elements.

11) Example problem No. 11 - Dynamic analysis (ResponseSpectrum) is performed for a steel structure. Results of a staticand dynamic analysis are combined. The combined results arethen used for steel design.

12) Example problem No. 12 - Moving load is applied on a bridgedeck. This type of loading creates enormous number of loadcases resulting in plenty of output to be sorted. To avoidlooking into a lot of output, the maximum force envelope isrequested for a few specific members.

13) Example problem No. 13 - Calculation of displacements atintermediate points of members of a plane frame isdemonstrated in this example.

14) Example problem No. 14 - A space frame is analysed as perthe current UBC Code. Combination load cases are used tocombine the lateral and vertical effects.

15) Example problem No. 15 - A space frame is analyzed forloads generated using the built-in wind and floor loadgeneration facilities.

16) Example problem No. 16 - Dynamic Analysis (Time History)is performed for a 3 span beam with concentrated anddistributed masses. The structure is subjected to "forcingfunction" and "ground motion" loading. The maxima of the


joint displacements, member end forces and support reactionsare determined.

17) Example problem No. 17 - The usage of User Provided SteelTables is illustrated in this example for the analysis and designof a plane frame.

18) Example problem No. 18 - This is an example whichdemonstrates the calculation of principal stresses on a finiteelement.

19) Example problem No. 19 - The MESH GENERATION facilityis utilized in this example to model a space frame consisting ofa slab supported on four columns.

20) Example problem No. 20 - This example generates thegeometry of a cylindrical tank structure using the cylindricalcoordinate system.

21) Example problem No. 21 - This example illustrates themodeling of tension-only members using the MEMBERTENSION command.

22) Example problem No. 22 - A space frame structure issubjected to a sinusoidal loading. The commands necessary todescribe the sine function are demonstrated in this example.Time History analysis is performed on this model.

23) Example problem No. 23 - This example illustrates the usageof commands necessary to automatically generate springsupports for a slab on grade. The slab is subjected to pressureloading. Analysis of the structure is performed.

24) Example problem No. 24 - The structure in this exampleconsists of "SOLID" finite elements.This input file containscommands for specifying solid elements.Analysis is performedon this structure.

25) Example problem No. 25 - This example demonstrates theusage of compression-only members. Since the structuralcondition is load dependent, the PERFORM ANALYSIScommand is specified twice, once for each primary load case.


Table of Contents

Example Problem No. 1 1

















Example Problem 1 1

Example Problem No. 1

Plane frame with steel design. After one analysis, member selectionis requested. Since the member sizes change during the memberselection, another analysis is done which is followed by final codechecking to verify that the final sizes meet the codal requirementsbased on the latest analysis results.

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Part III - Application Examples

Example Problem 12

Actual inputs are shown in bold lettering followed by explanation.

STAAD PLANE EXAMPLE PROBLEM NO. 1

Every input has to start with the word STAAD. The word PLANEsignifies that the structure is a plane frame structure and thegeometry is defined through X and Y axes.

UNIT FT KIP

Specifies the unit to be used.

JOINT COORDINATES1 0. 0. ; 2 30 0 ; 3 0 20 0 6 30 20 07 0 35 ; 8 30 35 ; 9 7.5 35 ; 10 22.5 35.11 15 35 ; 12 5. 38. ; 13 25 3814 10 41 ; 15 20 41 ; 16 15 44

Joint number followed by X, Y and Z coordinates are providedabove. Note that, since this is a plane structure, the Z coordinatesneed not be provided. Semicolon signs (;) are used as lineseparators, that is, multiple data can be input in one line. Note thatjoints between 3 and 6 (i.e. 4, 5) are generated in first line of input(see Users' Manual for input description).

MEMBER INCIDENCE1 1 3 ; 2 3 7 ; 3 2 6 ; 4 6 8 ; 5 3 46 4 5 ; 7 5 6 ; 8 7 12 ; 9 12 1410 14 16 ; 11 15 16 ; 12 13 15 ; 13 8 1314 9 12 ; 15 9 14 ; 16 11 14 ; 17 11 1518 10 15 ; 19 10 13 ; 20 7 921 9 11 ; 22 10 11 ; 23 8 10

Defines the members by the joints they are connected to.

MEMBER PROPERTY1 3 4 TABLE ST W14X90 ; 2 TA ST W10X495 6 7 TA ST W21X50 ; 8 TO 13 TA ST W18X3514 TO 23 TA ST L40404

All member properties are from the AISC steel table. The word STstands for standard single section.


Example Problem 1 3

MEMB TRUSS14 TO 23

Above command defines that members 14 through 23 are of typetruss. This means that these members can carry only axialtension/compression and no moments.

MEMB RELEASE5 START MZ

Member 5 has local moment-z (MZ) released at the start joint. Thismeans that the member cannot carry any moment-z (i.e. strong axismoment).

UNIT INCHCONSTANTSE 29000. ALLDEN 0.000283 ALLBETA 90.0 MEMB 3 4UNIT FT

CONSTANT command initiates input for material constants like E(modulus of elasticity) etc. Length unit is changed from FT toINCH to facilitate the input for E etc. Members 3 and 4 are rotatedby 90 degrees around their own axis. See Section 2 of Users'Manual for the definition of the BETA angle.


Joint 1 is a fixed support while joint 2 is pinned meaning nomoments will be carried by the support at joint 2.

DRAW JOINT MEMBER SUPPORT

The above command will generate a drawing of the structure aspart of the output. Joint/Member numbers and supports will bedisplayed.

PRINT MEMBER INFORMATION LIST 1 5 14PRINT MEMBER PROPERTY LIST 1 2 5 8 14



Example Problem 14

Above PRINT commands are self-explanatory. The LIST optionrestricts the print output to the members listed.

LOADING 1 DEAD AND LIVE LOAD

Load case 1 is initiated followed by a title.

SELFWEIGHT Y -1.0

The above command will apply the selfweight of the structure inthe global Y direction with a -1.0 factor. Since the global Y is inthe upward direction, this load will act downwards.

JOINT LOAD4 5 FY -15. ; 11 FY -35.

Load 1 contains joint loads. FY indicates that the load is a force inthe global Y direction.

MEMB LOAD8 TO 13 UNI Y -0.9 ; 6 UNI GY -1.2

Load 1 contains member loads also. GY indicates that the load is inthe global Y direction while Y indicates local Y direction. Theword UNI stands for uniformly distributed load.

CALCULATE NATURAL FREQUENCY

The above command at the end of load case 1, will obtain the valueof natural frequency for the above load case.

LOADING 2 WIND FROM LEFTMEMBER LOAD1 2 UNI GX 0.6 ; 8 TO 10 UNI Y -1.

Load case 2 is initiated and contains only several member loads.

* 1/3 RD INCREASE IS ACCOMPLISHED BY 75% LOADLOAD COMB 3 75 PERCENT DL LL WL1 0.75 2 0.75


Example Problem 1 5

Above command identifies a combination load (case no. 3) with atitle. The second line provides the load cases and their respectivefactors used for the load combination. Any line beginning with *mark is treated as a comment line.

PERFORM ANALYSISThis command makes the program proceed with the analysis.

LOAD LIST 1 3

Above command activates load cases 1 and 3 only for the followingcommands. This also means that load case 2 will be made inactive.

PRINT MEMBER FORCESPRINT SUPPORT REACTION

Above PRINT commands are self-explanatory. Also note that allthe forces and reactions will be printed for load case 1 and 3 only.

PARAMETERNSF 0.85 ALLKY 1.2 MEMB 3 4RATIO 0.9 ALLPROFILE W14 MEMB 1 3 4

The PARAMETER command is used to specify steel designparameters NSF and KY (Table 3.1 of User's Manual). The RATIOparameter specifies that the actual stress over allowable stress ratioshould not exceed 0.9. Members 1, 3, and 4 are to be selected fromthe W14 profile only.

SELECT ALL

Now all members are to be selected based on most economicalcriteria.

GROUP MEMB 1 3 4GROUP MEMB 5 6 7GROUP MEMB 8 TO 13GROUP MEMB 14 TO 23



Example Problem 16

Although the program selects the most economical section for allmembers, it is not always practical to use many different sizes inone structure. The above GROUP command groups the members bytheir input listing. This means that members 1, 3 and 4 will haveone size (i.e. largest of the three). The same is true for the othergroups too.

PERFORM ANALYSIS

Since the member sizes are now all different, it is necessary toreanalyze the structure to get new values of forces in the members.

PARAMETERRATIO 1.0 ALLTRACK 1.0 ALL

New set of parameter values are now provided. The actual stress toallowable stress RATIO has been redefined as 1.0. The TRACKparameter tells the program to print out the allowable stress valuesas well. Note that the remaining parameter values provided earlierremain unchanged.

CHECK CODE ALL

With the above command, the latest member sizes with the latestanalysis results are checked to verify that they meet the CODEspecifications.

STEEL TAKE OFF

The above command instructs the program to list the length andweight of all the different member sizes. This is useful forestimation purposes.

FINISH

This command terminates the STAAD/Pro run.


Example Problem 1 7

************************************************** * * * STAAD/Pro STAAD-III * * Revision * * Proprietary Program of * * RESEARCH ENGINEERS, Inc. * * Date= * * Time= * * * * USER ID: * **************************************************

1. STAAD PLANE EXAMPLE PROBLEM NO. 1 2. UNIT FT KIP 3. JOINT COORDINATES 4. 1 0. 0. ; 2 30 0 ; 3 0 20 0 6 30 20 0 5. 7 0 35 ; 8 30 35 ; 9 7.5 35 ; 10 22.5 35. 6. 11 15 35 ; 12 5. 38. ; 13 25 38 7. 14 10 41 ; 15 20 41 ; 16 15 44 8. MEMBER INCIDENCE 9. 1 1 3 ; 2 3 7 ; 3 2 6 ; 4 6 8 ; 5 3 4 10. 6 4 5 ; 7 5 6 ; 8 7 12 ; 9 12 14 11. 10 14 16 ; 11 15 16 ; 12 13 15 ; 13 8 13 12. 14 9 12 ; 15 9 14 ; 16 11 14 ; 17 11 15 13. 18 10 15 ; 19 10 13 ; 20 7 9 14. 21 9 11 ; 22 10 11 ; 23 8 10 15. MEMBER PROPERTY AMERICAN 16. 1 3 4 TA ST W14X90 ; 2 TA ST W10X49 17. 5 6 7 TA ST W21X50 ; 8 TO 13 TA ST W18X35 18. 14 TO 23 TA ST L40404 19. MEMB TRUSS 20. 14 TO 23 21. MEMB RELEASE 22. 5 START MZ 23. UNIT INCH 24. CONSTANTS 25. E 29000. ALL 26. DEN 0.000283 ALL 27. BETA 90.0 MEMB 3 4 28. UNIT FT 29. SUPPORT 30. 1 FIXED ; 2 PINNED 31. DRAW JOINT MEMBER SUPPORT

DATE:APR29 1998

S T A A D -III

REV: 22.3a

STRUCTURE DATA:

TYPE = PLANE

NJ = 16

NM = 23

NE = 0

NS = 2

NL = 0

XMAX= 30.0

YMAX= 44.0

ZMAX= .0

UNIT FEET KIP

1 2

3 4 5 6

7 89 1011

12 13

14 15

16

1

2

3

4

5 6 7

8

9

10 11

12

131415 16 17 18

1920 21 22 23



Example Problem 18

32. PRINT MEMBER INFORMATION LIST 1 5 14


MEMBER START END LENGTH BETA JOINT JOINT (FEET) (DEG) RELEASES

1 1 3 20.000 .00 5 3 4 10.000 .00 000001000000 14 9 12 3.905 TRUSS


33. PRINT MEMBER PROPERTY LIST 1 2 5 8 14

MEMBER PROPERTIES. UNIT - INCH -----------------

MEMB PROFILE AX/ IZ/ IY/ IX/ AY AZ SZ SY

1 ST W14 X90 26.50 999.00 362.00 4.06 6.17 13.75 142.51 49.86 2 ST W10 X49 14.40 272.00 93.40 1.39 3.39 7.47 54.51 18.68 5 ST W21 X50 14.70 984.00 24.90 1.14 7.92 4.66 94.48 7.63 8 ST W18 X35 10.30 510.00 15.30 .51 5.31 3.40 57.63 5.10 14 ST L40 404 1.94 1.22 4.85 .04 .67 .67 .79 1.72


34. LOADING 1 DEAD AND LIVE LOAD 35. SELFWEIGHT Y -1.0 36. JOINT LOAD 37. 4 5 FY -15. ; 11 FY -35. 38. MEMB LOAD 39. 8 TO 13 UNI Y -0.9 ; 6 UNI GY -1.2 40. CALCULATE NATURAL FREQUENCY 41. LOADING 2 WIND FROM LEFT 42. MEMBER LOAD 43. 1 2 UNI GX 0.6 ; 8 TO 10 UNI Y -1. 44. * 1/3 RD INCREASE IS ACCOMPLISHED BY 75% LOAD 45. LOAD COMB 3 75 PERCENT DL LL WL 46. 1 0.75 2 0.75 47. PERFORM ANALYSIS



********************************************************* * * * NATURAL FREQUENCY FOR LOADING 1 = 3.81968 CPS * * MAX DEFLECTION = 1.21499 INCH GLO X, AT JOINT 7 * * * *********************************************************

48. LOAD LIST 1 3 49. PRINT MEMBER FORCES


Example Problem 1 9



1 1 1 54.05 -2.00 .00 .00 .00 -61.88 3 -52.25 2.00 .00 .00 .00 21.88 3 1 40.71 19.01 .00 .00 .00 247.88 3 -39.36 -10.01 .00 .00 .00 42.32

2 1 3 33.81 -5.50 .00 .00 .00 -21.88 7 -33.08 5.50 .00 .00 .00 -60.67 3 3 28.90 -.20 .00 .00 .00 -42.32 7 -28.35 6.95 .00 .00 .00 -11.36

3 1 2 58.79 .00 -2.00 .00 .00 .00 6 -56.99 .00 2.00 .00 40.00 .00 3 2 55.17 .00 -3.49 .00 .00 .00 6 -53.82 .00 3.49 .00 69.79 .00

4 1 6 31.93 .00 -5.50 .00 59.27 .00 8 -30.58 .00 5.50 .00 23.27 .00 3 6 31.66 .00 -13.70 .00 105.62 .00 8 -30.65 .00 13.70 .00 99.94 .00

5 1 3 -3.50 18.44 .00 .00 .00 .00 4 3.50 -17.94 .00 .00 .00 181.90 3 3 -10.21 10.46 .00 .00 .00 .00 4 10.21 -10.09 .00 .00 .00 102.77

6 1 4 -3.50 2.94 .00 .00 .00 -181.90 5 3.50 9.56 .00 .00 .00 148.81 3 4 -10.21 -1.16 .00 .00 .00 -102.77 5 10.21 10.53 .00 .00 .00 44.30

7 1 5 -3.50 -24.56 .00 .00 .00 -148.81 6 3.50 25.06 .00 .00 .00 -99.27 3 5 -10.21 -21.78 .00 .00 .00 -44.30 6 10.21 22.16 .00 .00 .00 -175.41

8 1 7 36.40 16.70 .00 .00 .00 60.67 12 -36.30 -11.28 .00 .00 .00 20.93 3 7 37.53 10.52 .00 .00 .00 11.36 12 -37.45 -2.08 .00 .00 .00 25.35

9 1 12 36.67 8.86 .00 .00 .00 -20.93 14 -36.56 -3.44 .00 .00 .00 56.77 3 12 36.60 7.53 .00 .00 .00 -25.35 14 -36.52 .91 .00 .00 .00 44.63

10 1 14 41.86 -19.61 .00 .00 .00 -56.77 16 -41.75 25.04 .00 .00 .00 -73.40 3 14 34.32 -13.84 .00 .00 .00 -44.63 16 -34.24 22.28 .00 .00 .00 -60.68

11 1 15 41.84 -19.64 .00 .00 .00 -56.90 16 -41.74 25.06 .00 .00 .00 -73.40 3 15 35.85 -15.66 .00 .00 .00 -42.50 16 -35.77 19.73 .00 .00 .00 -60.68



Example Problem 110



12 1 13 40.04 7.80 .00 .00 .00 -27.24 15 -39.93 -2.38 .00 .00 .00 56.90 3 13 27.54 8.69 .00 .00 .00 -3.70 15 -27.46 -4.62 .00 .00 .00 42.50

13 1 8 40.44 11.37 .00 .00 .00 23.27 13 -40.34 -5.95 .00 .00 .00 27.24 3 8 26.53 19.81 .00 .00 .00 99.94 13 -26.45 -15.74 .00 .00 .00 3.70

14 1 9 -2.43 .01 .00 .00 .00 .00 12 2.45 .01 .00 .00 .00 .00 3 9 5.53 .01 .00 .00 .00 .00 12 -5.52 .01 .00 .00 .00 .00

15 1 9 1.96 .01 .00 .00 .00 .00 14 -1.92 .01 .00 .00 .00 .00 3 9 -4.65 .01 .00 .00 .00 .00 14 4.68 .01 .00 .00 .00 .00

16 1 11 -24.43 .02 .00 .00 .00 .00 14 24.47 .02 .00 .00 .00 .00 3 11 -10.23 .01 .00 .00 .00 .00 14 10.26 .01 .00 .00 .00 .00

17 1 11 -21.22 .02 .00 .00 .00 .00 15 21.26 .02 .00 .00 .00 .00 3 11 -24.00 .01 .00 .00 .00 .00 15 24.03 .01 .00 .00 .00 .00

18 1 10 -1.64 .01 .00 .00 .00 .00 15 1.68 .01 .00 .00 .00 .00 3 10 5.88 .01 .00 .00 .00 .00 15 -5.85 .01 .00 .00 .00 .00

19 1 10 1.89 .01 .00 .00 .00 .00 13 -1.87 .01 .00 .00 .00 .00

3 10 -7.12 .01 .00 .00 .00 .00 13 7.14 .01 .00 .00 .00 .00

20 1 7 -17.12 .02 .00 .00 .00 .00 9 17.12 .02 .00 .00 .00 .00 3 7 -19.82 .02 .00 .00 .00 .00 9 19.82 .02 .00 .00 .00 .00

21 1 9 -19.43 .02 .00 .00 .00 .00 11 19.43 .02 .00 .00 .00 .00 3 9 -14.49 .02 .00 .00 .00 .00 11 14.49 .02 .00 .00 .00 .00

22 1 10 -21.48 .02 .00 .00 .00 .00 11 21.48 .02 .00 .00 .00 .00 3 10 -5.67 .02 .00 .00 .00 .00 11 5.67 .02 .00 .00 .00 .00

23 1 8 -23.32 .02 .00 .00 .00 .00 10 23.32 .02 .00 .00 .00 .00 3 8 1.15 .02 .00 .00 .00 .00 10 -1.15 .02 .00 .00 .00 .00



Example Problem 1 11

50. PRINT SUPPORT REACTION



1 1 2.00 54.05 .00 .00 .00 -61.88 3 -19.01 40.71 .00 .00 .00 247.88 2 1 -2.00 58.79 .00 .00 .00 .00 3 -3.49 55.17 .00 .00 .00 .00


51. PARAMETER 52. NSF 0.85 ALL 53. KY 1.2 MEMB 3 4 54. RATIO 0.9 ALL 55. PROFILE W14 MEMB 1 3 4 56. SELECT ALL

STAAD-III MEMBER SELECTION - (AISC) **************************

ALL UNITS ARE - KIP FEET (UNLESS OTHERWISE NOTED)

MEMBER TABLE RESULT/ CRITICAL COND/ RATIO/ LOADING/ FX MY MZ LOCATION =======================================================================

1 ST W14 X109 PASS AISC- H1-3 .870 3 40.71 C .00 247.88 .00 2 ST W16 X40 PASS AISC- H1-1 .873 1 33.08 C .00 60.67 15.00 3 ST W14 X90 PASS AISC- H1-3 .752 3 53.82 C -69.79 .00 20.00 4 ST W14 X109 PASS AISC- H1-3 .823 3 31.66 C 105.62 .00 .00 5 ST W24 X62 PASS AISC- H2-1 .842 1 3.50 T .00 -181.90 10.00 6 ST W24 X62 PASS AISC- H2-1 .842 1 3.50 T .00 -181.90 .00 7 ST W24 X62 PASS AISC- H2-1 .812 3 10.21 T .00 175.41 10.00 8 ST W16 X31 PASS AISC- H1-2 .834 1 36.40 C .00 60.67 .00



9 ST W14 X30 PASS AISC- H1-2 .873 1 36.56 C .00 -56.77 5.83 10 ST W18 X35 PASS AISC- H1-2 .831 1 41.75 C .00 73.40 5.83 11 ST W18 X35 PASS AISC- H1-2 .831 1 41.74 C .00 73.40 5.83 12 ST W14 X30 PASS AISC- H1-2 .892 1 39.93 C .00 -56.90 5.83 13 ST W18 X40 PASS AISC- H1-3 .864 3 26.53 C .00 99.94 .00 14 ST L20 203 PASS AISC- H1-1 .740 3 5.53 C .00 .00 .00 15 ST L20 203 PASS AISC- H1-1 .718 1 1.96 C .00 .00 .00 16 ST L25 206 PASS TENSION .862 1 24.47 T .00 .00 7.81



Example Problem 112

17 ST L25 255 PASS TENSION .892 3 24.03 T .00 .00 7.81 18 ST L30 253 PASS AISC- H1-1 .854 3 5.88 C .00 .00 .00 19 ST L20 202 PASS TENSION .803 3 7.14 T .00 .00 3.91 20 ST L25 205 PASS TENSION .823 3 19.82 T .00 .00 .00 21 ST L25 254 PASS TENSION .891 1 19.43 T .00 .00 .00 22 ST L25 205 PASS TENSION .892 1 21.48 T .00 .00 .00 23 ST L30 304 PASS TENSION .883 1 23.32 T .00 .00 .00

57. GROUP MEMB 1 3 4 58. GROUP MEMB 5 6 7 59. GROUP MEMB 8 TO 13 60. GROUP MEMB 14 TO 23

********************************************************* * * * NATURAL FREQUENCY FOR LOADING 1 = 4.68143 CPS * * MAX DEFLECTION = .84726 INCH GLO X, AT JOINT 7 * * * *********************************************************

62. PARAMETER 63. RATIO 1.0 ALL 64. TRACK 1.0 ALL 65. CHECK CODE ALL




1 ST W14 X109 PASS AISC- H1-3 .850 3 40.84 C .00 241.49 .00----------------------------------------------------------------------- | MEM= 1, UNIT KIP-INCH, L= 240.0 AX= 32.00 SZ= 173.2 SY= 61.2 | | KL/R-Y= 64.2 CB= 1.00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= 21.60 | | FTZ= 21.60 FCY= 27.00 FTY= 27.00 FA= 17.01 FT= 21.60 FV= 14.40 | -----------------------------------------------------------------------* 2 ST W16 X40 FAIL AISC- H1-1 1.007 1 33.18 C .00 73.78 15.00----------------------------------------------------------------------- | MEM= 2, UNIT KIP-INCH, L= 180.0 AX= 11.80 SZ= 64.7 SY= 8.3 | | KL/R-Y= 115.0 CB= 1.00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= 15.70 | | FTZ= 21.60 FCY= 27.00 FTY= 27.00 FA= 10.98 FT= 21.60 FV= 14.40 | -----------------------------------------------------------------------3 ST W14 X109 PASS AISC- H1-3 .588 3 54.41 C -66.08 .00 20.00----------------------------------------------------------------------- | MEM= 3, UNIT KIP-INCH, L= 240.0 AX= 32.00 SZ= 173.2 SY= 61.2 | | KL/R-Y= 77.1 CB= 1.00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= 21.60 | | FTZ= 21.60 FCY= 27.00 FTY= 27.00 FA= 15.68 FT= 21.60 FV= 14.40 | -----------------------------------------------------------------------4 ST W14 X109 PASS AISC- H1-3 .866 3 32.05 C 111.44 .00 .00----------------------------------------------------------------------- | MEM= 4, UNIT KIP-INCH, L= 180.0 AX= 32.00 SZ= 173.2 SY= 61.2 | | KL/R-Y= 57.8 CB= 1.00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= 23.76 | | FTZ= 23.76 FCY= 27.00 FTY= 27.00 FA= 17.64 FT= 21.60 FV= 14.40 | -----------------------------------------------------------------------





5 ST W24 X62 PASS AISC- H2-1 .857 1 4.76 T .00 -185.22 10.00----------------------------------------------------------------------- | MEM= 5, UNIT KIP-INCH, L= 120.0 AX= 18.20 SZ= 130.6 SY= 9.8 | | KL/R-Y= 87.2 CB= 1.00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= 19.85 | | FTZ= 21.60 FCY= 27.00 FTY= 27.00 FA= 14.54 FT= 21.60 FV= 14.40 | -----------------------------------------------------------------------6 ST W24 X62 PASS AISC- H2-1 .857 1 4.76 T .00 -185.22 .00----------------------------------------------------------------------- | MEM= 6, UNIT KIP-INCH, L= 120.0 AX= 18.20 SZ= 130.6 SY= 9.8 | | KL/R-Y= 87.2 CB= 1.00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= 19.85 | | FTZ= 21.60 FCY= 27.00 FTY= 27.00 FA= 14.54 FT= 21.60 FV= 14.40 | -----------------------------------------------------------------------7 ST W24 X62 PASS AISC- H2-1 .822 3 11.02 T .00 177.52 10.00----------------------------------------------------------------------- | MEM= 7, UNIT KIP-INCH, L= 120.0 AX= 18.20 SZ= 130.6 SY= 9.8 | | KL/R-Y= 87.2 CB= 1.00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= 19.85 | | FTZ= 21.60 FCY= 27.00 FTY= 27.00 FA= 14.54 FT= 21.60 FV= 14.40 | -----------------------------------------------------------------------8 ST W18 X40 PASS AISC- H1-2 .675 1 33.26 C .00 73.78 .00----------------------------------------------------------------------- | MEM= 8, UNIT KIP-INCH, L= 70.0 AX= 11.80 SZ= 68.4 SY= 6.4 | | KL/R-Y= 55.0 CB= 1.00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= 23.76 | | FTZ= 23.76 FCY= 27.00 FTY= 27.00 FA= 17.90 FT= 21.60 FV= 14.40 | -----------------------------------------------------------------------9 ST W18 X40 PASS AISC- H1-2 .548 1 33.67 C .00 -56.34 5.83----------------------------------------------------------------------- | MEM= 9, UNIT KIP-INCH, L= 70.0 AX= 11.80 SZ= 68.4 SY= 6.4 | | KL/R-Y= 55.0 CB= 1.00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= 23.76 | | FTZ= 23.76 FCY= 27.00 FTY= 27.00 FA= 17.90 FT= 21.60 FV= 14.40 | -----------------------------------------------------------------------10 ST W18 X40 PASS AISC- H1-2 .655 1 40.08 C .00 67.43 5.83----------------------------------------------------------------------- | MEM= 10, UNIT KIP-INCH, L= 70.0 AX= 11.80 SZ= 68.4 SY= 6.4 | | KL/R-Y= 55.0 CB= 1.00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= 23.76 | | FTZ= 23.76 FCY= 27.00 FTY= 27.00 FA= 17.90 FT= 21.60 FV= 14.40 | -----------------------------------------------------------------------11 ST W18 X40 PASS AISC- H1-2 .655 1 39.99 C .00 67.43 5.83----------------------------------------------------------------------- | MEM= 11, UNIT KIP-INCH, L= 70.0 AX= 11.80 SZ= 68.4 SY= 6.4 | | KL/R-Y= 55.0 CB= 1.00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= 23.76 | | FTZ= 23.76 FCY= 27.00 FTY= 27.00 FA= 17.90 FT= 21.60 FV= 14.40 | -----------------------------------------------------------------------12 ST W18 X40 PASS AISC- H1-2 .565 1 36.50 C .00 -57.15 5.83----------------------------------------------------------------------- | MEM= 12, UNIT KIP-INCH, L= 70.0 AX= 11.80 SZ= 68.4 SY= 6.4 | | KL/R-Y= 55.0 CB= 1.00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= 23.76 | | FTZ= 23.76 FCY= 27.00 FTY= 27.00 FA= 17.90 FT= 21.60 FV= 14.40 | -----------------------------------------------------------------------



Example Problem 114

13 ST W18 X40 PASS AISC- H1-3 .891 3 26.93 C .00 103.42 .00----------------------------------------------------------------------- | MEM= 13, UNIT KIP-INCH, L= 70.0 AX= 11.80 SZ= 68.4 SY= 6.4 | | KL/R-Y= 55.0 CB= 1.00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= 23.76 | | FTZ= 23.76 FCY= 27.00 FTY= 27.00 FA= 17.90 FT= 21.60 FV= 14.40 | -----------------------------------------------------------------------14 ST L25 206 PASS AISC- H1-1 .226 3 3.99 C .00 .00 .00----------------------------------------------------------------------- | MEM= 14, UNIT KIP-INCH, L= 46.9 AX= 1.55 SZ= .3 SY= .7 | | KL/R-Z= 111.8 CB= .00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= .00 | | FTZ= .00 FCY= .00 FTY= .00 FA= 11.43 FT= 21.60 FV= .00 | -----------------------------------------------------------------------15 ST L25 206 PASS AISC- H1-1 .521 1 3.49 C .00 .00 .00----------------------------------------------------------------------- | MEM= 15, UNIT KIP-INCH, L= 78.0 AX= 1.55 SZ= .3 SY= .7 | | KL/R-Z= 185.8 CB= .00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= .00 | | FTZ= .00 FCY= .00 FTY= .00 FA= 4.32 FT= 21.60 FV= .00 | -----------------------------------------------------------------------16 ST L25 206 PASS TENSION .860 1 24.44 T .00 .00 7.81----------------------------------------------------------------------- | MEM= 16, UNIT KIP-INCH, L= 93.7 AX= 1.55 SZ= .3 SY= .7 | | KL/R-Z= 223.3 CB= .00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= .00 | | FTZ= .00 FCY= .00 FTY= .00 FA= 3.00 FT= 21.60 FV= .00 | -----------------------------------------------------------------------17 ST L25 206 PASS TENSION .836 3 23.74 T .00 .00 7.81----------------------------------------------------------------------- | MEM= 17, UNIT KIP-INCH, L= 93.7 AX= 1.55 SZ= .3 SY= .7 | | KL/R-Z= 223.3 CB= .00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= .00 | | FTZ= .00 FCY= .00 FTY= .00 FA= 3.00 FT= 21.60 FV= .00 | -----------------------------------------------------------------------18 ST L25 206 PASS AISC- H1-1 .816 3 5.46 C .00 .00 .00----------------------------------------------------------------------- | MEM= 18, UNIT KIP-INCH, L= 78.0 AX= 1.55 SZ= .3 SY= .7 | | KL/R-Z= 185.8 CB= .00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= .00 | | FTZ= .00 FCY= .00 FTY= .00 FA= 4.32 FT= 21.60 FV= .00 | -----------------------------------------------------------------------19 ST L25 206 PASS TENSION .233 3 6.61 T .00 .00 3.91----------------------------------------------------------------------- | MEM= 19, UNIT KIP-INCH, L= 46.9 AX= 1.55 SZ= .3 SY= .7 | | KL/R-Z= 111.8 CB= .00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= .00 | | FTZ= .00 FCY= .00 FTY= .00 FA= 11.43 FT= 21.60 FV= .00 | -----------------------------------------------------------------------20 ST L25 206 PASS TENSION .606 3 17.21 T .00 .00 .00----------------------------------------------------------------------- | MEM= 20, UNIT KIP-INCH, L= 90.0 AX= 1.55 SZ= .3 SY= .7 | | KL/R-Z= 214.4 CB= .00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= .00 | | FTZ= .00 FCY= .00 FTY= .00 FA= 3.25 FT= 21.60 FV= .00 | -----------------------------------------------------------------------21 ST L25 206 PASS TENSION .584 1 16.59 T .00 .00 .00





----------------------------------------------------------------------- | MEM= 21, UNIT KIP-INCH, L= 90.0 AX= 1.55 SZ= .3 SY= .7 | | KL/R-Z= 214.4 CB= .00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= .00 | | FTZ= .00 FCY= .00 FTY= .00 FA= 3.25 FT= 21.60 FV= .00 | -----------------------------------------------------------------------22 ST L25 206 PASS TENSION .656 1 18.62 T .00 .00 .00----------------------------------------------------------------------- | MEM= 22, UNIT KIP-INCH, L= 90.0 AX= 1.55 SZ= .3 SY= .7 | | KL/R-Z= 214.4 CB= .00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= .00 | | FTZ= .00 FCY= .00 FTY= .00 FA= 3.25 FT= 21.60 FV= .00 | -----------------------------------------------------------------------* 23 ST L25 206 FAIL L/R-EXCEEDS 1.072----------------------------------------------------------------------- | MEM= 23, UNIT KIP-INCH, L= 90.0 AX= 1.55 SZ= .3 SY= .7 | | KL/R-Z= 214.4 CB= .00 YLD= 36.00 ALLOWABLE STRESSES: FCZ= .00 | | FTZ= .00 FCY= .00 FTY= .00 FA= .00 FT= .00 FV= .00 | -----------------------------------------------------------------------

66. STEEL TAKE OFF

STEEL TAKE-OFF --------------

PROFILE LENGTH(FEET) WEIGHT(KIP )

ST W14 X109 55.00 5.977 ST W16 X40 15.00 .601 ST W24 X62 30.00 1.854 ST W18 X40 34.99 1.402 ST L25 206 66.43 .349 ---------------- TOTAL = 10.183


67. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****

********************************************************* * For questions on STAAD-III, contact: * * Research Engineers, Inc at Build No. 2428 * * West Coast: Ph- (714) 974-2500 Fax- (714) 921-2543 * * East Coast: Ph- (978) 688-3626 Fax- (978) 685-7230 * *********************************************************



Example Problem 116

NOTES




A floor structure (bound by global X-Z axis) made up of steelbeams is subjected to area load (i.e. load/area of floor) is appliedon the structure. Forces at intermediate section points (i.e.forces/moments at points between the incident joints) are obtainedand are used in the steel design.

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Example Problem 218


STAAD FLOOR A FLOOR FRAME DESIGN WITH AREA LOAD

Every input has to start with the word STAAD. The word FLOORsignifies that the structure is a floor structure and the geometry isdefined through X and Z axes.

UNIT FT KIP

Defines the UNITs.

JOINT COORDINATES1 0. 0. 0. 5 20. 0. 0. ; 7 5. 0. 10.8 10. 0. 10. ; 9 13. 0. 10. ; 10 15. 0. 10. ; 11 16.5 0. 10.12 20. 0. 10. ; 13 0. 0. 25. ; 14 5. 0. 25. ; 15 11. 0. 25.16 16.5 0. 25 ; 17 20. 0. 25. 18 0. 0. 28.19 20. 0. 28. ; 20 0. 0. 35. ; 21 20. 0. 35.

Joint number followed by X, Y and Z coordinates are providedabove. Note that, since this is a floor structure, the Y coordinatesare given as all zeros. Semicolon signs (;) are used as lineseparators, that is, multiple data can be input in one line. Note thatjoints between 1 and 5 (i.e. 2, 3, 4) are generated in the first line ofinput (see Users' Manual for input description).

MEMBER INCIDENCES1 1 2 4 ; 5 7 8 9 ; 10 13 14 13 ; 14 18 1915 20 21 ; 16 18 20 ; 17 13 18 ; 18 1 1319 7 14 ; 20 2 7 ; 21 9 1522 3 8 ; 23 11 16 ; 24 4 10 ; 25 19 2126 17 19 ; 27 12 17 ; 28 5 12


MEMB PROP1 TO 28 TABLE ST W12X26

All member properties are from AISC steel table W12X26. Theword ST stands for standard single section.

* MEMBERS WITH PINNED ENDS ARE RELEASED FOR MZ



MEMB RELEASE1 5 10 14 15 18 17 28 26 20 TO 24 START MZ4 9 13 14 15 18 16 27 25 19 21 TO 24 END MZ

First set of members (1 5 10 etc) have local moment-z (MZ)released at the start joint. This means that these members cannotcarry any moment-z (i.e. strong axis moment) at the start joint.Second set of members have MZ released at the end joints. Anyline beginning with * mark is treated as a comment line.

CONSTANTE 4176E3 ALL

CONSTANT command initiates input for material constants like E(modulus of elasticity) etc. A value of 4176E3 is same as4176000.0. Since the units at this point are KIP and FEET, thisvalue is equal to 29000 KSI.

SUPPORT1 5 13 17 20 21 FIXED

Above joints are defined as supports which are all fixed.

LOADING 1 300 POUNDS PER SFT DL+LL


AREA LOAD1 TO 28 ALOAD -0.30

All members are declared to carry Area load of 0.3 Kip/Sq.ft. Thisvalue is provided in local y-axis.

PERFORM ANALYSIS PRINT LOAD DATA

This command makes the program proceed with the analysis. Thecommand PRINT LOAD DATA will print the member load data.We want to see how the Area loads are distributed among themembers.

SECTION 0.5 MEMB 15 21 TO 24



Example Problem 220

An analysis results in the calculations of forces only at the endjoints of members. However, it may be necessary to determinevalues of forces at the intermediate points too. With the aboveSECTION command, the forces at 0.5 section (i.e. mid point) ofthe listed members are computed. These values will then be usedfor subsequent design.

PARAMETERSDMAX 2.0 ALLDMIN 1.0 ALLUNL 1.0 ALL

The PARAMETER command is used to specify steel designparameters (Table 3.1 of User's Manual). DMAX and DMINspecify maximum and minimum desired depths for ALL members.UNL stands for unsupported length to be used for calculation ofallowable bending stress.

SELECT MEMB 2 6 11 14 15 16 18 19 21 23 24 27

Above command instructs the program to select the mosteconomical section for the members listed.

FINISH

The FINISH command terminates the STAAD/Pro run.




1. STAAD FLOOR A FLOOR FRAME DESIGN WITH AREA LOAD 2. UNIT FT KIP 3. JOINT COORDINATES 4. 1 0. 0. 0. 5 20. 0. 0. ; 7 5. 0. 10. 5. 8 10. 0. 10. ; 9 13. 0. 10. ; 10 15. 0. 10. ; 11 16.5 0. 10. 6. 12 20. 0. 10. ; 13 0. 0. 25. ; 14 5. 0. 25. ; 15 11. 0. 25. 7. 16 16.5 0. 25 ; 17 20. 0. 25. 18 0. 0. 28. 8. 19 20. 0. 28. ; 20 0. 0. 35. ; 21 20. 0. 35. 9. MEMBER INCIDENCES 10. 1 1 2 4 ; 5 7 8 9 ; 10 13 14 13 ; 14 18 19 11. 15 20 21 ; 16 18 20 ; 17 13 18 ; 18 1 13 12. 19 7 14 ; 20 2 7 ; 21 9 15 13. 22 3 8 ; 23 11 16 ; 24 4 10 ; 25 19 21 14. 26 17 19 ; 27 12 17 ; 28 5 12 15. MEMB PROP AMERICAN 16. 1 TO 28 TABLE ST W12X26 17. * MEMBERS WITH PINNED ENDS ARE RELEASED FOR MZ 18. MEMB RELEASE 19. 1 5 10 14 15 18 17 28 26 20 TO 24 START MZ 20. 4 9 13 14 15 18 16 27 25 19 21 TO 24 END MZ 21. CONSTANT 22. E 4176E3 ALL 23. SUPPORT 24. 1 5 13 17 20 21 FIXED 25. LOADING 1 300 POUNDS PER SFT DL+LL 26. AREA LOAD 27. 1 TO 28 ALOAD -0.30 28. PERFORM ANALYSIS PRINT LOAD DATA



LOADING 1 300 POUNDS PER SFT DL+LL -----------

MEMBER LOAD - UNIT KIP FEET

MEMBER UDL L1 L2 CON L LIN1 LIN2

10 -0.450 GY 0.00 5.00 11 -0.450 GY 0.00 6.00 12 -0.450 GY 0.00 5.50 13 -0.450 GY 0.00 3.50 14 -1.500 GY 0.00 20.00 15 -1.050 GY 0.00 20.00 18 -0.750 GY 0.00 25.00 19 -1.950 -1.650 Y 20 -1.500 GY 0.00 10.00 21 -1.725 GY 0.00 15.13 22 -1.500 GY 0.00 10.00 23 -1.050 -1.350 Y 24 -1.500 GY 0.00 10.00 27 -0.525 GY 0.00 15.00 28 -0.750 GY 0.00 10.00




Example Problem 222

29. SECTION 0.5 MEMB 15 21 TO 24 30. PARAMETERS 31. CODE AISC 32. DMAX 2.0 ALL 33. DMIN 1.0 ALL 34. UNL 1.0 ALL 35. SELECT MEMB 2 6 11 14 15 16 18 19 21 23 24 27




2 ST W21 X44 PASS AISC- H1-3 0.863 1 0.00 C 0.00 -139.46 0.00 6 ST W18 X35 PASS AISC- H1-3 0.897 1 0.00 C 0.00 -102.32 3.00 11 ST W21 X50 PASS AISC- H1-3 0.897 1 0.00 C 0.00 -167.74 6.00 14 ST W12 X19 PASS SHEAR -Y 0.365 1 0.00 C 0.00 0.00 0.00 15 ST W14 X22 PASS AISC- H1-3 0.915 1 0.00 C 0.00 -52.50 10.00 16 ST W12 X19 PASS AISC- H1-3 0.744 1 0.00 C 0.00 -31.50 0.00 18 ST W14 X22 PASS SHEAR -Y 0.206 1 0.00 C 0.00 0.00 0.00 19 ST W24 X55 PASS AISC- H1-3 0.978 1 0.00 C 0.00 -221.85 0.00 21 ST W12 X22 PASS AISC- H1-3 0.984 1 0.00 C 0.00 -49.38 7.57 23 ST W12 X19 PASS AISC- H1-3 0.797 1 0.00 C 0.00 -33.75 7.50 24 ST W12 X19 PASS AISC- H1-3 0.443 1 0.00 C 0.00 -18.75 5.00



27 ST W21 X50 PASS AISC- H1-3 0.923 1 0.00 C 0.00 -172.59 0.00

36. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****

********************************************************* * FOR QUESTIONS REGARDING THIS VERSION OF PROGRAM * * RESEARCH ENGINEERS, Inc at * * Ph: (714) 974-2500 Fax: (714) 921-2543 * *********************************************************




A portal frame type steel structure is sitting on a concrete footing.The soil is to be considered as an elastic foundation. Value of soilsubgrade reaction is known from which spring constants arecalculated by simply multiplying the subgrade reaction by thetributary area of each modeled spring.

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NOTE:1) All dimensions are in feet.2) Soil Subgrade Reaction - 250 Kips/cft

Spring constant calculation: Spring of joints 1, 5, 10 & 14 = 8 x 1 x250 = 2000 Kips/ftSpring of joints 2, 3, 4, 11, 12 & 13 =8 x 2 x 250 = 4000 Kips/ft



Example Problem 324


STAAD PLANE PORTAL ON FOOTING FOUNDATION


UNIT FT KIPS


JOINT COORDINATES1 0.0 0.0 0.0 5 8.0 0.0 0.06 4.0 10.0 0.0 ; 7 4.0 20.0 0.08 24.0 20.0 0.0 ; 9 24.0 10.0 0.010 20.0 0.0 0.0 14 28.0 0.0 0.0

Joint number followed by X, Y and Z coordinates are providedabove. Note that, since this is a plane structure, the Z coordinatesare given as all zeros. Semicolon signs (;) are used as lineseparators, that is, multiple data can be input in one line.

MEMBER INCIDENCES1 1 2 45 3 6 ; 6 6 77 7 8 ; 8 6 99 8 9 ;10 9 1211 10 11 14


MEMBER PROPERTIES1 4 11 14 PRIS YD 1.0 ZD 8.02 3 12 13 PRIS YD 2.0 ZD 8.05 6 9 10 TABLE ST W10X337 8 TA ST W12X26

First two lines define member properties as PRIS (prismatic)followed by YD (depth) and ZD (width) values. The program willautomatically calculate the necessary properties to do the analysis.



Member properties for the remaining members are chosen from theAISC steel table. The word ST stands for standard single section.

* E FOR STEEL IS 29,000 AND FOR CONCRETE 3000UNIT INCHESCONSTANTSE 29000. MEMB 5 TO 10E 3000. MEMB 1 TO 4 11 TO 14DEN 0.283E-3 MEMB 5 TO 10DEN 8.68E-5 MEMB 1 TO 4 11 TO 14

CONSTANT command initiates input for material constants like E(modulus of elasticity) etc. Length unit is changed from FT toINCH to facilitate the input for E etc. Any line beginning with an* mark is treated as a comment line.

UNIT FTSUPPORTS2 TO 4 11 TO 13 FIXED BUT MZ KFY 4000.1 5 10 14 FIXED BUT MZ KFY 2000.

First set of joints are supports fixed in all directions except MZ(which is global moment-z). Also, a spring having a spring constantof 4000 kip/ft is provided in the global Y direction. The second setis similar to the former except for a different value of the springconstant.

LOADING 1 DEAD AND WIND LOAD COMBINED


SELF Y -1.0

The above command will apply the selfweight of the structure inthe global Y direction with a -1.0 factor. Since global Y is in theupward direction, this load will act downwards.

JOINT LOAD6 7 FX 5.0



Example Problem 326

Load 1 contains joint loads also. FX indicates that the load is aforce in the global X direction.

MEMBER LOAD7 8 UNI GY -3.0

Load 1 contains member loads also. GY indicates that the load actsin the global Y direction. The word UNI stands for uniformlydistributed load.

PERFORM ANALYSIS

This command makes the program proceed with the analysis.

PRINT ANALYSIS RESULTS

Above PRINT command instructs the program to print all analysisresults which include joint displacements, member forces andsupport reactions.

FINISH

This command terminates the STAAD/Pro run




1. STAAD PLANE PORTAL ON FOOTING FOUNDATION 2. UNIT FT KIPS 3. JOINT COORDINATES 4. 1 0.0 0.0 0.0 5 8.0 0.0 0.0 5. 6 4.0 10.0 0.0 ; 7 4.0 20.0 0.0 6. 8 24.0 20.0 0.0 ; 9 24.0 10.0 0.0 7. 10 20.0 0.0 0.0 14 28.0 0.0 0.0 8. MEMBER INCIDENCES 9. 1 1 2 4 10. 5 3 6 ; 6 6 7 11. 7 7 8 ; 8 6 9 12. 9 8 9 ;10 9 12 13. 11 10 11 14 14. MEMBER PROPERTIES AMERICAN 15. 1 4 11 14 PRIS YD 1.0 ZD 8.0

DEPTH NOT PROVIDED. HENCE, 9.99 UNITS ASSUMED.

16. 2 3 12 13 PRIS YD 2.0 ZD 8.0 17. 5 6 9 10 TA ST W10X33 18. 7 8 TA ST W12X26 19. * E FOR STEEL IS 29,000 AND FOR CONCRETE 3000 20. UNIT INCHES 21. CONSTANTS 22. E 29000. MEMB 5 TO 10 23. E 3000. MEMB 1 TO 4 11 TO 14 24. DEN 0.283E-3 MEMB 5 TO 10 25. DEN 8.68E-5 MEMB 1 TO 4 11 TO 14 26. UNIT FT 27. SUPPORTS 28. 2 TO 4 11 TO 13 FIXED BUT MZ KFY 4000. 29. 1 5 10 14 FIXED BUT MZ KFY 2000. 30. LOADING 1 DEAD AND WIND LOAD COMBINED 31. SELF Y -1.0 32. JOINT LOAD 33. 6 7 FX 5.0 34. MEMBER LOAD 35. 7 8 UNI GY -3.0 36. PERFORM ANALYSIS



37. PRINT ANALYSIS RESULTS



Example Problem 328

JOINT DISPLACEMENT (INCH RADIANS) STRUCTURE TYPE = PLANE ------------------

JOINT LOAD X-TRANS Y-TRANS Z-TRANS X-ROTAN Y-ROTAN Z-ROTAN

1 1 0.00000 -0.04273 0.00000 0.00000 0.00000 -0.00027 2 1 0.00000 -0.04899 0.00000 0.00000 0.00000 -0.00023 3 1 0.00000 -0.05434 0.00000 0.00000 0.00000 -0.00020 4 1 0.00000 -0.05846 0.00000 0.00000 0.00000 -0.00016 5 1 0.00000 -0.06123 0.00000 0.00000 0.00000 -0.00010 6 1 0.31747 -0.07850 0.00000 0.00000 0.00000 -0.00477 7 1 0.63262 -0.09080 0.00000 0.00000 0.00000 -0.00661 8 1 0.61484 -0.10243 0.00000 0.00000 0.00000 0.00388 9 1 0.32509 -0.08879 0.00000 0.00000 0.00000 0.00010 10 1 0.00000 -0.03595 0.00000 0.00000 0.00000 -0.00055 11 1 0.00000 -0.04882 0.00000 0.00000 0.00000 -0.00051 12 1 0.00000 -0.06095 0.00000 0.00000 0.00000 -0.00049 13 1 0.00000 -0.07167 0.00000 0.00000 0.00000 -0.00044 14 1 0.00000 -0.08056 0.00000 0.00000 0.00000 -0.00035

SUPPORT REACTIONS -UNIT KIPS FEET STRUCTURE TYPE = PLANE -----------------


2 1 0.00 16.33 0.00 0.00 0.00 0.00 3 1 -0.60 18.11 0.00 0.00 0.00 0.00 4 1 0.00 19.49 0.00 0.00 0.00 0.00 11 1 0.00 16.27 0.00 0.00 0.00 0.00 12 1 -9.40 20.32 0.00 0.00 0.00 0.00 13 1 0.00 23.89 0.00 0.00 0.00 0.00 1 1 0.00 7.12 0.00 0.00 0.00 0.00 5 1 0.00 10.20 0.00 0.00 0.00 0.00 10 1 0.00 5.99 0.00 0.00 0.00 0.00 14 1 0.00 13.43 0.00 0.00 0.00 0.00MEMBER END FORCES STRUCTURE TYPE = PLANE ----------------- ALL UNITS ARE -- KIPS FEET


1 1 1 0.00 7.12 0.00 0.00 0.00 0.00 2 0.00 -4.72 0.00 0.00 0.00 11.84

2 1 2 0.00 21.05 0.00 0.00 0.00 -11.84 3 0.00 -16.25 0.00 0.00 0.00 49.15

3 1 3 0.00 -22.49 0.00 0.00 0.00 -67.80 4 0.00 27.29 0.00 0.00 0.00 18.01

4 1 4 0.00 -7.80 0.00 0.00 0.00 -18.01 5 0.00 10.20 0.00 0.00 0.00 0.00

5 1 3 56.86 0.60 0.00 0.00 0.00 18.65 6 -56.53 -0.60 0.00 0.00 0.00 -12.61

6 1 6 29.01 -11.44 0.00 0.00 0.00 -50.87 7 -28.68 11.44 0.00 0.00 0.00 -63.52

7 1 7 16.44 28.68 0.00 0.00 0.00 63.52 8 -16.44 31.84 0.00 0.00 0.00 -95.12

8 1 6 -7.04 27.52 0.00 0.00 0.00 63.48 9 7.04 33.00 0.00 0.00 0.00 -118.26

9 1 8 31.84 16.44 0.00 0.00 0.00 95.12 9 -32.17 -16.44 0.00 0.00 0.00 69.27



10 1 9 65.17 9.40 0.00 0.00 0.00 48.99 12 -65.50 -9.40 0.00 0.00 0.00 44.97

11 1 10 0.00 5.99 0.00 0.00 0.00 0.00 11 0.00 -3.59 0.00 0.00 0.00 9.58

12 1 11 0.00 19.87 0.00 0.00 0.00 -9.58 12 0.00 -15.07 0.00 0.00 0.00 44.51

13 1 12 0.00 -30.12 0.00 0.00 0.00 -89.49 13 0.00 34.92 0.00 0.00 0.00 24.45

14 1 13 0.00 -11.03 0.00 0.00 0.00 -24.45 14 0.00 13.43 0.00 0.00 0.00 0.00


38. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****




Example Problem 330

NOTES




This example is a typical case of a load-dependent structure wherethe structural condition changes for different load cases. In thisexample, different bracing members are made inactive for differentload cases. This is done to prevent these members from carryingany compressive forces.

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Example Problem 432


STAAD PLANE* A PLANE FRAME STRUCTURE WITH TENSION BRACING


UNIT INCH KIP


SET NL 3

Above command sets maximum number of primary load cases to 3.This command is necessary only when the user will provide moreload cases after one analysis is done. In this example, we will beanalyzing the structure several times, each time changing thestructure and defining an associated load case.

JOINT COORDINATES1 0 0 0 3 480. 0 04 0 180. 0 6 480. 180. 07 240. 360. 0 ; 8 480. 360. 0

Joint number followed by X, Y, and Z coordinates are providedabove. Note that, since this is a plane structure, the Z coordinatesare given as all zeros. Semicolon signs (;) are used as lineseparators, that is, multiple data can be input in one line.

MEMBER INCIDENCE1 1 4 2 ; 3 5 7 ; 4 3 6 ; 5 6 8 ; 6 4 5 78 7 8 ; 9 1 5 ; 10 2 4 ; 11 3 5 ; 12 2 613 6 7 ;14 5 8


MEMBER TRUSS9 TO 14



Above command defines that members 9 through 14 are of typetruss. This means these members can only carry axialtension/compression and no moments.

MEMBER PROP1 TO 5 TABLE ST W12X266 7 8 TA ST W18X359 TO 14 TA LD L50505

All member properties are from the AISC steel table. The word STstands for standard single section. The word LD stands for long legback-to-back double angle.

CONSTANTSE 29000. ALL

CONSTANT command initiates input for material constants like E(modulus of elasticity) etc.

SUPPORT1 2 3 PINNED

Joints 1, 2 and 3 are supports. The word PINNED signifies that nomoments will be carried by these supports.

INACTIVE MEMBERS 9 TO 14

Above command makes the listed members inactive, that is, thesemembers will not be used in the analysis till they are made activeagain.

UNIT FTLOADING 1 DEAD AND LIVE LOAD

Load case 1 is initiated followed by a title. Note that UNIT ischanged from INCH to FT.

MEMBER LOAD6 8 UNI GY -1.07 UNI GY -1.5



Example Problem 434

Load 1 contains member loads also. GY indicates that the load actsin the global Y direction. The word UNI stands for uniformlydistributed load.

PERFORM ANALYSIS

This command makes the program proceed with the analysis. Notethat members 9 TO 14 will not be used in this analysis since theywere declared inactive before. In other words, for dead and liveload, the bracings are not used to carry any load.

CHANGES

Above CHANGE command will make all inactive members activeagain and informs the program to expect some changes.

INACTIVE MEMBERS 10 11 13

Above command makes the listed members inactive, i.e., thesemembers will not be used in the analysis till they are made activeagain. The reason for choosing these members is to avoidcompressive forces in these members in the next load case.

LOADING 2 WIND FROM LEFT


JOINT LOAD4 FX 30 ; 7 FX 15


PERFORM ANALYSIS

This command makes the program proceed with the analysis. Notethat only loading 2 will be used for this analysis.

CHANGE



Above CHANGE command will make all inactive members activeagain and informs the program to expect some changes.

INACTIVE MEMBERS 9 12 14

Above command makes the listed members inactive, that is, thesemembers will not be used in the analysis till they are made activeagain. The reason for choosing these members is to avoidcompressive forces in their members in the next load case.

LOADING 3 WIND FROM RIGHT


JOINT LOAD6 FX -30 ; 8 FX -15


LOAD COMBINATION 41 0.75 2 0.75LOAD COMBINATION 51 0.75 3 0.75

Above command identifies a combination load (case no. 4 and 5)with title. Note that for the analysis of a load-dependent structure,the load combinations must be provided immediately after the lastprimary load case has been provided.

PERFORM ANALYSIS

This command makes the program proceed with the analysis. Notethat only loadings 3, 4 and 5 will be considered for this analysis.

CHANGE

Above CHANGE command will make all inactive members activeagain.

LOAD LIST ALL



Example Problem 436

Above command will make all load cases active, since for eachanalysis, only corresponding load cases were active.

PRINT MEMBER FORCES

Above PRINT command is self-explanatory.

LOAD LIST 1 4 5

Above command will make load cases 1, 4 and 5 active. In thesubsequent design, we want only the forces of these load cases tobe used.

PARAMETERUNL 6.0 ALLKY 0.5 ALL

The PARAMETER command is used to specify the steel designparameters (Table 3.1 of Users' Manual). UNL stands for theunsupported length to be used for calculation of allowable bendingstress. Further, KY 0.5 ALL defines the effective length factor forbending about the Y-axis.

CHECK CODE ALL

Above command will now check to see how the latest sizes withlatest analysis results meet the CODE requirements.

FINISH

This command terminates a STAAD/Pro run.




1. STAAD PLANE A PLANE FRAME STRUCTURE WITH TENSION BRACING 2. UNIT INCH KIP 3. SET NL 3 4. JOINT COORDINATES 5. 1 0 0 0 3 480. 0 0 6. 4 0 180. 0 6 480. 180. 0 7. 7 240. 360. 0 ; 8 480. 360. 0 8. MEMBER INCIDENCE 9. 1 1 4 2 ; 3 5 7 ; 4 3 6 ; 5 6 8 ; 6 4 5 7 10. 8 7 8 ; 9 1 5 ; 10 2 4 ; 11 3 5 ; 12 2 6 11. 13 6 7 ;14 5 8 12. MEMBER TRUSS 13. 9 TO 14 14. MEMBER PROP AMERICAN 15. 1 TO 5 TABLE ST W12X26 16. 6 7 8 TA ST W18X35 17. 9 TO 14 TA LD L50505 18. CONSTANTS 19. E 29000. ALL 20. SUPPORT 21. 1 2 3 PINNED 22. INACTIVE MEMBERS 9 TO 14 23. UNIT FT 24. LOADING 1 DEAD AND LIVE LOAD 25. MEMBER LOAD 26. 6 8 UNI GY -1.0 27. 7 UNI GY -1.5 28. PERFORM ANALYSIS



29. CHANGES 30. INACTIVE MEMBERS 10 11 13 31. LOADING 2 WIND FROM LEFT 32. JOINT LOAD 33. 4 FX 30 ; 7 FX 15 34. PERFORM ANALYSIS 35. CHANGE 36. INACTIVE MEMBERS 9 12 14 37. LOADING 3 WIND FROM RIGHT 38. JOINT LOAD 39. 6 FX -30 ; 8 FX -15 40. LOAD COMBINATION 4 41. 1 0.75 2 0.75 42. LOAD COMBINATION 5 43. 1 0.75 3 0.75 44. PERFORM ANALYSIS 45. CHANGE 46. LOAD LIST ALL 47. PRINT MEMBER FORCES



Example Problem 438



1 1 1 8.26 -0.67 0.00 0.00 0.00 0.00 4 -8.26 0.67 0.00 0.00 0.00 -10.04 2 1 -0.31 0.22 0.00 0.00 0.00 0.00 4 0.31 -0.22 0.00 0.00 0.00 3.29 3 1 15.83 -0.20 0.00 0.00 0.00 0.00 4 -15.83 0.20 0.00 0.00 0.00 -2.93 4 1 5.96 -0.34 0.00 0.00 0.00 0.00 4 -5.96 0.34 0.00 0.00 0.00 -5.06 5 1 18.07 -0.65 0.00 0.00 0.00 0.00 4 -18.07 0.65 0.00 0.00 0.00 -9.73

2 1 2 38.48 -0.05 0.00 0.00 0.00 0.00 5 -38.48 0.05 0.00 0.00 0.00 -0.74 2 2 9.06 0.16 0.00 0.00 0.00 0.00 5 -9.06 -0.16 0.00 0.00 0.00 2.47 3 2 28.79 -0.15 0.00 0.00 0.00 0.00 5 -28.79 0.15 0.00 0.00 0.00 -2.25 4 2 35.65 0.09 0.00 0.00 0.00 0.00 5 -35.65 -0.09 0.00 0.00 0.00 1.30 5 2 50.45 -0.15 0.00 0.00 0.00 0.00 5 -50.45 0.15 0.00 0.00 0.00 -2.24

3 1 5 10.14 -2.21 0.00 0.00 0.00 -13.23 7 -10.14 2.21 0.00 0.00 0.00 -19.93 2 5 -0.29 0.43 0.00 0.00 0.00 3.42 7 0.29 -0.43 0.00 0.00 0.00 3.01 3 5 10.88 -0.64 0.00 0.00 0.00 -5.32 7 -10.88 0.64 0.00 0.00 0.00 -4.28 4 5 7.38 -1.34 0.00 0.00 0.00 -7.36 7 -7.38 1.34 0.00 0.00 0.00 -12.69 5 5 15.76 -2.14 0.00 0.00 0.00 -13.91 7 -15.76 2.14 0.00 0.00 0.00 -18.16

4 1 3 23.26 0.72 0.00 0.00 0.00 0.00 6 -23.26 -0.72 0.00 0.00 0.00 10.77 2 3 24.66 0.07 0.00 0.00 0.00 0.00 6 -24.66 -0.07 0.00 0.00 0.00 1.10 3 3 -11.25 -0.16 0.00 0.00 0.00 0.00 6 11.25 0.16 0.00 0.00 0.00 -2.44 4 3 35.94 0.59 0.00 0.00 0.00 0.00 6 -35.94 -0.59 0.00 0.00 0.00 8.91 5 3 9.01 0.42 0.00 0.00 0.00 0.00 6 -9.01 -0.42 0.00 0.00 0.00 6.25

5 1 6 9.86 2.21 0.00 0.00 0.00 15.94 8 -9.86 -2.21 0.00 0.00 0.00 17.23 2 6 10.94 0.37 0.00 0.00 0.00 2.74 8 -10.94 -0.37 0.00 0.00 0.00 2.89 3 6 -0.36 -0.33 0.00 0.00 0.00 -2.16 8 0.36 0.33 0.00 0.00 0.00 -2.84 4 6 15.61 1.94 0.00 0.00 0.00 14.00 8 -15.61 -1.94 0.00 0.00 0.00 15.08 5 6 7.13 1.41 0.00 0.00 0.00 10.33 8 -7.13 -1.41 0.00 0.00 0.00 10.79

6 1 4 0.67 8.26 0.00 0.00 0.00 10.04 5 -0.67 11.74 0.00 0.00 0.00 -44.81 2 4 29.78 -0.31 0.00 0.00 0.00 -3.29 5 -29.78 0.31 0.00 0.00 0.00 -2.97 3 4 20.79 0.38 0.00 0.00 0.00 2.93 5 -20.79 -0.38 0.00 0.00 0.00 4.75 4 4 22.84 5.96 0.00 0.00 0.00 5.06 5 -22.84 9.04 0.00 0.00 0.00 -35.84 5 4 16.09 6.48 0.00 0.00 0.00 9.73 5 -16.09 8.52 0.00 0.00 0.00 -30.05



7 1 5 -1.49 16.60 0.00 0.00 0.00 58.78 6 1.49 13.40 0.00 0.00 0.00 -26.71 2 5 17.54 -0.34 0.00 0.00 0.00 -2.91 6 -17.54 0.34 0.00 0.00 0.00 -3.84 3 5 44.20 0.37 0.00 0.00 0.00 2.82 6 -44.20 -0.37 0.00 0.00 0.00 4.60 4 5 12.04 12.20 0.00 0.00 0.00 41.90 6 -12.04 10.30 0.00 0.00 0.00 -22.91 5 5 32.03 12.73 0.00 0.00 0.00 46.20 6 -32.03 9.77 0.00 0.00 0.00 -16.58

8 1 7 2.21 10.14 0.00 0.00 0.00 19.93 8 -2.21 9.86 0.00 0.00 0.00 -17.23 2 7 14.57 -0.29 0.00 0.00 0.00 -3.01 8 -14.57 0.29 0.00 0.00 0.00 -2.89 3 7 14.67 0.36 0.00 0.00 0.00 4.28 8 -14.67 -0.36 0.00 0.00 0.00 2.84 4 7 12.59 7.38 0.00 0.00 0.00 12.69 8 -12.59 7.62 0.00 0.00 0.00 -15.08 5 7 12.66 7.87 0.00 0.00 0.00 18.16 8 -12.66 7.13 0.00 0.00 0.00 -10.79

9 1 1 0.00 0.00 0.00 0.00 0.00 0.00 5 0.00 0.00 0.00 0.00 0.00 0.00 2 1 -33.37 0.00 0.00 0.00 0.00 0.00 5 33.37 0.00 0.00 0.00 0.00 0.00 3 1 0.00 0.00 0.00 0.00 0.00 0.00 5 0.00 0.00 0.00 0.00 0.00 0.00 4 1 -25.03 0.00 0.00 0.00 0.00 0.00 5 25.03 0.00 0.00 0.00 0.00 0.00 5 1 0.00 0.00 0.00 0.00 0.00 0.00 5 0.00 0.00 0.00 0.00 0.00 0.00

10 1 2 0.00 0.00 0.00 0.00 0.00 0.00 4 0.00 0.00 0.00 0.00 0.00 0.00 2 2 0.00 0.00 0.00 0.00 0.00 0.00 4 0.00 0.00 0.00 0.00 0.00 0.00 3 2 -25.74 0.00 0.00 0.00 0.00 0.00 4 25.74 0.00 0.00 0.00 0.00 0.00 4 2 0.00 0.00 0.00 0.00 0.00 0.00 4 0.00 0.00 0.00 0.00 0.00 0.00 5 2 -19.31 0.00 0.00 0.00 0.00 0.00 4 19.31 0.00 0.00 0.00 0.00 0.00

11 1 3 0.00 0.00 0.00 0.00 0.00 0.00 5 0.00 0.00 0.00 0.00 0.00 0.00 2 3 0.00 0.00 0.00 0.00 0.00 0.00 5 0.00 0.00 0.00 0.00 0.00 0.00 3 3 -29.87 0.00 0.00 0.00 0.00 0.00 5 29.87 0.00 0.00 0.00 0.00 0.00 4 3 0.00 0.00 0.00 0.00 0.00 0.00 5 0.00 0.00 0.00 0.00 0.00 0.00 5 3 -22.41 0.00 0.00 0.00 0.00 0.00 5 22.41 0.00 0.00 0.00 0.00 0.00

12 1 2 0.00 0.00 0.00 0.00 0.00 0.00 6 0.00 0.00 0.00 0.00 0.00 0.00 2 2 -22.31 0.00 0.00 0.00 0.00 0.00 6 22.31 0.00 0.00 0.00 0.00 0.00 3 2 0.00 0.00 0.00 0.00 0.00 0.00 6 0.00 0.00 0.00 0.00 0.00 0.00 4 2 -16.73 0.00 0.00 0.00 0.00 0.00 6 16.73 0.00 0.00 0.00 0.00 0.00 5 2 0.00 0.00 0.00 0.00 0.00 0.00 6 0.00 0.00 0.00 0.00 0.00 0.00



Example Problem 440

13 1 6 0.00 0.00 0.00 0.00 0.00 0.00 7 0.00 0.00 0.00 0.00 0.00 0.00 2 6 0.00 0.00 0.00 0.00 0.00 0.00 7 0.00 0.00 0.00 0.00 0.00 0.00 3 6 -17.53 0.00 0.00 0.00 0.00 0.00 7 17.53 0.00 0.00 0.00 0.00 0.00 4 6 0.00 0.00 0.00 0.00 0.00 0.00 7 0.00 0.00 0.00 0.00 0.00 0.00 5 6 -13.15 0.00 0.00 0.00 0.00 0.00 7 13.15 0.00 0.00 0.00 0.00 0.00 14 1 5 0.00 0.00 0.00 0.00 0.00 0.00 8 0.00 0.00 0.00 0.00 0.00 0.00 2 5 -17.75 0.00 0.00 0.00 0.00 0.00 8 17.75 0.00 0.00 0.00 0.00 0.00 3 5 0.00 0.00 0.00 0.00 0.00 0.00 8 0.00 0.00 0.00 0.00 0.00 0.00 4 5 -13.31 0.00 0.00 0.00 0.00 0.00 8 13.31 0.00 0.00 0.00 0.00 0.00 5 5 0.00 0.00 0.00 0.00 0.00 0.00 8 0.00 0.00 0.00 0.00 0.00 0.00


48. LOAD LIST 1 4 5 49. PARAMETER 50. CODE AISC 51. UNL 6.0 ALL 52. KY 0.5 ALL 53. CHECK CODE ALL




1 ST W12 X26 PASS AISC- H1-3 0.283 5 18.07 C 0.00 9.73 15.00 2 ST W12 X26 PASS AISC- H1-1 0.409 5 50.45 C 0.00 2.24 15.00 3 ST W12 X26 PASS AISC- H1-3 0.393 5 15.76 C 0.00 18.16 15.00 4 ST W12 X26 PASS AISC- H1-1 0.388 4 35.94 C 0.00 -8.91 15.00 5 ST W12 X26 PASS AISC- H1-3 0.345 4 15.61 C 0.00 -15.08 15.00 6 ST W18 X35 PASS AISC- H1-1 0.440 4 22.84 C 0.00 35.84 20.00 7 ST W18 X35 PASS AISC- H1-1 0.589 5 32.03 C 0.00 46.20 0.00 8 ST W18 X35 PASS AISC- H1-3 0.253 5 12.66 C 0.00 18.16 0.00 9 LD L50 505 PASS TENSION 0.191 4 25.03 T 0.00 0.00 0.00 10 LD L50 505 PASS TENSION 0.147 5 19.31 T 0.00 0.00 0.00 11 LD L50 505 PASS TENSION 0.171 5 22.41 T 0.00 0.00 0.00 12 LD L50 505 PASS TENSION 0.128 4 16.73 T 0.00 0.00 0.00 13 LD L50 505 PASS TENSION 0.100 5 13.15 T 0.00 0.00 0.00 14 LD L50 505 PASS TENSION 0.102 4 13.31 T 0.00 0.00 0.00



54. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****




Example Problem 442

NOTES




This example demonstrates the application of support displacementload (commonly known as sinking support) on a space framestructure.

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Example Problem 544


STAAD SPACE TEST FOR SUPPORT DISPLACEMENT

Every input has to start with the word STAAD. The word SPACEsignifies that the structure is a space frame structure (3-D) and thegeometry is defined through all X, Y and Z coordinates.

UNITS KIP FEET


JOINT COORDINATES1 0.0 0.0 0.0 ; 2 0.0 10.0 0.03 20.0 10.0 0.0 ; 4 20.0 0.0 0.05 20. 10. 20. ; 6 20. 0. 20.

Joint number followed by X, Y and Z coordinates are providedabove. Semicolon signs (;) are used as line separators, that is,multiple data can be input in one line.

MEMBER INCIDENCE1 1 2 34 3 5 ; 5 5 6


UNIT INCHMEMB PROP1 TO 5 PRIS AX 10. IZ 300. IY 300. IX 10.

All member properties are prismatic and the values of AX (area),IZ (moment of inertia in major axis), IY (moment of inertia inminor axis) and IX (torsional constant) are provided in INCH unit.

CONSTANTE 29000. ALL


SUPPORT



1 4 6 FIXED

Joints 1, 4 and 6 are fixed supports.

LOADING 1 SINKING SUPPORT


SUPPORT DISPLACEMENT LOAD4 FY -0.50

Load 1 is a support displacement load which is also commonlyknown as sinking support. FY signifies that the support settlementis in the global Y direction and the value of this settlement is 0.5inch downward.

PERFORM ANALYSIS



Above PRINT command will print displacements, reactions andmember forces.

FINISH




Example Problem 546


1. STAAD SPACE TEST FOR SUPPORT DISPLACEMENT 2. UNITS KIP FEET 3. JOINT COORDINATES 4. 1 0.0 0.0 0.0 ; 2 0.0 10.0 0.0 5. 3 20.0 10.0 0.0 ; 4 20.0 0.0 0.0 6. 5 20. 10. 20. ; 6 20. 0. 20. 7. MEMBER INCIDENCE 8. 1 1 2 3 9. 4 3 5 ; 5 5 6 10. UNIT INCH 11. MEMB PROP 12. 1 TO 5 PRIS AX 10. IZ 300. IY 300. IX 10. 13. CONSTANT 14. E 29000. ALL 15. SUPPORT 16. 1 4 6 FIXED 17. LOADING 1 SINKING SUPPORT 18. SUPPORT DISPLACEMENT LOAD 19. 4 FY -0.50 20. PERFORM ANALYSIS




JOINT DISPLACEMENT (INCH RADIANS) STRUCTURE TYPE = SPACE ------------------


1 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 2 1 0.09122 -0.00040 -0.01097 -0.00014 0.00050 -0.00154 3 1 0.09116 -0.49919 -0.09116 -0.00154 0.00000 -0.00154 4 1 0.00000 -0.50000 0.00000 0.00000 0.00000 0.00000 5 1 0.01097 -0.00040 -0.09122 -0.00154 -0.00050 -0.00014 6 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000

SUPPORT REACTIONS -UNIT KIP INCH STRUCTURE TYPE = SPACE -----------------


1 1 0.08 0.97 0.16 19.46 -0.60 106.99 4 1 0.07 -1.95 -0.07 107.18 0.00 107.18 6 1 -0.16 0.97 -0.08 106.99 0.60 19.46



MEMBER END FORCES STRUCTURE TYPE = SPACE ----------------- ALL UNITS ARE -- KIP INCH


1 1 1 0.97 -0.08 0.16 -0.60 -19.46 106.99 2 -0.97 0.08 -0.16 0.60 0.85 -116.71

2 1 2 0.08 0.97 0.16 0.85 -0.60 116.71 3 -0.08 -0.97 -0.16 -0.85 -36.63 116.92

3 1 3 -1.95 -0.07 0.07 0.00 -116.08 -116.08 4 1.95 0.07 -0.07 0.00 107.18 107.18

4 1 3 0.08 -0.97 -0.16 -0.85 36.63 -116.92 5 -0.08 0.97 0.16 0.85 0.60 -116.71

5 1 5 0.97 0.16 0.08 0.60 -116.71 -0.85 6 -0.97 -0.16 -0.08 -0.60 106.99 19.46


22. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****




Example Problem 548

NOTES




An example of prestress load in a plane frame structure. Theexample also covers the effect of the prestress load during theapplication of the load (known in the program as PRESTRESSload) and the effect of prestress after the load is applied (known inthe program as POSTSTRESS load).

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Example Problem 650


STAAD PLANE FRAME WITH PRESTRESSING LOAD


UNIT KIP FT


JOINT COORD1 0. 0. ; 2 40. 0. ; 3 0. 20. ; 4 40. 20.5 0. 35. ; 6 40. 35. ; 7 0. 50. ; 8 40. 50.

Joint number followed by X and Y coordinates are provided above.Note that, since this is a plane structure, the Z coordinates need notbe provided. Semicolon signs (;) are used as line separators, that is,multiple data can be input in one line.

MEMBER INCIDENCE1 1 3 ; 2 3 5 ; 3 5 7 ; 4 2 4 ; 5 4 66 6 8 ; 7 3 4 ; 8 5 6 ; 9 7 8


SUPPORT1 2 FIXED

Joint 1 is a fixed support while joint 2 is pinned meaning nomoments will be carried by joint 2.

MEMB PROP1 TO 9 PRI AX 2.2 IZ 1.0

All member properties are provided as PRI (prismatic). Values ofarea (AX) and moment of inertia about the major axis (IZ) areprovided.

UNIT INCHCONSTANTE 3000. ALL



CONSTANT command initiates input for material constants like E(modulus of elasticity) etc. Length unit is changed from FT toINCH to facilitate the input for E etc.

LOADING 1 PRESTRESSING LOADMEMBER PRESTRESS7 8 FORCE 300. ES 3. EM -12. EE 3.

Load case 1 is initiated followed by a title. Load 1 containsprestress load. Members 7 and 8 have cable prestress load of 300kips. The location of the cable at the start (ES) and end (EE) are 3inches above the CG while at the middle (EM) it is 12 inches belowthe CG. A prestress load in the program means the effect of theprestressing force during its application and will cause reaction atthe supports.

LOADING 2 POSTSTRESSING LOAD


MEMBER POSTSTRESS7 8 FORCE 300. ES 3. EM -12. EE 3.

Load 2 is a prestress load. Members 7 and 8 have cable prestressload of 300 kips. The location of the cable at the start (ES) and end(EE) are 3 inches above the CG while at the middle (EM) it is 12inches below the CG. A poststress load in the program signifies theeffect of the existing prestress load after the prestressing operationis complete and will cause no reaction at the supports.

PERFORM ANALYSIS

This command makes the program proceed with analysis.

UNIT FTPRINT ANALYSIS RESULT


FINISH




Example Problem 652


1. STAAD PLANE FRAME WITH PRESTRESSING LOAD 2. UNIT KIP FT 3. JOINT COORD 4. 1 0. 0. ; 2 40. 0. ; 3 0. 20. ; 4 40. 20. 5. 5 0. 35. ; 6 40. 35. ; 7 0. 50. ; 8 40. 50. 6. MEMBER INCIDENCE 7. 1 1 3 ; 2 3 5 ; 3 5 7 ; 4 2 4 ; 5 4 6 8. 6 6 8 ; 7 3 4 ; 8 5 6 ; 9 7 8 9. SUPPORT 10. 1 2 FIXED 11. MEMB PROP 12. 1 TO 9 PRI AX 2.2 IZ 1.0 13. UNIT INCH 14. CONSTANT 15. E 3000. ALL 16. LOADING 1 PRESTRESSING LOAD 17. MEMBER PRESTRESS 18. 7 8 FORCE 300. ES 3. EM -12. EE 3. 19. LOADING 2 POSTSTRESSING LOAD 20. MEMBER POSTSTRESS 21. 7 8 FORCE 300. ES 3. EM -12. EE 3. 22. PERFORM ANALYSIS



23. UNIT FT 24. PRINT ANALYSIS RESULT



1 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 2 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 3 1 0.07698 0.00000 0.00000 0.00000 0.00000 0.00039 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 4 1 -0.07698 0.00000 0.00000 0.00000 0.00000 -0.00039 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 5 1 0.07224 0.00000 0.00000 0.00000 0.00000 0.00087 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 6 1 -0.07224 0.00000 0.00000 0.00000 0.00000 -0.00087 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 7 1 -0.00059 0.00000 0.00000 0.00000 0.00000 0.00015 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 8 1 0.00059 0.00000 0.00000 0.00000 0.00000 -0.00015 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000





1 1 -6.71 0.00 0.00 0.00 0.00 58.62 2 0.00 0.00 0.00 0.00 0.00 0.00 2 1 6.71 0.00 0.00 0.00 0.00 -58.62 2 0.00 0.00 0.00 0.00 0.00 0.00



1 1 1 0.00 6.71 0.00 0.00 0.00 58.62 3 0.00 -6.71 0.00 0.00 0.00 75.67 2 1 0.00 0.00 0.00 0.00 0.00 0.00 3 0.00 0.00 0.00 0.00 0.00 0.00

2 1 3 0.00 13.92 0.00 0.00 0.00 90.81 5 0.00 -13.92 0.00 0.00 0.00 117.98 2 3 0.00 0.00 0.00 0.00 0.00 0.00 5 0.00 0.00 0.00 0.00 0.00 0.00

3 1 5 0.00 2.34 0.00 0.00 0.00 38.31 7 0.00 -2.34 0.00 0.00 0.00 -3.16 2 5 0.00 0.00 0.00 0.00 0.00 0.00 7 0.00 0.00 0.00 0.00 0.00 0.00

4 1 2 0.00 -6.71 0.00 0.00 0.00 -58.62 4 0.00 6.71 0.00 0.00 0.00 -75.67 2 2 0.00 0.00 0.00 0.00 0.00 0.00 4 0.00 0.00 0.00 0.00 0.00 0.00

5 1 4 0.00 -13.92 0.00 0.00 0.00 -90.81 6 0.00 13.92 0.00 0.00 0.00 -117.98 2 4 0.00 0.00 0.00 0.00 0.00 0.00 6 0.00 0.00 0.00 0.00 0.00 0.00

6 1 6 0.00 -2.34 0.00 0.00 0.00 -38.31 8 0.00 2.34 0.00 0.00 0.00 3.16 2 6 0.00 0.00 0.00 0.00 0.00 0.00 8 0.00 0.00 0.00 0.00 0.00 0.00

7 1 3 304.85 -37.50 0.00 0.00 0.00 -241.48 4 -304.85 -37.50 0.00 0.00 0.00 241.48 2 3 297.65 -37.50 0.00 0.00 0.00 -75.00 4 -297.65 -37.50 0.00 0.00 0.00 75.00

8 1 5 286.07 -37.50 0.00 0.00 0.00 -231.29 6 -286.07 -37.50 0.00 0.00 0.00 231.29 2 5 297.65 -37.50 0.00 0.00 0.00 -75.00 6 -297.65 -37.50 0.00 0.00 0.00 75.00

9 1 7 -2.34 0.00 0.00 0.00 0.00 3.16 8 2.34 0.00 0.00 0.00 0.00 -3.16 2 7 0.00 0.00 0.00 0.00 0.00 0.00 8 0.00 0.00 0.00 0.00 0.00 0.00


25. FINISH *************** END OF STAAD-III ***************

**** DATE= TIME= ****




Example Problem 654

NOTES




This example illustrates modelling of structures with OFFSETconnections. OFFSET connections arise w hen the center lines ofthe connected members do not intersect at the connection point.The connection eccentricity is modeled through specification ofMEMBER OFFSETS.

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Example Problem 756


STAAD PLANE TEST FOR MEMBER OFFSETS


UNIT FT KIP


JOINT COORD1 0. 0. ; 2 20. 0. ; 3 0. 15.4 20. 15. ; 5 0. 30. ; 6 20. 30.

Joint number followed by X and Y coordinates are provided above.Note that, since this is a plane structure, the Z coordinates need notbe provided. Semicolon signs (;) are used as line separators, that is,multiple data can be input in one line.

SUPPORT1 2 PINNED

Joints 1 and 2 are pinned supports. The word PINNED signifiesthat no moments will be carried by these supports.

MEMB INCI1 1 3 2 ; 3 3 5 45 3 4 ; 6 5 6 ; 7 1 4


MEMB PROP1 TO 4 TABLE ST W14X905 6 TA ST W12X267 TA LD L90408

All member properties are from AISC steel table. The word STstands for standard single section. LD stands for long leg back-to-back double angle.



UNIT INCHMEMB OFFSET5 6 START 7.0 0.0 0.05 6 END -7.0 0.0 0.07 END -7.0 -6.0 0.0

The member offset specification above provides the offset locationof the start or end joints of the members followed by X, Y and Zglobal coordinates from the corresponding incident joint.

CONSTANTE 29000. ALL


LOADING 1 WIND LOAD


JOINT LOAD3 FX 50. ; 5 FX 25.0

Load 1 contains joint loads. FX indicates that the load is a force inthe global X direction.

PERFORM ANALYSIS

This command makes the program proceed with analysis.

UNIT FTPRINT FORCESPRINT REACTIONS

Above PRINT commands are self-explanatory.

FINISH




Example Problem 758


1. STAAD PLANE TEST FOR MEMBER OFFSETS 2. UNIT FT KIP 3. JOINT COORD 4. 1 0. 0. ; 2 20. 0. ; 3 0. 15. 5. 4 20. 15. ; 5 0. 30. ; 6 20. 30. 6. SUPPORT 7. 1 2 PINNED 8. MEMB INCI 9. 1 1 3 2; 3 3 5 4 10. 5 3 4 ; 6 5 6 ; 7 1 4 11. MEMB PROP AMERICAN 12. 1 TO 4 TABLE ST W14X90 13. 5 6 TA ST W12X26 14. 7 TA LD L90408 15. UNIT INCH 16. MEMB OFFSET 17. 5 6 START 7.0 0.0 0.0 18. 5 6 END -7.0 0.0 0.0 19. 7 END -7.0 -6.0 0.0 20. CONSTANT 21. E 29000. ALL 22. LOADING 1 WIND LOAD 23. JOINT LOAD 24. 3 FX 50. ; 5 FX 25.0 25. PERFORM ANALYSIS



26. UNIT FT 27. PRINT FORCES



1 1 1 -10.76 -4.48 0.00 0.00 0.00 4.26 3 10.76 4.48 0.00 0.00 0.00 -71.48

2 1 2 75.00 -5.62 0.00 0.00 0.00 0.00 4 -75.00 5.62 0.00 0.00 0.00 -84.33

3 1 3 -6.76 11.89 0.00 0.00 0.00 111.68 5 6.76 -11.89 0.00 0.00 0.00 66.64

4 1 4 6.76 13.11 0.00 0.00 0.00 128.10 6 -6.76 -13.11 0.00 0.00 0.00 68.58

5 1 3 66.37 -4.00 0.00 0.00 0.00 -37.86 4 -66.37 4.00 0.00 0.00 0.00 -37.44



6 1 5 13.11 -6.76 0.00 0.00 0.00 -62.70 6 -13.11 6.76 0.00 0.00 0.00 -64.64

7 1 1 -106.63 -0.55 0.00 0.00 0.00 -4.26 4 106.63 0.55 0.00 0.00 0.00 -9.08


28. PRINT REACTIONS



1 1 -80.62 -75.00 0.00 0.00 0.00 0.00 2 1 5.62 75.00 0.00 0.00 0.00 0.00


29. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****




Example Problem 760

NOTES




Concrete design is performed on some members of a space framestructure. Design includes computation reinforcement for beamsand colummns. Secondary moments on the columns are obtainedthrough the means of a P-Delta analysis.

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The above example represents a space frame, and the members aremade of concrete. The input in the next page will show thedimensions of the members.

Two load cases, namely one for dead plus live load and anotherwith dead, live and wind load, are considered in design.



Example Problem 862


STAAD SPACE FRAME WITH CONCRETE DESIGN

Every input has to start with the word STAAD. The word SPACEsignifies that the structure is a space frame structure (3-D) and thegeometry is defined through all X, Y and Z coordinates.

UNIT KIP FT


JOINT COORDINATE1 0 0 0 ; 2 18 0 0 ; 3 38 0. 04 0 0 24 ; 5 18 0 24 ; 6 38 0 247 0 12 0 ; 8 18. 12 0 ; 9 38 12 010 0 12 24 ; 11 18 12 24 ; 12 38 12 2413 18 24 0 ; 14 38 24 0 ; 15 18 24 2416 38 24 24

Joint number followed by X, Y and Z coordinates are providedabove. Semicolon signs (;) are used as line separators, that is,multiple data can be input in one line.

MEMBER INCIDENCE1 1 7 ; 2 4 10 ; 3 2 8 ; 4 8 135 5 11 ; 6 11 15 ; 7 3 9 ; 8 9 149 6 12 ; 10 12 16 ; 11 7 8 1213 10 11 14 ; 15 13 14 ; 16 15 1617 7 10 ; 18 8 11 ; 19 9 1220 13 15 ; 21 14 16


UNIT INCHMEMB PROP1 2 PRISMATIC YD 12.0 IZ 509. IY 509. IX 1018.3 TO 10 PR YD 12.0 ZD 12.0 IZ 864. IY 864. IX 1279.11 TO 21 PR YD 21.0 ZD 16.0 IZ 5788. IY 2953. IX 6497.

All member properties are provided as prismatic. YD and ZD standfor depth and width. If ZD is not given, a circular shape is



assumed. All properties are calculated automatically from thesedimensions unless a different set of values of the properties aredefined. For this particular example, moment of inertia (IZ, IY andIX) are provided but only half the actual value is used in theanalysis. This is because the full moment of inertia will not beeffective due to cracking of concrete.

CONSTANTE 3150.0 ALLUNIT FTCONSTANTDEN .15 ALL

CONSTANT command initiates input for material constants like E(modulus of elasticity) etc. Length unit is changed from INCH toFT to facilitate the input for DENsity.

SUPPORT1 TO 6 FIXED

Joints 1 to 6 are fixed supports.

LOAD 1 (1.4DL + 1.7LL)


SELF Y -1.4

The above command will apply selfweight of the structure in globalY direction with a -1.4 factor. Since the global Y is in the upwarddirection, this load will act downwards.

MEMB LOAD11 TO 16 UNI Y -2.811 TO 16 UNI Y -5.1

Load 1 contains member loads also. Y indicates that the load is inthe local Y direction. The word UNI stands for uniformlydistributed load.

LOAD 2 .75 (1.4DL + 1.7LL + 1.7WL)



Example Problem 864


REPEAT LOAD1 0.75

The above command will repeat load 1 with a factor of 0.75 andwill use it in load 2.

JOINT LOAD15 16 FZ 8.511 FZ 20.012 FZ 16.010 FZ 8.5

Load 2 contains joint loads also. FZ indicates that the load is aforce in the global Z direction.

PDELTA ANALYSIS

This command makes the program proceed with the analysis takingP-DELTA (second order analysis) effect into account.

PRINT FORCES LIST 2 5 9 14 16

Above PRINT commands are self-explanatory. The LIST optionrestricts the print output to the members listed.

START CONCRETE DESIGN

The above command initiates a concrete design.

TRACK 1.0 MEMB 14TRACK 2.0 MEMB 16MAXMAIN 11 ALL

The values for the concrete design parameters are defined in theabove 3 commands. TRACK value of 1.0 will print maximummoments for which design governs, while a value of 2.0 will printmaximum moments at every tenth point along with the requiredreinforcement. MAXMAIN indicates that the maximum size of



main reinforcement is the number 11 bar. These parameters aredescribed in Table 4.1 of the Users' Manual.

DESIGN BEAM 14 16

Above command will design beams 14 and 16 producing output ofreinforcement bar patterns along with cut-off length.

DESIGN COLUMN 2 5

Above command will design columns 2 and 5 producing output ofreinforcement bar patterns.

END CONCRETE DESIGN

This will end the concrete design.

FINISH




Example Problem 866


1. STAAD SPACE FRAME WITH CONCRETE DESIGN 2. UNIT KIP FT 3. JOINT COORDINATE 4. 1 0 0 0 ; 2 18 0 0 ; 3 38 0. 0 5. 4 0 0 24 ; 5 18 0 24 ; 6 38 0 24 6. 7 0 12 0 ; 8 18 12 0 ; 9 38 12 0 7. 10 0 12 24 ; 11 18 12 24 ; 12 38 12 24 8. 13 18 24 0 ; 14 38 24 0 ; 15 18 24 24 9. 16 38 24 24 10. MEMBER INCIDENCE 11. 1 1 7 ; 2 4 10 ; 3 2 8 ; 4 8 13 12. 5 5 11 ; 6 11 15 ; 7 3 9 ; 8 9 14 13. 9 6 12 ; 10 12 16 ; 11 7 8 12 14. 13 10 11 14 ; 15 13 14 ; 16 15 16 15. 17 7 10 ; 18 8 11 ; 19 9 12 16. 20 13 15 ; 21 14 16 17. UNIT INCH 18. MEMB PROP 19. 1 2 PRISMATIC YD 12.0 IZ 509. IY 509. IX 1018.


20. 3 TO 10 PR YD 12.0 ZD 12.0 IZ 864. IY 864. IX 1279. 21. 11 TO 21 PR YD 21.0 ZD 16.0 IZ 5788. IY 2953. IX 6497. 22. CONSTANT 23. E 3150. ALL 24. UNIT FT 25. CONSTANT 26. DEN .15 ALL 27. SUPPORT 28. 1 TO 6 FIXED 29. LOAD 1 (1.4DL + 1.7LL) 30. SELF Y -1.4 31. MEMB LOAD 32. 11 TO 16 UNI Y -2.8 33. 11 TO 16 UNI Y -5.1 34. LOAD 2 .75(1.4DL + 1.7LL + 1.7WL) 35. REPEAT LOAD 36. 1 0.75 37. JOINT LOAD 38. 15 16 FZ 8.5 39. 11 FZ 20.0 40. 12 FZ 16.0 41. 10 FZ 8.5 42. PDELTA ANALYSIS



43. PRINT FORCES LIST 2 5 9 14 16



MEMBER END FORCES STRUCTURE TYPE = SPACE ----------------- ALL UNITS ARE -- KIP FEET


2 1 4 68.03 -4.06 -0.69 0.00 2.75 -17.48 10 -66.05 4.06 0.69 0.00 5.53 -31.65 2 4 54.84 -3.37 -6.54 1.16 41.74 -15.19 10 -53.36 3.37 6.54 -1.16 41.22 -25.74

5 1 5 289.34 -0.48 -0.73 0.00 2.93 -4.49 11 -286.82 0.48 0.73 0.00 5.89 -3.11 2 5 227.49 -0.89 -12.26 1.02 89.85 -6.93 11 -225.60 0.89 12.26 -1.02 82.40 -5.83

9 1 6 170.71 4.53 -0.68 0.00 2.70 15.80 12 -168.19 -4.53 0.68 0.00 5.42 37.54 2 6 139.09 2.89 -13.34 0.19 92.20 8.45 12 -137.20 -2.89 13.34 -0.19 83.84 24.97

14 1 11 -9.11 97.15 0.00 -0.26 -0.01 371.26 12 9.11 70.65 0.00 0.26 0.00 -106.23 2 11 -7.72 73.04 0.60 -1.02 -8.34 279.91 12 7.72 52.81 -0.60 1.02 -3.76 -77.60

16 1 15 13.65 84.54 0.00 0.03 0.00 105.58 16 -13.65 83.26 0.00 -0.03 0.00 -92.87 2 15 10.23 63.37 0.07 -0.09 -0.74 78.92 16 -10.23 62.48 -0.07 0.09 -0.52 -69.99


44. START CONCRETE DESIGN 45. CODE ACI 46. TRACK 1.0 MEMB 14 47. TRACK 2.0 MEMB 16 48. MAXMAIN 11 ALL 49. DESIGN BEAM 14 16

=====================================================================

B E A M N O. 14 D E S I G N R E S U L T S - FLEXURE

LEN - 20.00FT. FY - 60000. FC - 4000. SIZE - 16.00 X 21.00 INCHES

LEVEL HEIGHT BAR INFO FROM TO ANCHOR FT. IN. FT. IN. FT. IN. STA END _____________________________________________________________________

1 0 + 2-3/4 2-NUM.10 0 + 2-5/8 20 + 0-0/0 NO YES |----------------------------------------------------------------| | CRITICAL POS MOMENT= 191.17 KIP-FT AT 11.67 FT, LOAD 1 | | REQD STEEL= 2.50 IN2, ROW=0.0085, ROWMX=0.0214 ROWMN=0.0033 | | MAX/MIN/ACTUAL BAR SPACING= 10.73/ 2.54/10.73 INCH | | BASIC/REQD. DEVELOPMENT LENGTH = 48.19/ 47.45 INCH | |----------------------------------------------------------------|

2 1 + 6-1/8 4-NUM.11 0 + 0-0/0 16 + 2-0/0 YES NO |----------------------------------------------------------------| | CRITICAL NEG MOMENT= 371.26 KIP-FT AT 0.00 FT, LOAD 1 | | REQD STEEL= 5.38 IN2, ROW=0.0184, ROWMX=0.0214 ROWMN=0.0033 | | MAX/MIN/ACTUAL BAR SPACING= 10.59/ 2.82/ 3.53 INCH | | BASIC/REQD. DEVELOPMENT LENGTH = 59.20/153.91 INCH | |----------------------------------------------------------------|

3 1 + 6-3/8 3-NUM.6 15 + 2-1/4 20 + 0-0/0 NO YES |----------------------------------------------------------------| | CRITICAL NEG MOMENT= 106.23 KIP-FT AT 20.00 FT, LOAD 1 | | REQD STEEL= 1.31 IN2, ROW=0.0044, ROWMX=0.0214 ROWMN=0.0033 | | MAX/MIN/ACTUAL BAR SPACING= 11.25/ 1.75/ 5.63 INCH | | BASIC/REQD. DEVELOPMENT LENGTH = 16.70/ 27.75 INCH | |----------------------------------------------------------------|



Example Problem 868

B E A M N O. 14 D E S I G N R E S U L T S - SHEAR

AT START SUPPORT - Vu= 84.22 KIP Vc= 37.44 KIP Vs= 61.64 KIP PROVIDE NUM. 4 BARS AT 7.2 IN. C/C FOR 110. IN. AT END SUPPORT - Vu= 57.72 KIP Vc= 37.44 KIP Vs= 30.46 KIP PROVIDE NUM. 4 BARS AT 9.3 IN. C/C FOR 70. IN.

___ 11J____________________ 240.X 16.X 21_____________________ 12J____ | | ||=========================================================================|| | 4#11H |18. |0.TO |194. | | | | | | | | | 3#6 H 18.|182.TO 240. | | 17#4 C/C 7 | | | | | | | | | | | | | | | | 9#4 C/C 9 | | | 2#10H | 3. |3.TO |240. | | | | | | | | | | | | | | | | | | |==========================================================================|| | | |___________________________________________________________________________| ___________ ___________ ___________ ___________ ___________ | | | | | | | | | | | OOOO | | OOOO | | OOOO | | OOOO | | ooo | | 4#11 | | 4#11 | | 4#11 | | 4#11 | | 3#6 | | | | | | | | | | | | | | 2#10 | | 2#10 | | 2#10 | | 2#10 | | | | OO | | OO | | OO | | OO | | | | | | | | | | | |___________| |___________| |___________| |___________| |___________|

=====================================================================

B E A M N O. 16 D E S I G N R E S U L T S - FLEXURE

LEN - 20.00FT. FY - 60000. FC - 4000. SIZE - 16.00 X 21.00 INCHES

LEVEL HEIGHT BAR INFO FROM TO ANCHOR FT. IN. FT. IN. FT. IN. STA END _____________________________________________________________________

1 0 + 2-3/4 3-NUM.11 0 + 0-0/0 20 + 0-0/0 YES YES |----------------------------------------------------------------| | CRITICAL POS MOMENT= 320.30 KIP-FT AT 10.00 FT, LOAD 1 | | REQD STEEL= 4.50 IN2, ROW=0.0154, ROWMX=0.0214 ROWMN=0.0033 | | MAX/MIN/ACTUAL BAR SPACING= 10.59/ 2.82/ 5.30 INCH | | BASIC/REQD. DEVELOPMENT LENGTH = 59.20/ 79.71 INCH | |----------------------------------------------------------------|

2 1 + 6-3/8 3-NUM.6 0 + 0-0/0 2 + 3-3/4 YES NO |----------------------------------------------------------------| | CRITICAL NEG MOMENT= 105.58 KIP-FT AT 0.00 FT, LOAD 1 | | REQD STEEL= 1.30 IN2, ROW=0.0043, ROWMX=0.0214 ROWMN=0.0033 | | MAX/MIN/ACTUAL BAR SPACING= 11.25/ 1.75/ 5.63 INCH | | BASIC/REQD. DEVELOPMENT LENGTH = 16.70/ 27.75 INCH | |----------------------------------------------------------------|

3 1 + 6-3/8 2-NUM.7 16 + 5-5/8 20 + 0-0/0 NO YES |----------------------------------------------------------------| | CRITICAL NEG MOMENT= 92.87 KIP-FT AT 20.00 FT, LOAD 1 | | REQD STEEL= 1.15 IN2, ROW=0.0039, ROWMX=0.0214 ROWMN=0.0033 | | MAX/MIN/ACTUAL BAR SPACING= 11.13/ 1.88/11.13 INCH | | BASIC/REQD. DEVELOPMENT LENGTH = 22.77/ 32.37 INCH | |----------------------------------------------------------------|



REQUIRED REINF. STEEL SUMMARY : ------------------------------- SECTION REINF STEEL(+VE/-VE) MOMENTS(+VE/-VE) LOAD(+VE/-VE) (FEET) (SQ. INCH) (KIP-FEET)

0.00 0.000/ 1.325 0.00/ 105.58 0/ 1 1.67 0.288/ 0.000 23.66/ 0.00 1/ 0 3.33 1.643/ 0.000 129.60/ 0.00 1/ 0 5.00 2.791/ 0.000 212.23/ 0.00 1/ 0 6.67 3.678/ 0.000 271.56/ 0.00 1/ 0 8.33 4.247/ 0.000 307.58/ 0.00 1/ 0 10.00 4.454/ 0.000 320.30/ 0.00 1/ 0 11.67 4.281/ 0.000 309.70/ 0.00 1/ 0 13.33 3.743/ 0.000 275.81/ 0.00 1/ 0 15.00 2.884/ 0.000 218.61/ 0.00 1/ 0 16.67 1.757/ 0.000 138.10/ 0.00 1/ 0 18.33 0.419/ 0.000 34.29/ 0.00 1/ 0 20.00 0.000/ 1.160 0.00/ 92.87 0/ 1

B E A M N O. 16 D E S I G N R E S U L T S - SHEAR

AT START SUPPORT - Vu= 71.60 KIP Vc= 37.44 KIP Vs= 46.80 KIP PROVIDE NUM. 4 BARS AT 9.3 IN. C/C FOR 90. IN. AT END SUPPORT - Vu= 70.33 KIP Vc= 37.44 KIP Vs= 45.30 KIP PROVIDE NUM. 4 BARS AT 9.3 IN. C/C FOR 90. IN.

___ 15J____________________ 240.X 16.X 21_____________________ 16J____ | | ||======= =============|| | 3#6|H |18. 0.TO 28. 2#7 H 18.|198.TO 240. | | 11#4 C/C 9 11#4 C/C 9 | | | 3#11H | 3. 0.TO 240. | | | | | | ||=========================================================================|| | | |___________________________________________________________________________| ___________ ___________ ___________ ___________ ___________ | | | | | | | | | | | ooo | | | | | | | | oo | | 3#6 | | | | | | | | 2#7 | | | | | | | | | | | | 3#11 | | 3#11 | | 3#11 | | 3#11 | | 3#11 | | OOO | | OOO | | OOO | | OOO | | OOO | | | | | | | | | | | |___________| |___________| |___________| |___________| |___________|

********************END OF BEAM DESIGN**************************

50. DESIGN COLUMN 2 5

====================================================================

C O L U M N N O. 2 D E S I G N R E S U L T S

FY - 60000 FC - 4000 PSI, CIRC SIZE 12.00 INCHES DIAMETER TIED

AREA OF STEEL REQUIRED = 3.189 SQ. IN.

BAR CONFIGURATION REINF PCT. LOAD LOCATION PHI ----------------------------------------------------------

11 - NUMBER 5 3.015 2 END 0.700 (EQUALLY SPACED)

====================================================================



Example Problem 870

C O L U M N N O. 5 D E S I G N R E S U L T S

FY - 60000 FC - 4000 PSI, SQRE SIZE - 12.00 X 12.00 INCHES, TIED

AREA OF STEEL REQUIRED = 6.581 SQ. IN.

BAR CONFIGURATION REINF PCT. LOAD LOCATION PHI ----------------------------------------------------------

12 - NUMBER 7 5.000 2 STA 0.700 (PROVIDE EQUAL NUMBER OF BARS ON EACH FACE)

********************END OF COLUMN DESIGN RESULTS********************

51. END CONCRETE DESIGN 52. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****





A space frame structure in this example consists of frame membersand finite elements. The finite element part is used to model floorflat plates and a shear wall. Design of an element is performed.



Example Problem 972


STAAD SPACE* EXAMPLE PROBLEM WITH FRAME MEMBERS AND*FINITE ELEMENTS

Every STAAD3 input file has to begin with the word STAAD. Theword SPACE signifies that the structure is a space frame and thegeometry is defined through X, Y and Z axes. The second lineforms the title to identify this project.

UNIT FEET KIP

The units for the data that follows are specified above.

JOINT COORD1 0 0 0 ; 2 0 0 20REP ALL 2 20 0 07 0 15 0 11 0 15 2012 5 15 0 14 15 15 015 5 15 20 17 15 15 2018 20 15 0 22 20 15 2023 25 15 0 25 35 15 026 25 15 20 28 35 15 2029 40 15 0 33 40 15 2034 20 3.75 0 36 20 11.25 037 20 3.75 20 39 20 11.25 20

The joint numbers and their coordinates are defined through theabove set of commands. The automatic generation facility has beenused several times in the above lines. Users are urged to readsection 6 of the Reference Manual where the joint coordinategeneration facilities are described..

MEMBER INCI*COLUMNS1 1 7 ; 2 2 113 3 34 ; 4 34 35 ; 5 35 36 ; 6 36 187 4 37 ; 8 37 38 ; 9 38 39 ; 10 39 2211 5 29 ; 12 6 33



*BEAMS IN Z DIRECTION AT X=013 7 8 16*BEAMS IN Z DIRECTION AT X=2017 18 19 20*BEAMS IN Z DIRECTION AT X=4021 29 30 24*BEAMS IN X DIRECTION AT Z = 025 7 12 ; 26 12 13 ; 27 13 14 ; 28 14 1829 18 23 ; 30 23 24 ; 31 24 25 ; 32 25 29*BEAMS IN X DIRECTION AT Z = 2033 11 15 ; 34 15 16 ; 35 16 17 ; 36 17 2237 22 26 ; 38 26 27 ; 39 27 28 ; 40 28 33

The member incidences are defined through the above set ofcommands. For some members, the member number followed bythe start and end joint numbers are defined. In other cases,STAAD3's automatic generation facilities are utilized. Section 6 ofthe Reference Manual describes these facilities in detail.

DEFINE MESHA JOINT 7B JOINT 11C JOINT 22D JOINT 18E JOINT 33F JOINT 29G JOINT 3H JOINT 4

The above lines define the nodes of super-elements. Super-elements are plate/shell surfaces from which a number of individualplate/shell elements can be generated. In this case, the pointsdescribe the outer edges of a slab and that of a shear wall. Our goalis to define the slab and the wall as several plate/shell elements.

GENERATE ELEMENTMESH ABCD 4 4MESH DCEF 4 4MESH DCHG 4 4



Example Problem 974

The above lines form the instructions to generate elements from thesuperelement profiles. For example, the command MESH ABCD 44 means that STAAD3 has to generate 16 elements from the surfaceformed by the points A, B, C and D with 4 elements along the sideAB & CD and 4 elements along the edges BC & DA.

MEMB PROP1 TO 40 PRIS YD 1 ZD 1

Members 1 to 40 are defined as a rectangular prismatic sectionwith 1 ft depth and 1 ft width.

ELEM PROP41 TO 88 TH 0.5

Elements 41 to 88 are defined to be 0.5 ft thick.

UNIT INCHCONSTANTE 3000 ALL

The modulus of elasticity for all the members and elements isdefined above following the command CONSTANT. Length unitsare changed to inches to facilitate the above input.

SUPPORT1 TO 6 FIXED

Joints 1 to 6 are defined to fixed supported.

UNIT FEETLOAD 1 DEAD LOAD FROM FLOORELEMENT LOAD41 TO 72 PRESSURE -1.0

Load 1 consists of a pressure load of 1 kip/sq.ft. intensity onelements 41 to 72.

LOAD 2 WIND LOADJOINT LOAD



11 33 FZ -20.22 FZ -100.

Load 2 consists of joint loads in the Z direction at joints 11, 22 and33.

LOAD COMB 31 0.9 2 1.3

Load 3 is a combination of 0.9 times load case 1 and 1.3 times loadcase 2.

PERFORM ANALYSIS

The command to perform an elastic analysis is specified above.

LOAD LIST 1 3PRINT SUPP REACPRINT MEMBER FORCES LIST 27PRINT ELEMENT FORCES LIST 47

Support reactions, members forces and element forces are printedfor load cases 1 and 3.

START CONCRETE DESIGNDESIGN ELEMENT 47END CONCRETE DESIGN

The above set of command form the instructions to STAAD3 toperform a concrete design on element 47. Design is done accordingto the ACI code. Note that design will consist only of flexuralreinforcement calculations in the longitudinal and transversedirections of the elements for the moments MX and MY.

FINI

The STAAD3 run is terminated.



Example Problem 976


1. STAAD SPACE 2. * EXAMPLE PROBLEM WITH FRAME MEMBERS AND 3. * FINITE ELEMENTS 4. UNIT FEET KIP 5. JOINT COORD 6. 1 0 0 0 ; 2 0 0 20 7. REP ALL 2 20 0 0 8. 7 0 15 0 11 0 15 20 9. 12 5 15 0 14 15 15 0 10. 15 5 15 20 17 15 15 20 11. 18 20 15 0 22 20 15 20 12. 23 25 15 0 25 35 15 0 13. 26 25 15 20 28 35 15 20 14. 29 40 15 0 33 40 15 20 15. 34 20 3.75 0 36 20 11.25 0 16. 37 20 3.75 20 39 20 11.25 20 17. MEMBER INCI 18. *COLUMNS 19. 1 1 7 ; 2 2 11 20. 3 3 34 ; 4 34 35 ; 5 35 36 ; 6 36 18 21. 7 4 37 ; 8 37 38 ; 9 38 39 ; 10 39 22 22. 11 5 29 ; 12 6 33 23. *BEAMS IN Z DIRECTION AT X=0 24. 13 7 8 16 25. *BEAMS IN Z DIRECTION AT X=20 26. 17 18 19 20 27. *BEAMS IN Z DIRECTION AT X=40 28. 21 29 30 24 29. *BEAMS IN X DIRECTION AT Z = 0 30. 25 7 12 ; 26 12 13 ; 27 13 14 ; 28 14 18 31. 29 18 23 ; 30 23 24 ; 31 24 25 ; 32 25 29 32. *BEAMS IN X DIRECTION AT Z = 20 33. 33 11 15 ; 34 15 16 ; 35 16 17 ; 36 17 22 34. 37 22 26 ; 38 26 27 ; 39 27 28 ; 40 28 33 35. DEFINE MESH 36. A JOINT 7 37. B JOINT 11 38. C JOINT 22 39. D JOINT 18 40. E JOINT 33 41. F JOINT 29 42. G JOINT 3 43. H JOINT 4 44. GENERATE ELEMENT 45. MESH ABCD 4 4 46. MESH DCEF 4 4 47. MESH DCHG 4 4 48. MEMB PROP 49. 1 TO 40 PRIS YD 1 ZD 1 50. ELEM PROP 51. 41 TO 88 TH 0.5 52. UNIT INCH 53. CONSTANT 54. E 3000 ALL 55. SUPPORT 56. 1 TO 6 FIXED 57. UNIT FEET



58. LOAD 1 DEAD LOAD FROM FLOOR 59. ELEMENT LOAD 60. 41 TO 72 PRESSURE -1.0 61. LOAD 2 WIND LOAD 62. JOINT LOAD 63. 11 33 FZ -20. 64. 22 FZ -100. 65. LOAD COMB 3 66. 1 0.9 2 1.3 67. PERFORM ANALYSIS



** WARNING : PRESSURE LOAD ON "PLANE STRESS" ELEMENT 42 IS IGNORED. **

68. LOAD LIST 1 3 69. PRINT SUPP REAC

SUPPORT REACTIONS -UNIT KIP FEET STRUCTURE TYPE = SPACE -----------------


1 1 8.91 82.54 11.36 56.50 -0.01 -44.35 3 8.05 74.62 10.57 53.79 0.03 -39.97 2 1 8.91 82.54 -11.36 -56.50 0.01 -44.35 3 8.00 73.97 -9.86 -47.77 0.18 -39.93 3 1 0.00 234.91 77.98 -36.31 0.00 0.00 3 0.00 344.96 162.44 -15.43 0.00 0.00 4 1 0.00 234.91 -77.98 36.31 0.00 0.00 3 0.00 77.87 18.12 49.48 0.00 0.00 5 1 -8.91 82.54 11.36 56.50 0.01 44.35 3 -8.05 74.62 10.57 53.79 -0.03 39.97 6 1 -8.91 82.54 -11.36 -56.50 -0.01 44.35 3 -8.00 73.97 -9.86 -47.77 -0.18 39.93


70. PRINT MEMBER FORCES LIST 27

MEMBER END FORCES STRUCTURE TYPE = SPACE ----------------- ALL UNITS ARE -- KIP FEET


27 1 13 0.76 -13.51 -0.06 23.36 0.15 -80.12 14 -0.76 13.51 0.06 -23.36 0.16 12.55 3 13 5.40 -12.13 -0.22 21.18 0.53 -72.15 14 -5.40 12.13 0.22 -21.18 0.56 11.52


71. PRINT ELEMENT FORCES LIST 47



Example Problem 978

ELEMENT FORCES FORCE,LENGTH UNITS= KIP FEET -------------- FORCE OR STRESS = FORCE/WIDTH/THICK, MOMENT = FORCE-LENGTH/WIDTH

ELEMENT LOAD QX QY MX MY MXY VONT VONB FX FY FXY

47 1 1.74 0.42 -12.58 -15.46 1.30 347.52 344.39 -1.14 -1.64 0.49 TOP : SMAX= -290.87 SMIN= -384.84 TMAX= 46.98 ANGLE= 21.2 BOTT: SMAX= 381.02 SMIN= 289.12 TMAX= 45.95 ANGLE= 20.9 3 1.55 0.38 -11.36 -13.91 1.14 314.60 308.32 -1.71 -2.40 3.97 TOP : SMAX= -261.25 SMIN= -349.22 TMAX= 43.98 ANGLE= 22.6 BOTT: SMAX= 339.33 SMIN= 262.94 TMAX= 38.19 ANGLE= 18.8

********************END OF ELEMENT FORCES********************

72. START CONCRETE DESIGN 73. DESIGN ELEMENT 47

ELEMENT DESIGN SUMMARY ----------------------

ELEMENT LONG. REINF MOM-X /LOAD TRANS. REINF MOM-Y /LOAD (SQ.IN/FT) (K-FT/FT) (SQ.IN/FT) (K-FT/FT)

47 TOP : 0.000 0.00 / 0 0.000 0.00 / 0 BOTT: 0.615 12.58 / 1 0.894 15.46 / 1

***************************END OF ELEMENT DESIGN***************************

74. END CONCRETE DESIGN 75. FINI

*************** END OF STAAD-III ***************

**** DATE= TIME= ****





A tank structure modeled with four-noded plate elements. Waterpressure from inside is used as loading for the tank. Reinforcementcalculations have been done for some elements.

Tank Model

Deflected Shape



Example Problem 1080


STAAD SPACE FINITE ELEMENT MODEL OF TANK

Every input has to start with the word STAAD. The word SPACEsignifies that the structure is a space frame (3-D) structure.

UNITS FEET KIPS


JOINT COORDINATES1 0. 0. 0. 5 0. 20. 0.REPEAT 4 5. 0. 0.REPEAT 4 0. 0. 5.REPEAT 4 -5. 0. 0.REPEAT 3 0. 0. -5.81 5. 0. 5. 83 5. 0. 15.REPEAT 2 5. 0. 0.

Joint number followed by X, Y and Z coordinates are providedabove. The REPEAT command generates joint coordinates byrepeating the pattern of the previous line of joint coordinates. Thenumber following the REPEAT command is the number ofrepetitions to be carried out. This is followed by X, Y and Zcoordinate increments.

ELEMENT INCIDENCES1 1 2 7 6 TO 4 1 1REPEAT 14 4 561 76 77 2 1 TO 64 1 165 1 6 81 7666 76 81 82 7167 71 82 83 6668 66 83 56 6169 6 11 84 8170 81 84 85 8271 82 85 86 8372 83 86 51 5673 11 16 87 8474 84 87 88 8575 85 88 89 8676 86 89 46 51



77 16 21 26 8778 87 26 31 8879 88 31 36 8980 89 36 41 46

Element connectivities are input as above by providing the elementnumber followed by joint numbers defining the element. TheREPEAT command generates element incidences by repeating thepattern of the previous line of element joints. The numberfollowing the REPEAT command is the number of repetitions to becarried out; followed by element and joint number increments.

UNIT INCHESELEMENT PROPERTIES1 TO 80 TH 8.0

Element properties are provided by specifying the THickness of 8.0inches.

CONSTANTSE 3000. ALL


SUPPORT1 TO 76 BY 5 81 TO 89 PINNED

The joints listed above are pinned supports. No moments will becarried by these supports. Note that 1 TO 76 BY 5 means 1 6 11etc. up to 76.

UNIT FTLOAD 1


ELEMENT LOAD4 TO 64 BY 4 PR 1.3 TO 63 BY 4 PR 2.2 TO 62 BY 4 PR 3.1 TO 61 BY 4 PR 4.




Load 1 consists of element load in the form of uniform PRessure.

PERFORM ANALYSISThis command makes the program proceed with the analysis.

UNIT INCHESPRINT JOINT DISPLACEMENTS LIST 5 25 45 65PRINT ELEM FORCE LIST 9 TO 16

Above PRINT commands are self-explanatory. The LIST optionrestricts the print output to that for the joints/elements listed.

START CONCRETE DESIGN

Above command initiates concrete design.

DESIGN SLAB 9 12

Slabs (i.e. elements) 9 and 12 will be designed and thereinforcement requirements obtained .

END CONCRETE DESIGN

Terminates concrete design.

DRAW STRESS 1 ROTATE X -20 Y 30 Z 20

The above command will create a stress contour plot for a rotatedconfiguration of the structure. The stress contour will be generatedfor load case 1 and they will be part of the run output.

FINISH





1. STAAD SPACE FINITE ELEMENT MODEL OF TANK STRUCTURE 2. UNITS FEET KIPS 3. JOINT COORDINATES 4. 1 0. 0. 0. 5 0. 20. 0. 5. REPEAT 4 5. 0. 0. 6. REPEAT 4 0. 0. 5. 7. REPEAT 4 -5. 0. 0. 8. REPEAT 3 0. 0. -5. 9. 81 5. 0. 5. 83 5. 0. 15. 10. REPEAT 2 5. 0. 0. 11. ELEMENT INCIDENCES 12. 1 1 2 7 6 TO 4 1 1 13. REPEAT 14 4 5 14. 61 76 77 2 1 TO 64 1 1 15. 65 1 6 81 76 16. 66 76 81 82 71 17. 67 71 82 83 66 18. 68 66 83 56 61 19. 69 6 11 84 81 20. 70 81 84 85 82 21. 71 82 85 86 83 22. 72 83 86 51 56 23. 73 11 16 87 84 24. 74 84 87 88 85 25. 75 85 88 89 86 26. 76 86 89 46 51 27. 77 16 21 26 87 28. 78 87 26 31 88 29. 79 88 31 36 89 30. 80 89 36 41 46 31. UNIT INCHES 32. ELEMENT PROPERTIES 33. 1 TO 80 TH 8.0 34. CONSTANTS 35. E 3000. ALL 36. SUPPORT 37. 1 TO 76 BY 5 81 TO 89 PINNED 38. UNIT FT 39. LOAD 1 40. ELEMENT LOAD 41. 4 TO 64 BY 4 PR 1. 42. 3 TO 63 BY 4 PR 2. 43. 2 TO 62 BY 4 PR 3. 44. 1 TO 61 BY 4 PR 4. 45. PERFORM ANALYSIS



46. UNIT INCHES 47. PRINT JOINT DISPLACEMENTS LIST 5 25 45 65






5 1 -.00357 -.00035 -.00357 .00027 .00000 -.00027 25 1 .00357 -.00035 -.00357 .00027 .00000 .00027 45 1 .00357 -.00035 .00357 -.00027 .00000 .00027 65 1 -.00357 -.00035 .00357 -.00027 .00000 -.00027


48. PRINT ELEM FORCE LIST 9 TO 16

ELEMENT FORCES FORCE,LENGTH UNITS= KIPS INCH -------------- FORCE OR STRESS = FORCE/WIDTH/THICK, MOMENT = FORCE-LENGTH/WIDTH


9 1 .15 .01 -4.83 5.10 4.85 1.20 1.06 .02 .08 .03 TOP : SMAX= .76 SMIN= -.63 TMAX= .69 ANGLE= -22.0 BOTT: SMAX= .65 SMIN= -.57 TMAX= .61 ANGLE= -22.3

10 1 .01 -.05 16.70 20.65 3.75 2.00 1.78 -.02 .18 .01 TOP : SMAX= 2.29 SMIN= 1.36 TMAX= .46 ANGLE= -25.9 BOTT: SMAX= -1.32 SMIN= -2.02 TMAX= .35 ANGLE= -38.1

11 1 -.03 -.05 9.81 22.77 -.04 2.05 1.67 -.02 .21 -.01 TOP : SMAX= 2.34 SMIN= .90 TMAX= .72 ANGLE= .5 BOTT: SMAX= -.94 SMIN= -1.93 TMAX= .49 ANGLE= -.4

12 1 -.02 -.04 .77 19.79 .21 1.98 1.66 .00 .16 -.01 TOP : SMAX= 2.02 SMIN= .07 TMAX= .97 ANGLE= -.4 BOTT: SMAX= -.07 SMIN= -1.69 TMAX= .81 ANGLE= -.9

13 1 .00 -.04 -3.82 -7.26 5.33 1.12 .99 -.02 .07 .07 TOP : SMAX= .08 SMIN= -1.07 TMAX= .58 ANGLE= 39.1 BOTT: SMAX= 1.02 SMIN= .07 TMAX= .48 ANGLE= 32.4

14 1 -.04 -.17 .17 -16.43 3.76 1.46 1.87 .02 .24 .01 TOP : SMAX= .13 SMIN= -1.39 TMAX= .76 ANGLE= 14.3 BOTT: SMAX= 1.84 SMIN= -.05 TMAX= .95 ANGLE= 10.5

15 1 -.01 -.15 -4.10 -21.34 -.17 1.65 2.03 .02 .20 -.02 TOP : SMAX= -.36 SMIN= -1.80 TMAX= .72 ANGLE= -1.3 BOTT: SMAX= 2.20 SMIN= .41 TMAX= .90 ANGLE= .0

16 1 .00 -.12 -6.03 -21.11 -.19 1.62 1.92 .00 .16 -.01 TOP : SMAX= -.56 SMIN= -1.82 TMAX= .63 ANGLE= -1.2 BOTT: SMAX= 2.14 SMIN= .56 TMAX= .79 ANGLE= -.3


49. START CONCRETE DESIGN 50. CODE ACI 51. DESIGN SLAB 9 12



ELEMENT DESIGN SUMMARY ----------------------

ELEMENT LONG. REINF MOM-X /LOAD TRANS. REINF MOM-Y /LOAD (SQ.IN/FT) (K-FT/FT) (SQ.IN/FT) (K-FT/FT)

9 TOP : .000 .00 / 0 .178 5.10 / 1 BOTT: .173 4.83 / 1 .000 .00 / 0

12 TOP : .173 .77 / 1 .738 19.79 / 1 BOTT: .000 .00 / 1 .000 .00 / 0

***************************END OF ELEMENT DESIGN***************************

52. END CONCRETE DESIGN 53. DRAW STRESS 1 ROTATE X -20 Y 30 Z 20

DATE:APR 29,1998

S T A A D -III

REV: 22.3a

STRUCTURE DATA:

TYPE = SPACE

NJ = 89

NM = 0

NE = 80

NS = 25

NL = 1

XMAX= 240.0

YMAX= 240.0

ZMAX= 240.0

UNIT INCH KIPS

STRESS CONTOUR

.57

.79

1.01

1.23

1.46

1.68

1.9

2.12

2.34

STDR LOAD= 1

54. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****

********************************************************* * For questions on STAAD-III, contact: * * Research Engineers, Inc at Build No. 2428 * * West Coast: Ph- (714) 974-2500 Fax- (714) 921-2543 * * East Coast: Ph- (978) 688-3626 Fax- (978) 685-7230 * *********************************************************




NOTES




Dynamic analysis (Response Spectrum) is performed for a steelstructure. Results of a static and dynamic analysis are combined.The combined results are then used for steel design.

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STAAD PLANE RESPONSE SPECTRUM ANALYSIS

Every input has to start with the word STAAD. The word PLANEsignifies that the structure is a plane frame structure and thegeometry is defined through X and Y axis.

UNIT FEET KIPS


JOINT COORDINATES1 0 0 0 ; 2 20 0 03 0 10 0 ; 4 20 10 05 0 20 0 ; 6 20 20 0

Joint number followed by X, Y and Z coordinates are providedabove. Note that, since this is a plane structure, the Z coordinatesare given as all zeros. Semicolon signs (;) are used as lineseparators, that is, multiple data can be input in one line.

MEMBER INCIDENCES1 1 3 ; 2 2 4 ; 3 3 5 ; 4 4 65 3 4 ; 6 5 6


MEMBER PROPERTIES1 TO 4 TA ST W10X335 TA ST W12X406 TA ST W8X40


SUPPORTS1 2 FIXED

Joints 1 and 2 are fixed supports.

UNIT INCH



CONSTANTSE 29000. ALLDEN 0.000283 ALL

CONSTANT command initiates input for material constants like E(modulus of elasticity) DEN (density) etc. Length unit is changedfrom FT to INCH to facilitate the input for E etc.

CUT OFF MODE SHAPE 2

Number of mode shapes to be considered in dynamic analysis is setto 2. Without the above command this will be set to 3.

* LOAD 1 WILL BE STATIC LOADUNIT FEETLOAD 1 DEAD AND LIVE LOADS

Load case 1 is initiated followed by a title. Note that line startingwith * mark indicates a comment line.

SELFWEIGHT Y -1.0

The above command will apply selfweight of the structure in theglobal Y direction with a -1.0 factor. Since the global Y is in theupward direction, this load will act downwards.

MEMBER LOADS5 CON GY -5.0 6.05 CON GY -7.5 10.05 CON GY -5.0 14.05 6 UNI Y -1.5

Load 1 contains member loads also. GY indicates that the load is inthe global Y direction while Y indicates local Y direction. Theword UNI stands for uniformly distributed load while CON standsfor concentrated load. GY is followed by the value of the load andthe distance at which it is applied.

* NEXT LOAD WILL BE RESPONSE SPECTRUM LOAD* WITH MASSES PROVIDED IN TERMS OF LOAD.LOAD 2 SEISMIC LOADING




Load case 2 is initiated followed by a title. This will be a dynamicload case. Permanent masses will be provided in the forms of loads.These masses (in terms of loads) will be considered for theeigensolution. Since these loads are converted to masses, signs areimmaterial. Also, the direction(X, Y, Z etc.) of the loads willcorrespond to the dynamic degrees of freedom. In a PLANE frame,only X and Y directions need to be considered. In a SPACE frame,masses (loads) may be provided in all three (X, Y and Z)directions. The user has the freedom to restrict one or moredirections.

SELFWEIGHT X 1.0SELFWEIGHT Y 1.0

The above command will apply the selfweight of the structure inthe global X and Y directions with a factor of 1.0

MEMBER LOADS5 CON GX 5.0 6.05 CON GY 5.0 6.05 CON GX 7.5 10.05 CON GY 7.5 10.05 CON GX 5.0 14.05 CON GY 5.0 14.0

Masses are provided as member loads. GX indicates that the load isin the global X direction. The word CON stands for concentratedload.

SPECTRUM CQC X 1.0 ACC DAMP 0.05 SCALE 32.20.03 1.00 ; 0.05 1.350.1 1.95 ; 0.2 2.800.5 2.80 ; 1.0 1.60

The above SPECTRUM command specifies that the modalresponses be combined using the CQC method instead of the SRSSmethod. The spectrum effect is in the global X direction with afactor of 1.0. Spectrum data will be given as acceleration versustime. Damping ratio of 0.05 (5%) and a scale factor of 32.2 areused. The values of accelerations and corresponding times aregiven in the last 3 lines.



LOAD COMBINATION 31 0.75 2 0.75

Above command identifies a combination load ( case no. 3) with atitle. The second line provides the load cases and their respectivefactors used for the load combination. Note that the static load (1)is combined with dynamic load (2) to form load comb 3.

LOAD COMBINATION 41 0.75 2 -0.75

The above command is similar to that defined earlier except thatthe dynamic load values are added with a negative effect. Note thatthe forces produced by the dynamic analysis are in absolutenumbers. Therefore for design purpose, it is necessary to make aload combination with a negative effect.

PERFORM ANALYSIS PRINT MODE SHAPES

This command makes the program proceed with analysis. ThePRINT command will cause the program to print mode shapes.



LOAD LIST 1 3 4SELECT ALL

All members will be selected from steel tables. Only load cases 1, 3and 4 will be considered.

FINISH






1. STAAD PLANE RESPONSE SPECTRUM ANALYSIS 2. UNIT FEET KIPS 3. JOINT COORDINATES 4. 1 0 0 0 ; 2 20 0 0 5. 3 0 10 0 ; 4 20 10 0 6. 5 0 20 0 ; 6 20 20 0 7. MEMBER INCIDENCES 8. 1 1 3 ; 2 2 4 ; 3 3 5 ; 4 4 6 9. 5 3 4 ; 6 5 6 10. MEMBER PROPERTIES AMERICAN 11. 1 TO 4 TA ST W10X33 12. 5 TA ST W12X40 13. 6 TA ST W8X40 14. SUPPORTS 15. 1 2 FIXED 16. UNIT INCH 17. CONSTANTS 18. E 29000. ALL 19. DEN 0.000283 ALL 20. CUT OFF MODE SHAPE 2 21. *LOAD 1 WILL BE STATIC LOAD 22. UNIT FEET 23. LOAD 1 DEAD AND LIVE LOADS 24. SELFWEIGHT Y -1.0 25. MEMBER LOADS 26. 5 CON GY -5.0 6.0 27. 5 CON GY -7.5 10.0 28. 5 CON GY -5.0 14.0 29. 5 6 UNI Y -1.5 30. * NEXT LOAD WILL BE RESPONSE SPECTRUM LOAD 31. * WITH MASSES PROVIDED IN TERMS OF LOAD. 32. LOAD 2 SEISMIC LOADING 33. SELFWEIGHT X 1.0 34. SELFWEIGHT Y 1.0 35. MEMBER LOADS 36. 5 CON GX 5.0 6.0 37. 5 CON GY 5.0 6.0 38. 5 CON GX 7.5 10.0 39. 5 CON GY 7.5 10.0 40. 5 CON GX 5.0 14.0 41. 5 CON GY 5.0 14.0 42. SPECTRUM CQC X 1.0 ACC DAMP 0.05 SCALE 32.2 43. 0.03 1.00 ; 0.05 1.35 44. 0.1 1.95 ; 0.2 2.80 45. 0.5 2.80 ; 1.0 1.60 46. LOAD COMBINATION 3 47. 1 0.75 2 0.75 48. LOAD COMBINATION 4 49. 1 0.75 2 -0.75 50. PERFORM ANALYSIS PRINT MODE SHAPES





CALCULATED FREQUENCIES FOR LOAD CASE 2

MODE FREQUENCY(CYCLES/SEC) PERIOD(SEC)

1 4.535 0.22052 2 16.382 0.06104

MODE SHAPES -----------

JOINT MODE X-TRANS Y-TRANS Z-TRANS X-ROTAN Y-ROTAN Z-ROTAN

1 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 2 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 3 1 -0.13410 -0.00063 0.00000 0.00000 0.00000 0.00068 2 0.04893 -0.00291 0.00000 0.00000 0.00000 0.00147 4 1 -0.13410 0.00063 0.00000 0.00000 0.00000 0.00068 2 0.04892 0.00291 0.00000 0.00000 0.00000 0.00147 5 1 -0.20002 -0.00074 0.00000 0.00000 0.00000 0.00029 2 -0.54844 -0.00438 0.00000 0.00000 0.00000 0.00396 6 1 -0.20002 0.00074 0.00000 0.00000 0.00000 0.00029 2 -0.54843 0.00438 0.00000 0.00000 0.00000 0.00396

MASS PARTICIPATION FACTORS IN PERCENT BASE SHEAR IN KIPS -------------------------------------- ------------------

MODE X Y Z SUMM-X SUMM-Y SUMM-Z X Y Z

1 98.63 0.00 0.00 98.627 0.000 0.000 55.50 0.00 0.00 2 1.25 0.00 0.00 99.873 0.000 0.000 0.37 0.00 0.00 --------------------------- TOTAL SHEAR 55.50 0.00 0.00




1 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 3 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 4 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 2 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 3 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 4 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 3 1 -0.00150 -0.01706 0.00000 0.00000 0.00000 -0.00244 2 1.27997 0.00601 0.00000 0.00000 0.00000 0.00647 3 0.95885 -0.00829 0.00000 0.00000 0.00000 0.00302 4 -0.96110 -0.01731 0.00000 0.00000 0.00000 -0.00668 4 1 0.00150 -0.01706 0.00000 0.00000 0.00000 0.00244 2 1.27997 0.00601 0.00000 0.00000 0.00000 0.00647 3 0.96110 -0.00829 0.00000 0.00000 0.00000 0.00668 4 -0.95885 -0.01731 0.00000 0.00000 0.00000 -0.00302 5 1 0.00314 -0.02370 0.00000 0.00000 0.00000 -0.00240 2 1.90920 0.00703 0.00000 0.00000 0.00000 0.00282 3 1.43425 -0.01250 0.00000 0.00000 0.00000 0.00031 4 -1.42954 -0.02304 0.00000 0.00000 0.00000 -0.00391 6 1 -0.00314 -0.02370 0.00000 0.00000 0.00000 0.00240 2 1.90920 0.00703 0.00000 0.00000 0.00000 0.00282 3 1.42954 -0.01250 0.00000 0.00000 0.00000 0.00391 4 -1.43425 -0.02304 0.00000 0.00000 0.00000 -0.00031




SUPPORT REACTIONS -UNIT KIPS FEET STRUCTURE TYPE = PLANE -----------------


1 1 4.60 40.21 0.00 0.00 0.00 -14.64 2 27.75 14.10 0.00 0.00 0.00 160.90 3 24.26 40.73 0.00 0.00 0.00 109.69 4 -17.37 19.58 0.00 0.00 0.00 -131.65 2 1 -4.60 40.21 0.00 0.00 0.00 14.64 2 27.75 14.10 0.00 0.00 0.00 160.90 3 17.37 40.73 0.00 0.00 0.00 131.65 4 -24.26 19.58 0.00 0.00 0.00 -109.69

MEMBER END FORCES STRUCTURE TYPE = PLANE ----------------- ALL UNITS ARE -- KIPS FEET


1 1 1 40.21 -4.60 0.00 0.00 0.00 -14.64 3 -39.88 4.60 0.00 0.00 0.00 -31.33 2 1 14.10 27.75 0.00 0.00 0.00 160.90 3 14.10 27.75 0.00 0.00 0.00 116.62 3 1 40.73 17.37 0.00 0.00 0.00 109.69 3 -40.49 -17.37 0.00 0.00 0.00 -110.96 4 1 19.58 -24.26 0.00 0.00 0.00 -131.65 3 -19.33 24.26 0.00 0.00 0.00 63.97

2 1 2 40.21 4.60 0.00 0.00 0.00 14.64 4 -39.88 -4.60 0.00 0.00 0.00 31.33 2 2 14.10 27.75 0.00 0.00 0.00 160.90 4 14.10 27.75 0.00 0.00 0.00 116.62 3 2 40.73 24.26 0.00 0.00 0.00 131.65 4 -40.49 -24.26 0.00 0.00 0.00 -63.97 4 2 19.58 -17.37 0.00 0.00 0.00 -109.69 4 -19.33 17.37 0.00 0.00 0.00 110.96

3 1 3 15.73 -8.88 0.00 0.00 0.00 -44.54 5 -15.40 8.88 0.00 0.00 0.00 -44.27 2 3 2.39 2.28 0.00 0.00 0.00 2.54 5 2.39 2.28 0.00 0.00 0.00 23.83 3 3 13.59 -4.95 0.00 0.00 0.00 -31.50 5 -13.34 4.95 0.00 0.00 0.00 -51.08 4 3 10.00 -8.37 0.00 0.00 0.00 -35.31 5 -9.75 8.37 0.00 0.00 0.00 -15.33

4 1 4 15.73 8.88 0.00 0.00 0.00 44.54 6 -15.40 -8.88 0.00 0.00 0.00 44.27 2 4 2.39 2.28 0.00 0.00 0.00 2.54 6 2.39 2.28 0.00 0.00 0.00 23.83 3 4 13.59 8.37 0.00 0.00 0.00 35.31 6 -13.34 -8.37 0.00 0.00 0.00 15.33 4 4 10.00 4.95 0.00 0.00 0.00 31.50 6 -9.75 -4.95 0.00 0.00 0.00 51.08

5 1 3 -4.29 24.15 0.00 0.00 0.00 75.87 4 4.29 24.15 0.00 0.00 0.00 -75.87 2 3 0.00 11.59 0.00 0.00 0.00 115.93 4 0.00 11.59 0.00 0.00 0.00 115.93 3 3 -3.21 26.81 0.00 0.00 0.00 143.85 4 3.21 9.42 0.00 0.00 0.00 -143.85 4 3 -3.21 9.42 0.00 0.00 0.00 -30.05 4 3.21 26.81 0.00 0.00 0.00 30.05



6 1 5 8.88 15.40 0.00 0.00 0.00 44.27 6 -8.88 15.40 0.00 0.00 0.00 -44.27 2 5 0.00 2.38 0.00 0.00 0.00 23.84 6 0.00 2.38 0.00 0.00 0.00 23.84 3 5 6.66 13.34 0.00 0.00 0.00 51.08 6 -6.66 9.76 0.00 0.00 0.00 -51.08 4 5 6.66 9.76 0.00 0.00 0.00 15.33 6 -6.66 13.34 0.00 0.00 0.00 -15.33


52. LOAD LIST 1 3 4 53. PARAMETERS 54. CODE AISC 55. SELECT ALL


ALL UNITS ARE - KIPS FEET (UNLESS OTHERWISE NOTED)


1 ST W21 X50 PASS AISC- H1-3 0.964 4 19.58 C 0.00 -131.65 0.00 2 ST W21 X50 PASS AISC- H1-2 0.997 3 40.73 C 0.00 131.65 0.00 3 ST W12 X30 PASS AISC- H1-3 0.834 3 13.34 C 0.00 51.08 10.00 4 ST W12 X26 PASS AISC- H1-3 0.993 4 9.75 C 0.00 -51.08 10.00 5 ST W14 X61 PASS AISC- H2-1 0.876 3 3.21 T 0.00 143.85 0.00 6 ST W8X 35 PASS AISC- H1-3 0.968 3 6.66 C 0.00 51.08 0.00

56. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****





NOTES




Moving load is applied on a bridge deck. This type of loadingcreates enormous number of load cases resulting in plenty of outputto be sorted. To avoid looking into a lot of output, the maximumforce envelope is requested for a few specific members.

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STAAD FLOOR A SIMPLE BRIDGE DECK

Every input has to start with the word STAAD. The word FLOORsignifies that the structure is a floor structure and the geometry isdefined through X and Z axis.

UNITS FEET KIPS


JOINT COORDINATES1 0 0 0 6 25 0 0R 5 0 0 30

Joint number followed by X, Y and Z coordinates are providedabove. Note that, since this is a floor structure, the Y coordinatesare given as all zeros. First line generates joints 1 through 6. Arepeat command (R), repeats these 6 coordinates 5 times with X, Yand Z increments of 0 0 30 respectively. With the repeat (R)command, the coordinates of the next 30 joints are generated byrepeating the pattern of the coordinates of the first 6 joints 5 timeswith X, Y and Z increments of 0,0 & 30 respectively.

MEMBER INCIDENCES1 1 7 67 1 2 11R A 4 11 656 31 32 60

Defines the members by the joints they are connected to. Fourthnumber indicates the final member number upto which they will begenerated. Repeat all (abbreviated as R A) will create members byrepeating the member incidence pattern of the previous 11members. The number of repetitions to be carried out is providedafter the R A command and the member increment and jointincrement are defined as 11 and 6 respectively. The fifth line ofinput defines the member incidences for members 56 to 60.

MEMBER PROPERTIES



1 TO 60 TA ST W12X26

All member properties are from AISC steel table. The word STstands for standard single section.

SUPPORTS1 TO 6 31 TO 36 PINNED

The above joints are listed as pinned supports meaning that nomoments will be carried by these supports.

UNITS INCHCONSTANTSE 29000. ALLDEN 0.283E-3 ALL

CONSTANT command initiates input for material constants like E(modulus of elasticity) DENsity etc. Length unit is changed fromFT to INCH to facilitate the input for E etc.

UNIT FEET KIPDEFINE MOVING LOADTYPE 1 LOAD 20. 20. 10. DISTANCE 10. 5. WIDTH 10.0

Moving loads are defined above in FEET KIP units. The typenumber (1) is a label for identification of the moving load. 3 loads( 20 20 10) are specified with the LOAD command. The spacingbetween them is specified after the DISTANCE command. TheWIDTH is the spacing in the other direction, that is, the movingload is acting in 2 rows as in the case of a truck load.

LOAD 1

Load case 1 is initiated.

SELF Y -1.0

The above command will apply the selfweight of the structure inthe global Y direction with a -1.0 factor. Since the global Y is inthe upward direction, this load will act downwards.




LOAD GENERATION 10TYPE 1 7.5 0. 0. ZI 10.

The above command will generate 10 load cases for the Type Iload. For the first of these load cases, the X, Y and Z location ofthe reference load (see section 6.30.1 of the User's Manual) havebeen specified after the command TYPE 1. A Z increment of 10feet will be used to generate the remaining 9 load cases.

PERFORM ANALYSIS PRINT LOAD

This command makes the program proceed with the analysis andprint all the generated load cases as member loads.

PRINT MAXFORCE ENVELOP LIST 3 41 42

Maximum force envelope consisting of all the forces at every tenthpoints of the members will be printed.

FINISH





1. STAAD FLOOR A SIMPLE BRIDGE DECK 2. UNITS FEET KIPS 3. JOINT COORDINATES 4. 1 0 0 0 6 25 0 0 5. R 5 0 0 30 6. MEMBER INCIDENCES 7. 1 1 7 6 8. 7 1 2 11 9. R A 4 11 6 10. 56 31 32 60 11. MEMBER PROPERTIES AMERICAN 12. 1 TO 60 TA ST W12X26 13. SUPPORTS 14. 1 TO 6 31 TO 36 PINNED 15. UNITS INCH 16. CONSTANTS 17. E 29000. ALL 18. DEN 0.283E-3 ALL 19. UNIT FEET KIP 20. DEFINE MOVING LOAD 21. TYPE 1 LOAD 20. 20. 10. DISTANCE 10. 5. WIDTH 10. 22. LOAD 1 23. SELF Y -1.0 24. LOAD GENERATION 10 25. TYPE 1 7.5 0. 0. ZI 10. 26. PERFORM ANALYSIS PRINT LOAD



LOADING 1 LOAD 1 -----------

SELFWEIGHT Y -1.000

ACTUAL WEIGHT OF THE STRUCTURE = 27.278 KIP

LOADING 2 -----------



8 -20.000 GY 2.50 10 -20.000 GY 2.50 3 -10.000 GY 10.00 2 -10.000 GY 10.00 5 -10.000 GY 10.00 4 -10.000 GY 10.00 3 -5.000 GY 15.00 2 -5.000 GY 15.00 5 -5.000 GY 15.00 4 -5.000 GY 15.00




LOADING 3 -----------



3 -10.000 GY 10.00 2 -10.000 GY 10.00 5 -10.000 GY 10.00 4 -10.000 GY 10.00 3 -10.000 GY 20.00 2 -10.000 GY 20.00 5 -10.000 GY 20.00 4 -10.000 GY 20.00 3 -5.000 GY 25.00 2 -5.000 GY 25.00 5 -5.000 GY 25.00 4 -5.000 GY 25.00

LOADING 4 -----------




LOADING 5 -----------






LOADING 6 -----------




LOADING 7 -----------




LOADING 8 -----------







LOADING 9 -----------




LOADING 10 -----------




LOADING 11 -----------





27. PRINT MAXFORCE ENVELOP LIST 3 41 42



MEMBER FORCE ENVELOPE ---------------------

ALL UNITS ARE KIP FEET

MAX AND MIN FORCE VALUES AMONGST ALL SECTION LOCATIONS

MEMB FY/ DIST LD MZ/ DIST LD FZ DIST LD MY DIST LD FX DIST LD

3 MAX 18.03 0.00 3 0.02 0.00 4 0.00 0.00 1 0.00 0.00 1 0.00 0.00 1 MIN -6.97 27.50 3 -373.87 30.00 5 0.00 30.00 11 0.00 30.00 11 0.00 30.00 11

41 MAX 16.33 0.00 10 6.82 5.00 5 0.00 0.00 1 0.00 0.00 1 0.00 0.00 1 MIN -4.08 5.00 11 -109.08 2.50 10 0.00 5.00 11 0.00 5.00 11 0.00 5.00 11

42 MAX 0.06 0.00 1 6.84 4.58 5 0.00 0.00 1 0.00 0.00 1 0.00 0.00 1 MIN -0.07 5.00 1 -99.90 5.00 10 0.00 5.00 11 0.00 5.00 11 0.00 5.00 11

********** END OF FORCE ENVELOPE FROM INTERNAL STORAGE **********

28. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****





NOTES




Calculation of displacements at intermediate points of members ofa plane frame is demonstrated in this example.

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The dashed line represents the deflected shape of the structure. Theshape considers displacements of twelve intermediate points of themembers.





STAAD PLANE TEST FOR SECTION DISPLACEMENT

Every input has to start with the word STAAD. The word PLANEsignifies that the structure is a plane frame structure and thegeometry is defined through X and Y axis.

UNIT KIP FEET


JOINT COORDINATES1 0. 0. ; 2 0. 15. ; 3 20. 15. ; 4 20. 0.

Joint number followed by X, Y and Z coordinates are providedabove. Note that, since this is a plane structure, the Z coordinatesneed not be provided. Semicolon signs (;) are used as lineseparators, that is, multiple data can be input in one line.

MEMBER INCIDENCE1 1 2 ; 2 2 3 ; 3 3 4


MEMBER PROPERTY1 3 TABLE ST W8X182 TABLE ST W12X26


UNIT INCHESCONSTANTSE 29000.0 ALL

CONSTANT command initiates input for material constants like E(modulus of elasticity) etc. Length unit is changed from FT toINCH to facilitate the input for E etc.




Joint 1 is a fixed support while joint 4 is pinned meaning nomoments will be carried by joint 4.

UNIT FTLOADING 1 DEAD + LIVE + WIND


JOINT LOAD2 FX 5.

Load 1 contains joint loads. FX indicates that the load is a force inthe global X direction.

MEMBER LOAD2 UNI GY -3.0

Load 1 contains member loads also. GY indicates that the load is inthe global Y direction. The word UNI stands for uniformlydistributed load.

PERFORM ANALYSIS


PRINT MEMBER FORCES

Above PRINT command is self-explanatory.

** FOLLOWING PRINT COMMAND WILL PRINT* DISPLACEMENTS OF THE MEMBERS* CONSIDERING EVERY TWELVETH INTERMEDIATE* POINTS (THAT IS TOTAL 13 POINTS). THESE* DISPLACEMENTS ARE MEASURED IN GLOBAL X* Y Z COORDINATE SYSTEM AND THE VALUES* ARE FROM ORIGINAL COORDINATES (THAT IS* UNDEFLECTED) OF CORRESPONDING TENTH* POINTS.** MAX LOCAL DISPLACEMENT IS ALSO PRINTED.* THE LOCATION OF MAXIMUM INTERMEDIATE




* DISPLACEMENT IS DETERMINED. THIS VALUE IS* MEASURED FROM ABOVE LOCATION TO THE* STRAIGHT LINE JOINING START AND END* JOINTS OF THE DEFLECTED MEMBER.*PRINT SECTION DISPLACEMENT

Above PRINT command is explained in the comment lines.

FINISH





1. STAAD PLANE TEST FOR SECTION DISPLACEMENT 2. UNIT KIP FEET 3. JOINT COORDINATES 4. 1 0. 0. ; 2 0. 15. ; 3 20. 15. ; 4 20. 0. 5. MEMBER INCIDENCE 6. 1 1 2 ; 2 2 3 ; 3 3 4 7. MEMBER PROPERTY AMERICAN 8. 1 3 TABLE ST W8X18 9. 2 TABLE ST W12X26 10. UNIT INCHES 11. CONSTANTS 12. E 29000.0 ALL 13. SUPPORT 14. 1 FIXED ; 4 PINNED 15. UNIT FT 16. LOADING 1 DEAD + LIVE + WIND 17. JOINT LOAD 18. 2 FX 5. 19. MEMBER LOAD 20. 2 UNI GY -3.0 21. PERFORM ANALYSIS



22. PRINT MEMBER FORCES



1 1 1 27.37 0.97 0.00 0.00 0.00 22.44 2 -27.37 -0.97 0.00 0.00 0.00 -7.89

2 1 2 4.03 27.37 0.00 0.00 0.00 7.89 3 -4.03 32.63 0.00 0.00 0.00 -60.45

3 1 3 32.63 4.03 0.00 0.00 0.00 60.45 4 -32.63 -4.03 0.00 0.00 0.00 0.00


23. * 24. * FOLLOWING PRINT COMMAMND WILL PRINT DISPLACEMENTS 25. * OF THE MEMBERS CONSIDERING EVERY TENTH INTERMEDIATE 26. * POINTS (THAT IS TOTAL 11 POINTS). THESE DISPLACEMENTS 27. * ARE MEASURED IN GLOBAL X Y Z COORDINATE SYSTEM AND 28. * THE VALUES ARE FROM ORIGINAL COORDINATES (THAT IS 29. * UNDEFLECTED) OF CORRESPONDING TENTH POINTS. 30. *




31. * MAX LOCAL DISPLACEMENT IS ALSO PRINTED. THE LOCATION 32. * OF THE MAXIMUM INTERMEDIATE DISPLACEMENT IS DETERMINED. 33. * THIS VALUE IS MEASURED FROM ABOVE LOCATION TO THE STRAIGHT 34. * LINE JOINING START AND END JOINTS OF THE DEFLECTED MEMBER. 35. * 36. PRINT SECTION DISPLACEMENT

MEMBER SECTION DISPLACEMENTS ---------------------------- UNIT =INCHES FOR FPS AND CM FOR METRICS/SI SYSTEM

MEMB LOAD GLOBAL X,Y,Z DISPL FROM START TO END JOINTS AT 1/12TH PTS

1 1 0.0000 0.0000 0.0000 0.0171 -0.0027 0.0000 0.0661 -0.0054 0.0000 0.1453 -0.0081 0.0000 0.2527 -0.0108 0.0000 0.3865 -0.0135 0.0000 0.5450 -0.0162 0.0000 0.7263 -0.0188 0.0000 0.9286 -0.0215 0.0000 1.1501 -0.0242 0.0000 1.3888 -0.0269 0.0000 1.6431 -0.0296 0.0000 1.9112 -0.0323 0.0000


2 1 1.9112 -0.0323 0.0000 1.9108 -0.3902 0.0000 1.9105 -0.7220 0.0000 1.9101 -1.0008 0.0000 1.9098 -1.2065 0.0000 1.9094 -1.3258 0.0000 1.9090 -1.3520 0.0000 1.9087 -1.2854 0.0000 1.9083 -1.1329 0.0000 1.9079 -0.9082 0.0000 1.9076 -0.6316 0.0000 1.9072 -0.3306 0.0000 1.9068 -0.0385 0.0000


3 1 1.9068 -0.0385 0.0000 2.0675 -0.0353 0.0000 2.1448 -0.0321 0.0000 2.1464 -0.0289 0.0000 2.0797 -0.0257 0.0000 1.9525 -0.0225 0.0000 1.7722 -0.0192 0.0000 1.5464 -0.0160 0.0000 1.2827 -0.0128 0.0000 0.9888 -0.0096 0.0000 0.6721 -0.0064 0.0000 0.3403 -0.0032 0.0000 0.0000 0.0000 0.0000


************ END OF SECT DISPL RESULTS ***********

37. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****





A space frame is analysed as per the current UBC Code.Combination load cases are used to combine the lateral and verticaleffects.

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STAAD SPACE EXAMPLE PROBLEM FOR UBC LOAD

Every input has to start with the word STAAD. The word SPACEsignifies that the structure is a space frame.

UNIT FEET KIP


JOINT COORDINATES1 0 0 0 4 30 0 0REPEAT 3 0 0 10REPEAT ALL 3 0 10 0

The X, Y and Z coordinates of the joints are specified here. First,coordinates of joints 1 through 4 are generated by taking advantageof the fact that they are equally spaced. Then, this pattern isREPEATed 3 times with a Z increment of 10 feet for eachrepetition to generate joints 5 to 16. The REPEAT ALL commandwill then repeat 3 times, the pattern of joints 1 to 16 to generatejoints 17 to 64.

MEMBER INCIDENCES* beams in x direction101 17 18 103104 21 22 106107 25 26 109110 29 30 112REPEAT ALL 2 12 16* beams in z direction201 17 21 204205 21 25 208209 25 29 212REPEAT ALL 2 12 16* columns301 1 17 348

Defines the members by the joints they are connected to. Followingthe specification of incidences for members 101 to 112, theREPEAT ALL command command is used to repeat the pattern andgenerate incidences for members 113 through 136. A similar logicis used in specification of incidences of members 201 through 212



and generation of incidences for members 213 to 236. Finally,members incidences of columns 301 to 348 are specified.

UNIT INCHMEMBER PROPERTIES101 TO 136 201 TO 236 PRIS YD 15 ZD 15301 TO 348 TA ST W18X35

The beam members have prismatic member property specification(YD & ZD) while the columns (members 301 to 348) have theirproperties called from the built-in AISC steel table.

CONSTANTE STEEL MEMB 301 TO 348E CONCRETE MEMB 101 TO 136 201 TO 236DENSITY STEEL MEMB 301 TO 348DENSITY CONCRETE MEMB 101 TO 136 201 TO 236

In the specification of material constants, the default built-invalues are used. The user may see these values with the help of thecommand PRINT MATERIAL PROPERTIES following the abovecommands.

SUPPORT1 TO 16 FIXED

Indicates the joints where the supports are located as well as thetype of support restraints.

UNIT FEETDEFINE UBC LOADZONE 0.2 I 1.0 RWX 9 RWZ 9 S 1.5 CT 0.032SELFWEIGHTJOINT WEIGHT17 TO 48 WEIGHT 2.549 TO 64 WEIGHT 1.25

There are two stages in the command specification of the UBCloads. The first stage is initiated with the command DEFINE UBCLOAD. Here the parameters such as Zone factor, Importancefactor, site coefficient for soil characteristics etc. and, the verticalloads from which the base shear will be calculated are specified.




The vertical loads may be specified in the form of selfweight, jointweights and/or member weights. Member weights are not shown inthis example. It is important to note that these vertical loads areused purely in the determination of the horizontal base shear only.In other words, the structure is not analysed for these verticalloads.

LOAD 1UBC LOAD X 0.75SELFWEIGHT Y -1.0JOINT LOADS17 TO 48 FY -2.549 TO 64 FY -1.25LOAD 2UBC LOAD Z 0.75SELFWEIGHT Y -1.0JOINT LOADS17 TO 48 FY -2.549 TO 64 FY -1.25

This is the second stage in which the UBC load is applied with thehelp of load case number, corresponding direction and a factor bywhich generated horizontal loads needs to be multiplied. Alongwith the UBC load, deadweight is also added to the same load case.Since we will be doing second-order PDELTA analysis, it isimportant that we add horizontal and vertical loads in the sameload case.

PDELTA ANALYSIS PRINT LOAD DATA

We are requesting a second-order analysis by specifying PDELTAANALYSIS. PRINT LOAD DATA is used to print all the appliedand generated loadings. The UBC loadings will include 0.75 factoras specified before.

PRINT SUPPORT REACTIONSFINISH

The above commands are self-explanatory.




1. STAAD SPACE EXAMPLE PROBLEM FOR UBC LOAD 2. UNIT FEET KIP 3. JOINT COORDINATES 4. 1 0 0 0 4 30 0 0 5. REPEAT 3 0 0 10 6. REPEAT ALL 3 0 10 0 7. MEMBER INCIDENCES 8. * BEAMS IN X DIRECTION 9. 101 17 18 103 10. 104 21 22 106 11. 107 25 26 109 12. 110 29 30 112 13. REPEAT ALL 2 12 16 14. * BEAMS IN Z DIRECTION 15. 201 17 21 204 16. 205 21 25 208 17. 209 25 29 212 18. REPEAT ALL 2 12 16 19. * COLUMNS 20. 301 1 17 348 21. UNIT INCH 22. MEMBER PROPERTIES AMERICAN 23. 101 TO 136 201 TO 236 PRIS YD 15 ZD 15


24. 301 TO 348 TA ST W18X35 25. CONSTANT 26. E STEEL MEMB 301 TO 348 27. E CONCRETE MEMB 101 TO 136 201 TO 236 28. DENSITY STEEL MEMB 301 TO 348 29. DENSITY CONCRETE MEMB 101 TO 136 201 TO 236 30. SUPPORT 31. 1 TO 16 FIXED 32. UNIT FEET 33. DEFINE UBC LOAD 34. ZONE 0.2 I 1.0 RWX 9 RWZ 9 S 1.5 CT 0.032 35. SELFWEIGHT 36. JOINT WEIGHT 37. 17 TO 48 WEIGHT 2.5 38. 49 TO 64 WEIGHT 1.25 39. LOAD 1 40. UBC LOAD X 0.75 41. SELFWEIGHT Y -1.0 42. JOINT LOADS 43. 17 TO 48 FY -2.5 44. 49 TO 64 FY -1.25 45. LOAD 2 46. UBC LOAD Z 0.75 47. SELFWEIGHT Y -1.0 48. JOINT LOADS 49. 17 TO 48 FY -2.5 50. 49 TO 64 FY -1.25 51. PERFORM ANALYSIS PRINT LOAD DATA






LOADING 1 LOAD 1 -----------

SELFWEIGHT Y -1.000


JOINT LOAD - UNIT KIP FEET

JOINT FORCE-X FORCE-Y FORCE-Z MOM-X MOM-Y MOM-Z

17 0.00 -2.50 0.00 0.00 0.00 0.00 18 0.00 -2.50 0.00 0.00 0.00 0.00 19 0.00 -2.50 0.00 0.00 0.00 0.00 20 0.00 -2.50 0.00 0.00 0.00 0.00 21 0.00 -2.50 0.00 0.00 0.00 0.00 22 0.00 -2.50 0.00 0.00 0.00 0.00 23 0.00 -2.50 0.00 0.00 0.00 0.00 24 0.00 -2.50 0.00 0.00 0.00 0.00 25 0.00 -2.50 0.00 0.00 0.00 0.00 26 0.00 -2.50 0.00 0.00 0.00 0.00 27 0.00 -2.50 0.00 0.00 0.00 0.00 28 0.00 -2.50 0.00 0.00 0.00 0.00 29 0.00 -2.50 0.00 0.00 0.00 0.00 30 0.00 -2.50 0.00 0.00 0.00 0.00 31 0.00 -2.50 0.00 0.00 0.00 0.00 32 0.00 -2.50 0.00 0.00 0.00 0.00 33 0.00 -2.50 0.00 0.00 0.00 0.00 34 0.00 -2.50 0.00 0.00 0.00 0.00 35 0.00 -2.50 0.00 0.00 0.00 0.00 36 0.00 -2.50 0.00 0.00 0.00 0.00 37 0.00 -2.50 0.00 0.00 0.00 0.00 38 0.00 -2.50 0.00 0.00 0.00 0.00 39 0.00 -2.50 0.00 0.00 0.00 0.00 40 0.00 -2.50 0.00 0.00 0.00 0.00 41 0.00 -2.50 0.00 0.00 0.00 0.00 42 0.00 -2.50 0.00 0.00 0.00 0.00 43 0.00 -2.50 0.00 0.00 0.00 0.00 44 0.00 -2.50 0.00 0.00 0.00 0.00 45 0.00 -2.50 0.00 0.00 0.00 0.00 46 0.00 -2.50 0.00 0.00 0.00 0.00 47 0.00 -2.50 0.00 0.00 0.00 0.00 48 0.00 -2.50 0.00 0.00 0.00 0.00 49 0.00 -1.25 0.00 0.00 0.00 0.00 50 0.00 -1.25 0.00 0.00 0.00 0.00 51 0.00 -1.25 0.00 0.00 0.00 0.00 52 0.00 -1.25 0.00 0.00 0.00 0.00 53 0.00 -1.25 0.00 0.00 0.00 0.00 54 0.00 -1.25 0.00 0.00 0.00 0.00 55 0.00 -1.25 0.00 0.00 0.00 0.00 56 0.00 -1.25 0.00 0.00 0.00 0.00 57 0.00 -1.25 0.00 0.00 0.00 0.00 58 0.00 -1.25 0.00 0.00 0.00 0.00 59 0.00 -1.25 0.00 0.00 0.00 0.00 60 0.00 -1.25 0.00 0.00 0.00 0.00 61 0.00 -1.25 0.00 0.00 0.00 0.00 62 0.00 -1.25 0.00 0.00 0.00 0.00 63 0.00 -1.25 0.00 0.00 0.00 0.00 64 0.00 -1.25 0.00 0.00 0.00 0.00



LOADING 2 LOAD 2 -----------

SELFWEIGHT Y -1.000




17 0.00 -2.50 0.00 0.00 0.00 0.00 18 0.00 -2.50 0.00 0.00 0.00 0.00 19 0.00 -2.50 0.00 0.00 0.00 0.00 20 0.00 -2.50 0.00 0.00 0.00 0.00 21 0.00 -2.50 0.00 0.00 0.00 0.00 22 0.00 -2.50 0.00 0.00 0.00 0.00 23 0.00 -2.50 0.00 0.00 0.00 0.00 24 0.00 -2.50 0.00 0.00 0.00 0.00 25 0.00 -2.50 0.00 0.00 0.00 0.00 26 0.00 -2.50 0.00 0.00 0.00 0.00 27 0.00 -2.50 0.00 0.00 0.00 0.00 28 0.00 -2.50 0.00 0.00 0.00 0.00 29 0.00 -2.50 0.00 0.00 0.00 0.00 30 0.00 -2.50 0.00 0.00 0.00 0.00 31 0.00 -2.50 0.00 0.00 0.00 0.00 32 0.00 -2.50 0.00 0.00 0.00 0.00 33 0.00 -2.50 0.00 0.00 0.00 0.00 34 0.00 -2.50 0.00 0.00 0.00 0.00 35 0.00 -2.50 0.00 0.00 0.00 0.00 36 0.00 -2.50 0.00 0.00 0.00 0.00 37 0.00 -2.50 0.00 0.00 0.00 0.00 38 0.00 -2.50 0.00 0.00 0.00 0.00 39 0.00 -2.50 0.00 0.00 0.00 0.00 40 0.00 -2.50 0.00 0.00 0.00 0.00 41 0.00 -2.50 0.00 0.00 0.00 0.00 42 0.00 -2.50 0.00 0.00 0.00 0.00 43 0.00 -2.50 0.00 0.00 0.00 0.00 44 0.00 -2.50 0.00 0.00 0.00 0.00 45 0.00 -2.50 0.00 0.00 0.00 0.00 46 0.00 -2.50 0.00 0.00 0.00 0.00 47 0.00 -2.50 0.00 0.00 0.00 0.00 48 0.00 -2.50 0.00 0.00 0.00 0.00 49 0.00 -1.25 0.00 0.00 0.00 0.00 50 0.00 -1.25 0.00 0.00 0.00 0.00 51 0.00 -1.25 0.00 0.00 0.00 0.00 52 0.00 -1.25 0.00 0.00 0.00 0.00 53 0.00 -1.25 0.00 0.00 0.00 0.00 54 0.00 -1.25 0.00 0.00 0.00 0.00 55 0.00 -1.25 0.00 0.00 0.00 0.00 56 0.00 -1.25 0.00 0.00 0.00 0.00 57 0.00 -1.25 0.00 0.00 0.00 0.00 58 0.00 -1.25 0.00 0.00 0.00 0.00 59 0.00 -1.25 0.00 0.00 0.00 0.00 60 0.00 -1.25 0.00 0.00 0.00 0.00 61 0.00 -1.25 0.00 0.00 0.00 0.00 62 0.00 -1.25 0.00 0.00 0.00 0.00 63 0.00 -1.25 0.00 0.00 0.00 0.00 64 0.00 -1.25 0.00 0.00 0.00 0.00

********************************************************* * * * CALC/USED PERIOD FOR X UBC = 0.2485/ 0.2485 SEC * * C, C-ALT = 4.7436 , 2.7171, LOAD FACTOR = 0.750 * * UBC FACTOR V = 0.0611 X 285.53 = 17.45 KIP * * * *********************************************************




********************************************************* * * * CALC/USED PERIOD FOR Z UBC = 0.9868/ 0.9868 SEC * * C, C-ALT = 1.8917 , 2.7171, LOAD FACTOR = 0.750 * * UBC FACTOR V = 0.0604 X 285.53 = 17.24 KIP * * * *********************************************************

JOINT LATERAL LOAD (KIP ), LOAD - 1 ----- ------------ FACTOR - 0.750

17 FX 0.125 18 FX 0.154 19 FX 0.154 20 FX 0.125 21 FX 0.154 22 FX 0.182 23 FX 0.182 24 FX 0.154 25 FX 0.154 26 FX 0.182 27 FX 0.182 28 FX 0.154 29 FX 0.125 30 FX 0.154 31 FX 0.154 32 FX 0.125 * ----------- * TOTAL = 2.456 AT LEVEL 10.000 FEET *

33 FX 0.250 34 FX 0.307 35 FX 0.307 36 FX 0.250 37 FX 0.307 38 FX 0.364 39 FX 0.364 40 FX 0.307 41 FX 0.307 42 FX 0.364 43 FX 0.364 44 FX 0.307 45 FX 0.250 46 FX 0.307 47 FX 0.307 48 FX 0.250 * ----------- * TOTAL = 4.912 AT LEVEL 20.000 FEET * 49 FX 0.273 50 FX 0.357 51 FX 0.357 52 FX 0.273 53 FX 0.357 54 FX 0.442 55 FX 0.442 56 FX 0.357 57 FX 0.357 58 FX 0.442 59 FX 0.442 60 FX 0.357 61 FX 0.273 62 FX 0.357 63 FX 0.357 64 FX 0.273 * ----------- * TOTAL = 5.719 AT LEVEL 30.000 FEET *



JOINT LATERAL LOAD (KIP ), LOAD - 2 ----- ------------ FACTOR - 0.750

17 FZ 0.115 18 FZ 0.141 19 FZ 0.141 20 FZ 0.115 21 FZ 0.141 22 FZ 0.167 23 FZ 0.167 24 FZ 0.141 25 FZ 0.141 26 FZ 0.167 27 FZ 0.167 28 FZ 0.141 29 FZ 0.115 30 FZ 0.141 31 FZ 0.141 32 FZ 0.115 * ----------- * TOTAL = 2.259 AT LEVEL 10.000 FEET * 33 FZ 0.230 34 FZ 0.282 35 FZ 0.282 36 FZ 0.230 37 FZ 0.282 38 FZ 0.334 39 FZ 0.334 40 FZ 0.282 41 FZ 0.282 42 FZ 0.334 43 FZ 0.334 44 FZ 0.282 45 FZ 0.230 46 FZ 0.282 47 FZ 0.282 48 FZ 0.230 * ----------- * TOTAL = 4.518 AT LEVEL 20.000 FEET * 49 FZ 0.293 50 FZ 0.385 51 FZ 0.385 52 FZ 0.293 53 FZ 0.385 54 FZ 0.476 55 FZ 0.476 56 FZ 0.385 57 FZ 0.385 58 FZ 0.476 59 FZ 0.476 60 FZ 0.385 61 FZ 0.293 62 FZ 0.385 63 FZ 0.385 64 FZ 0.293 * ----------- * TOTAL = 6.153 AT LEVEL 30.000 FEET *








1 1 -0.60 12.07 0.01 0.05 0.00 4.31 2 0.11 11.63 -0.78 -3.99 0.00 -0.34 2 1 -0.90 17.34 0.01 0.05 0.00 5.24 2 0.01 14.97 -0.78 -3.99 0.00 -0.02 3 1 -0.92 17.10 0.01 0.05 0.00 5.29 2 -0.01 14.97 -0.78 -3.99 0.00 0.02 4 1 -0.82 15.69 0.01 0.05 0.00 5.00 2 -0.11 11.63 -0.78 -3.99 0.00 0.34 5 1 -0.62 16.63 0.00 -0.01 0.00 4.39 2 0.11 19.40 -0.82 -4.12 0.00 -0.34 6 1 -0.92 21.94 0.00 -0.01 0.00 5.32 2 0.01 22.74 -0.82 -4.13 0.00 -0.03 7 1 -0.93 21.69 0.00 -0.01 0.00 5.37 2 -0.01 22.74 -0.82 -4.13 0.00 0.03 8 1 -0.84 20.31 0.00 -0.01 0.00 5.08 2 -0.11 19.40 -0.82 -4.12 0.00 0.34 9 1 -0.62 16.63 0.00 0.01 0.00 4.39 2 0.11 17.54 -0.82 -4.11 0.00 -0.34 10 1 -0.92 21.94 0.00 0.01 0.00 5.32 2 0.01 20.88 -0.82 -4.12 0.00 -0.02 11 1 -0.93 21.69 0.00 0.01 0.00 5.37 2 -0.01 20.88 -0.82 -4.12 0.00 0.02 12 1 -0.84 20.31 0.00 0.01 0.00 5.08 2 -0.11 17.54 -0.82 -4.11 0.00 0.34 13 1 -0.60 12.07 -0.01 -0.05 0.00 4.31 2 0.11 16.12 -0.81 -4.08 0.00 -0.34 14 1 -0.90 17.34 -0.01 -0.05 0.00 5.24 2 0.01 19.47 -0.81 -4.08 0.00 -0.03 15 1 -0.92 17.10 -0.01 -0.05 0.00 5.29 2 -0.01 19.47 -0.81 -4.08 0.00 0.03 16 1 -0.82 15.69 -0.01 -0.05 0.00 5.00 2 -0.11 16.12 -0.81 -4.08 0.00 0.34


53. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****





A space frame is analyzed for loads generated using the built-inwind and floor load generation facilities.

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STAAD SPACE - WIND AND FLOOR LOAD GENERATION

This is a SPACE frame analysis problem. Every STAAD input hasto start with the command STAAD. The SPACE specification isused to denote a SPACE frame.

UNIT FEET KIP

The UNIT specification is used to specify the length and/or forceunits to be used.

JOINT COORDINATES1 0 0 02 10 0 03 21 0 04 0 0 105 10 0 106 0 0 207 10 0 208 21 0 20REPEAT ALL 2 0 12 0

The JOINT COORDINATE specification is used to specify the X,Y and Z coordinates of the JOINTs. Note that the REPEAT ALLcommand has been used to generate JOINTs for two higher levelseach with a Y increment of 12 ft.

MEMBER INCIDENCES* Columns1 1 9 16* Beams in the X direction17 9 10 1819 12 1320 14 15 2122 17 18 2324 20 2125 22 23 26* Beams in the Z direction27 9 12 ; 28 12 14 ; 29 10 13 ; 30 13 15 ; 31 11 1632 17 20 ; 33 20 22 ; 34 18 21 ; 35 21 23 ; 36 19 24



The MEMBER INCIDENCE specification is used for specifyingMEMBER connectivities.

UNIT INCHMEMBER PROPERTIES1 TO 16 TA ST W21X5017 TO 26 TA ST W18X3527 TO 36 TA ST W14X90

All member properties are specified from the built-in AISC steeltable. Three different section types have been used.

CONSTANTE STEEL ALLDENSITY STEEL ALL

The CONSTANT specification is used to specify materialproperties. In this case, the default values have been used.

SUPPORT1 TO 8 FIXED BUT MX MZ

The SUPPORTs of the structure are defined through the SUPPORTspecification. Here all the supports are FIXED with RELEASESspecified in the MX (rotation about global X-axis) and MZ(rotation about global Z-axis) directions.

UNIT FEETDEFINE WIND LOADTYPE 1INTENSITY 0.1 0.15 HEIGHT 12 24EXPOSURE 0.90 YRANGE 11 13EXPOSURE 0.85 JOINT 17 20 22

This problem utilizes the automatic wind load generation facilities.The input specification is done in two stages. The first stage isinitiated above through the DEFINE WIND LOAD command. Thebasic parameters of the WIND loading are specified here. Allvalues need to be provided in the current UNIT system. EachWIND loading is identified with a TYPE specification which maybe used subsequently to specify load cases.




Two different wind intensities (0.1 Kips/sq. ft and 0.15 Kips/sq. ft)are specified for two different height zones (0 to 12 ft. and 12 to 24ft.). The EXPOSURE specification is used to define the exposurefactors for joints subjected to wind loading. In this case, twodifferent exposure factors are specified. The first EXPOSUREspecification specifies the exposure factor as 0.9 for all jointswithin the height range (defined as global Y-range) of 11 ft. - 13 ft.The second EXPOSURE specification specifies the exposure factoras 0.85 for joints 17, 20 and 22. Note that in the EXPOSUREFACTOR specification, the joints may be specified directly orthrough a vertical range specification.

LOAD 1 WIND LOAD IN X-DIRECTIONWIND LOAD X 1.2 TYPE 1

This is the second stage of input specification for the wind loadgeneration. The WIND LOAD command is used to specify theWIND LOADING in a particular lateral direction. In this case,WIND loading TYPE 1, defined previously, is being applied in theglobal X-direction with a positive multiplying factor of 1.2 .

LOAD 2 FLOOR LOAD @ Y = 12 FT AND 24 FTFLOOR LOADYRANGE 11.9 12.1 FLOAD -0.45 XRANGE 0.0 10.0 ZRANGE0.0 20.0YRANGE 11.9 12.1 FLOAD -0.25 XRANGE 10.0 21.0 ZRANGE0.0 20.0YRANGE 23.9 24.1 FLOAD -0.25

The FLOOR LOAD specification is used to specify a uniformlydistributed floor loading on a defined area of the structure. TheYRANGE, XRANGE and ZRANGE specifications are used todefine the area of the structure on which the load needs to beapplied. The FLOAD specification is used to specify the value ofthe load per unit area. All values need to be provided in the currentUNIT system. For example, in the first line in the above FLOORLOAD specification, on the plane lying in the vertical YRANGE11.9-12.1, an uniformly distributed load of 0.45 Kip/sq. ft. isapplied on an area bound by the global XRANGE of 0.0-10.0 ft



and ZRANGE of 0.0-20.0 ft.. The -0.45 and the -0.25 signify thatthe load is in the negative global Y direction.

The program will identify all members lying within the specifiedarea and distribute the applied loading as MEMBER LOADS onthese members based on two-way load distribution. The PRINTLOAD DATA command used with PERFORM ANALYSISspecification below will generate a listing of the MEMBERLOADings resulting out of the FLOOR LOAD distribution.

PERFORM ANALYSIS PRINT LOAD DATAPRINT SUPPORT REACTIONFINISH





1. STAAD SPACE 2. UNIT FEET KIP 3. JOINT COORDINATES 4. 1 0 0 0 5. 2 10 0 0 6. 3 21 0 0 7. 4 0 0 10 8. 5 10 0 10 9. 6 0 0 20 10. 7 10 0 20 11. 8 21 0 20 12. REPEAT ALL 2 0 12 0 13. MEMBER INCIDENCES 14. * COLUMNS 15. 1 1 9 16 16. * BEAMS IN THE X DIRECTION 17. 17 9 10 18 18. 19 12 13 19. 20 14 15 21 20. 22 17 18 23 21. 24 20 21 22. 25 22 23 26 23. * BEAMS IN THE Z DIRECTION 24. 27 9 12 ; 28 12 14 ; 29 10 13 ; 30 13 15 ; 31 11 16 25. 32 17 20 ; 33 20 22 ; 34 18 21 ; 35 21 23 ; 36 19 24 26. UNIT INCH 27. MEMBER PROPERTIES AMERICAN 28. 1 TO 16 TA ST W21X50 29. 17 TO 26 TA ST W18X35 30. 27 TO 36 TA ST W14X90 31. CONSTANT 32. E STEEL ALL 33. DENSITY STEEL ALL 34. SUPPORT 35. 1 TO 8 FIXED BUT MX MZ 36. UNIT FEET 37. DEFINE WIND LOAD 38. TYPE 1 39. INTENSITY 0.1 0.15 HEIGHT 12 24 40. EXPOSURE 0.90 YRANGE 11 13 41. EXPOSURE 0.85 JOINT 17 20 22 42. LOAD 1 WIND LOAD IN X-DIRECTION 43. WIND LOAD X 1.2 TYPE 1 44. LOAD 2 FLOOR LOAD AT Y = 12FT @ 24FT 45. FLOOR LOAD 46. YRANGE 11.9 12.1 FLOAD 0.45 XRANGE 0.0 10.0 ZRANGE 0.0 20.0 47. YRANGE 11.9 12.1 FLOAD 0.25 XRANGE 10.0 21.0 ZRANGE 0.0 20.0 48. YRANGE 23.9 24.1 FLOAD 0.25 49. PERFORM ANALYSIS PRINT LOAD DATA





LOADING 1 WIND LOAD IN X-D -----------



1 3.60 0.00 0.00 0.00 0.00 0.00 4 7.20 0.00 0.00 0.00 0.00 0.00 6 3.60 0.00 0.00 0.00 0.00 0.00 9 8.10 0.00 0.00 0.00 0.00 0.00 12 16.20 0.00 0.00 0.00 0.00 0.00 14 8.10 0.00 0.00 0.00 0.00 0.00 17 4.59 0.00 0.00 0.00 0.00 0.00 20 9.18 0.00 0.00 0.00 0.00 0.00 22 4.59 0.00 0.00 0.00 0.00 0.00

LOADING 2 FLOOR LOAD AT Y = 12FT @ 24FT -----------



19 0.088 GY 0.42 19 0.264 GY 0.97 19 0.439 GY 1.58 19 0.615 GY 2.20 19 0.791 GY 2.82 19 0.967 GY 3.45 19 1.143 GY 4.07 19 1.318 GY 4.69 19 1.318 GY 5.31 19 1.143 GY 5.93 19 0.967 GY 6.55 19 0.791 GY 7.18 19 0.615 GY 7.80 19 0.439 GY 8.42 19 0.264 GY 9.03 19 0.088 GY 9.58 29 1.318 GY 5.31 29 1.143 GY 5.93 29 0.967 GY 6.55 29 0.791 GY 7.18 29 0.615 GY 7.80 29 0.439 GY 8.42 29 0.264 GY 9.03 29 0.088 GY 9.58 29 0.088 GY 0.42 29 0.264 GY 0.97 29 0.439 GY 1.58 29 0.615 GY 2.20 29 0.791 GY 2.82 29 0.967 GY 3.45 29 1.143 GY 4.07 29 1.318 GY 4.69 17 1.318 GY 5.31 17 1.143 GY 5.93 17 0.967 GY 6.55 17 0.791 GY 7.18 17 0.615 GY 7.80 17 0.439 GY 8.42 17 0.264 GY 9.03 17 0.088 GY 9.58 17 0.088 GY 0.42 17 0.264 GY 0.97 17 0.439 GY 1.58 17 0.615 GY 2.20




17 0.791 GY 2.82 17 0.967 GY 3.45 17 1.143 GY 4.07 17 1.318 GY 4.69 27 0.088 GY 0.42 27 0.264 GY 0.97 27 0.439 GY 1.58 27 0.615 GY 2.20 27 0.791 GY 2.82 27 0.967 GY 3.45 27 1.143 GY 4.07 27 1.318 GY 4.69 27 1.318 GY 5.31 27 1.143 GY 5.93 27 0.967 GY 6.55 27 0.791 GY 7.18 27 0.615 GY 7.80 27 0.439 GY 8.42 27 0.264 GY 9.03 27 0.088 GY 9.58 20 0.088 GY 0.42 20 0.264 GY 0.97 20 0.439 GY 1.58 20 0.615 GY 2.20 20 0.791 GY 2.82 20 0.967 GY 3.45 20 1.143 GY 4.07 20 1.318 GY 4.69 20 1.318 GY 5.31 20 1.143 GY 5.93 20 0.967 GY 6.55 20 0.791 GY 7.18 20 0.615 GY 7.80 20 0.439 GY 8.42 20 0.264 GY 9.03 20 0.088 GY 9.58 30 1.318 GY 5.31 30 1.143 GY 5.93 30 0.967 GY 6.55 30 0.791 GY 7.18 30 0.615 GY 7.80 30 0.439 GY 8.42 30 0.264 GY 9.03 30 0.088 GY 9.58 30 0.088 GY 0.42 30 0.264 GY 0.97 30 0.439 GY 1.58 30 0.615 GY 2.20 30 0.791 GY 2.82 30 0.967 GY 3.45 30 1.143 GY 4.07 30 1.318 GY 4.69 19 1.318 GY 5.31 19 1.143 GY 5.93 19 0.967 GY 6.55 19 0.791 GY 7.18 19 0.615 GY 7.80 19 0.439 GY 8.42 19 0.264 GY 9.03 19 0.088 GY 9.58 19 0.088 GY 0.42 19 0.264 GY 0.97 19 0.439 GY 1.58 19 0.615 GY 2.20 19 0.791 GY 2.82 19 0.967 GY 3.45 19 1.143 GY 4.07 19 1.318 GY 4.69 28 0.088 GY 0.42



22 0.439 GY 7.18 22 0.342 GY 7.80 22 0.244 GY 8.42 22 0.146 GY 9.03 22 0.049 GY 9.58 22 0.049 GY 0.42 22 0.146 GY 0.97 22 0.244 GY 1.58 22 0.342 GY 2.20 22 0.439 GY 2.82 22 0.537 GY 3.45 22 0.635 GY 4.07 22 0.732 GY 4.69 32 0.049 GY 0.42 32 0.146 GY 0.97 32 0.244 GY 1.58 32 0.342 GY 2.20 32 0.439 GY 2.82 32 0.537 GY 3.45 32 0.635 GY 4.07 32 0.732 GY 4.69 32 0.732 GY 5.31 32 0.635 GY 5.93 32 0.537 GY 6.55 32 0.439 GY 7.18 32 0.342 GY 7.80 32 0.244 GY 8.42 32 0.146 GY 9.03 32 0.049 GY 9.58 34 0.059 GY 0.46 34 0.177 GY 1.07 34 0.295 GY 1.74 34 0.414 GY 2.42 34 0.532 GY 3.11 34 0.650 GY 3.79 34 0.768 GY 4.48 34 0.886 GY 5.16 34 0.773 GY 5.78 34 0.773 GY 6.34 34 0.773 GY 6.91 34 0.773 GY 7.47 34 0.773 GY 8.03 34 0.773 GY 8.59 34 0.773 GY 9.16 34 0.773 GY 9.72 35 0.773 GY 0.28 35 0.773 GY 0.84 35 0.773 GY 1.41 35 0.773 GY 1.97 35 0.773 GY 2.53 35 0.773 GY 3.09 35 0.773 GY 3.66 35 0.773 GY 4.22 35 0.886 GY 4.84 35 0.768 GY 5.52 35 0.650 GY 6.21 35 0.532 GY 6.89 35 0.414 GY 7.58 35 0.295 GY 8.26 35 0.177 GY 8.93 35 0.059 GY 9.54 26 0.059 GY 0.46 26 0.177 GY 1.07 26 0.295 GY 1.74 26 0.414 GY 2.42 26 0.532 GY 3.11 26 0.650 GY 3.79 26 0.768 GY 4.48



35 0.342 GY 7.80 35 0.244 GY 8.42 35 0.146 GY 9.03 35 0.049 GY 9.58 35 0.049 GY 0.42 35 0.146 GY 0.97 35 0.244 GY 1.58 35 0.342 GY 2.20 35 0.439 GY 2.82 35 0.537 GY 3.45 35 0.635 GY 4.07 35 0.732 GY 4.69 24 0.732 GY 5.31 24 0.635 GY 5.93 24 0.537 GY 6.55 24 0.439 GY 7.18 24 0.342 GY 7.80 24 0.244 GY 8.42 24 0.146 GY 9.03 24 0.049 GY 9.58 24 0.049 GY 0.42 24 0.146 GY 0.97 24 0.244 GY 1.58 24 0.342 GY 2.20 24 0.439 GY 2.82 24 0.537 GY 3.45 24 0.635 GY 4.07 24 0.732 GY 4.69 33 0.049 GY 0.42 33 0.146 GY 0.97 33 0.244 GY 1.58 33 0.342 GY 2.20 33 0.439 GY 2.82 33 0.537 GY 3.45 33 0.635 GY 4.07 33 0.732 GY 4.69 33 0.732 GY 5.31 33 0.635 GY 5.93 33 0.537 GY 6.55 33 0.439 GY 7.18 33 0.342 GY 7.80 33 0.244 GY 8.42 33 0.146 GY 9.03 33 0.049 GY 9.58





1 1 -9.35 -16.19 0.00 0.00 -0.01 0.00 2 -0.30 -15.64 -0.03 0.00 0.00 0.00 2 1 -7.26 2.51 0.01 0.00 -0.01 0.00 2 0.15 -29.58 -0.04 0.00 0.00 0.00 3 1 -5.56 14.18 0.00 0.00 0.00 0.00 2 0.24 -27.42 -0.17 0.00 0.00 0.00 4 1 -14.05 -19.36 0.00 0.00 0.00 0.00 2 -0.74 -38.55 0.00 0.00 0.00 0.00 5 1 -6.78 18.36 0.00 0.00 0.00 0.00 2 0.56 -66.16 0.00 0.00 0.00 0.00 6 1 -9.35 -16.19 0.00 0.00 0.01 0.00 2 -0.30 -15.64 0.03 0.00 0.00 0.00 7 1 -7.26 2.51 -0.01 0.00 0.01 0.00 2 0.15 -29.58 0.04 0.00 0.00 0.00 8 1 -5.56 14.18 0.00 0.00 0.00 0.00 2 0.24 -27.42 0.17 0.00 0.00 0.00





51. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****





Dynamic Analysis (Time History) is performed for a 3 span beamwith concentrated and distributed masses. The structure issubjected to "forcing function" and "ground motion" loading. Themaxima of the joint displacements, member end forces and supportreactions are determined.




STAAD PLANE EXAMPLE FOR TIME HISTORY ANALYSIS

Every input file has to start with the word STAAD. The wordPLANE signifies that the structure is a plane frame.

UNITS FEET KIP

Specifies the units to be used.

JOINT COORDINATES1 0.0 0.0 0.02 0.0 3.5 0.03 0.0 7.0 0.04 0.0 10.5 0.0

Joint number followed by the X, Y and Z coordinates are specifiedabove.

MEMBER INCIDENCES1 1 2 3

Incidences of members 1 to 3 are specified above.

UNIT INCHMEMBER PROPERTIES1 2 3 PRIS AX 3.0 IZ 240.0

All the members have "PRISMATIC" property specification. Sincethis is a PLANE frame, Area of cross section "AX", and Moment ofInertia "IZ" about the Z axis are adequate for the analysis.

SUPPORTS1 4 PINNED

Joints 1 to 4 all have pinned supports.

CONSTANTSE 14000 ALLDENSITY 0.0868E-3 ALL

The material constants defined include Young's Modulus "E", anddensity.



DEFINE TIME HISTORYTYPE 1 FORCE0.0 -0.0001 0.5 0.0449 1.0 0.2244 1.5 0.2244 2.0 0.6731 2.5 -0.6731TYPE 2 ACCELERATION0.0 0.001 0.5 -7.721 1.0 -38.61 1.5 -38.61 2.0 -115.82 2.5 115.82ARRIVAL TIMES0.0DAMPING 0.075

There are 2 stages in the command specification required for a timehistory analysis. The first stage is defined above. First thecharacteristics of the time varying load are provided. The loadingtype may be a forcing function (vibrating machinery) or groundmotion (earthquake). The former is input in the form of time-forcepairs while the latter is in the form of time-acceleration pairs.Following this data, all possible arrival times for these loads onthe structure are also specified as well as the modal damping ratio.Note that only one value for damping for the entire structure maybe specified.

UNIT FEETLOAD 1 STATIC LOADMEMBER LOAD1 2 3 UNI GX 0.5

Load case 1 above is a static load.

LOAD 2 TIME HISTORY LOADSELFWEIGHT X 1.0SELFWEIGHT Y 1.0JOINT LOAD2 3 FX 2.5TIME LOAD2 3 FX 1 1GROUND MOTION X 2 1

This is the second stage in the command specification for timehistory analysis. This involves the application of the time varyingload on the structure. The masses that constitute the mass matrix ofthe structure are specified in the form of selfweight and joint load.Following that, both the "TIME LOAD" and "GROUND




MOTION" are applied simultaneously. The user must note that thisexample is only for illustration purposes and that it may not benecessary for both a "TIME FUNCTION" and a "GROUNDMOTION" to act on the structure at the same time. However, onlyone load case involving time history can be applied in oneanalysis.

PERFORM ANALYSIS

The above command initiates the analysis process.

UNIT INCHPRINT JOINT DISPLACEMENTS

The joint displacements are calculated for every time step. Themaximum value of the displacement for every joint is thenextracted from this joint displacement history and printed usingthe above command.

UNIT FEETPRINT MEMBER FORCES

The member forces are calculated for every time step. Themaximum value of the force for every member is then extractedfrom this member force history and printed using the abovecommand.

PRINT SUPPORT REACTION

The support reactions are obtained directly from the member forcesobtained in the previous command.

FINISH




1. STAAD PLANE EXAMPLE FOR TIME HISTORY ANALYSIS 2. UNITS FEET KIP 3. JOINT COORDINATES 4. 1 0.0 0.0 0.0 5. 2 0.0 3.5 0.0 6. 3 0.0 7.0 0.0 7. 4 0.0 10.5 0.0 8. MEMBER INCIDENCES 9. 1 1 2 3 10. UNIT INCH 11. MEMBER PROPERTIES 12. 1 2 3 PRIS AX 3.0 IZ 240.0 13. SUPPORTS 14. 1 4 PINNED 15. CONSTANTS 16. E 14000 ALL 17. DENSITY 0.0868E-3 ALL 18. DEFINE TIME HISTORY 19. TYPE 1 FORCE 20. 0.0 -0.0001 0.5 0.0449 1.0 0.2244 1.5 0.2244 2.0 0.6731 2.5 -0.6731 21. TYPE 2 ACCELERATION 22. 0.0 0.001 0.5 -7.721 1.0 -38.61 1.5 -38.61 2.0 -115.82 2.5 115.82 23. ARRIVAL TIMES 24. 0.0 25. DAMPING 0.075 26. UNIT FEET 27. LOAD 1 STATIC LOAD 28. MEMBER LOAD 29. 1 2 3 UNI GX 0.5 30. LOAD 2 TIME HISTORY LOAD 31. SELFWEIGHT X 1.0 32. SELFWEIGHT Y 1.0 33. JOINT LOAD 34. 2 3 FX 2.5 35. TIME LOAD 36. 2 3 FX 1 1 37. GROUND MOTION X 2 1 38. PERFORM ANALYSIS





1 14.565 0.06866 2 56.409 0.01773 3 946.005 0.00106




MASS PARTICIPATION FACTORS IN PERCENT --------------------------------------

MODE X Y Z SUMM-X SUMM-Y SUMM-Z

1 99.94 0.00 0.00 99.939 0.000 0.000 2 0.00 0.00 0.00 99.939 0.000 0.000 3 0.00 0.01 0.00 99.939 0.000 0.000

39. UNIT INCH 40. PRINT JOINT DISPLACEMENTS



1 1 0.00000 0.00000 0.00000 0.00000 0.00000 -0.00103 2 0.00000 0.00000 0.00000 0.00000 0.00000 -0.00075 2 1 0.03537 0.00000 0.00000 0.00000 0.00000 -0.00050 2 0.02631 0.00000 0.00000 0.00000 0.00000 -0.00038 3 1 0.03537 0.00000 0.00000 0.00000 0.00000 0.00050 2 0.02631 0.00000 0.00000 0.00000 0.00000 0.00038 4 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.00103 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00075


41. UNIT FEET 42. PRINT MEMBER FORCES



1 1 1 0.00 2.63 0.00 0.00 0.00 0.00 2 0.00 -0.88 0.00 0.00 0.00 6.13 2 1 0.00 1.43 0.00 0.00 0.00 0.00 2 0.00 -1.43 0.00 0.00 0.00 5.01

2 1 2 0.00 0.87 0.00 0.00 0.00 -6.13 3 0.00 0.88 0.00 0.00 0.00 6.13 2 2 0.00 0.00 0.00 0.00 0.00 -5.01 3 0.00 0.00 0.00 0.00 0.00 5.01

3 1 3 0.00 -0.88 0.00 0.00 0.00 -6.13 4 0.00 2.63 0.00 0.00 0.00 0.00 2 3 0.00 -1.43 0.00 0.00 0.00 -5.01 4 0.00 1.43 0.00 0.00 0.00 0.00





1 1 -2.63 0.00 0.00 0.00 0.00 0.00 2 1.43 0.00 0.00 0.00 0.00 0.00 4 1 -2.63 0.00 0.00 0.00 0.00 0.00 2 1.43 0.00 0.00 0.00 0.00 0.00




44. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****





NOTES




The usage of User Provided Steel Tables is illustrated in thisexample for the analysis and design of a plane frame.

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STAAD PLANE EXAMPLE FOR USER TABLE

Every input file has to start with the command STAAD. ThePLANE command is used to designate the structure as a planeframe.

UNIT FT KIP

The UNIT command sets the length and force units to be used.

JOINT COORDINATES1 0. 0. ; 2 30 0 ; 3 0 20 0 6 30 20 07 0 35 ; 8 30 35 ; 9 7.5 35 ; 10 22.5 35.11 15 35 ; 12 5. 38. ; 13 25 38 ; 14 10 41 ; 15 20 4116 15 44

The above command is used to provide joint coordinates for thevarious joints of the structure. The cartesian system is being usedhere. The data consists of the joint numberfollowed by global X and Y coordinates. Note that for a spaceframe, the Z coordinate(s) need to be provided also. In the aboveinput, semicolon (;) signs are used as line separators. This allowsthe user to provide multiple data on one line of input.

MEMBER INCIDENCES1 1 3 ; 2 3 7 ; 3 2 6 ; 4 6 8 ; 5 3 46 4 5 ; 7 5 6 ; 8 7 12 ; 9 12 1410 14 16 ; 11 15 16 ; 12 13 15 ; 13 8 1314 9 12 ; 15 9 14 ; 16 11 14 ; 17 11 1518 10 15 ; 19 10 13 ; 20 7 921 9 11 ; 22 10 11 ; 23 8 10

The above data set contains the member incidence information orthe joint connectivity data for each member. This completes thegeometry of the structure.

UNIT INCHSTART USER TABLE



This command is utilized to set up an User Provided steel table.All user provided steel tables must start with this command.

TABLE 1

Each table needs an unique numerical identification. The abovecommand starts setting up Table no. 1. Any number between 1 and50 may be used as the table number. For multiple tables, thenumber need not be sequential. Upto four tables may be specifiedper run.

WIDE FLANGE

This command is used to specify the section-type as WIDEFLANGE in this table. Note that several section-types (WIDEFLANGE, CHANNEL, ANGLE, TEE etc.) are available forspecification.

W14X308.85 13.84 .27 6.73 .385 291. 19.6 .38 4.0 4.1W21X6218.3 20.99 .4 8.24 .615 1330 57.5 1.83 0.84 7.0W14X10932. 14.32 .525 14.605 .86 1240 447 7.12 7.52 16.

The above data set is used to specify the properties of three wideflange sections. Note that the data for each section consists of twoparts. In the first line, the section-name is provided. The user isallowed to provide any section name within seven characters. Thesecond line contains the section properties required for theparticular section-type. Each section-type requires a certain numberof data (area of cross-section, depth, moment of inertias etc.)provided in a certain order. For example, in this case, for wideflanges ten different properties are required. For detailedinformation on the various properties required for the differentsection-types and their order of specification, refer to Section 5.19in the STAAD/Pro Technical Reference Manual. Note that allrequired properties for the particular section-type must beprovided.

TABLE 2




ANGLESL252552.5 2.5 .3125 .489 0 0L404044 4 .25 .795 0 0

The above command and data lines set up another user providedtable consisting of angle sections.

END

This command signifies the end of the user provided table. All userprovided table related input must be terminated with this command.

MEMBER PROPERTIES1 3 4 UPT 1 W14X1092 UPT 1 W14X30 ; 5 6 7 UPT 1 W21X628 TO 13 UPT 1 W14X3014 TO 23 UPT 2 L40404

In the above command lines, the member properties are beingprovided from the user provided tables created before. Thecommand segment UPT signifies that the properties are from theuser provided table. This is followed by the table number and thenthe section name as specified in the user provided table. Note thatmember properties are being specified fromboth tables.

MEMBER TRUSS14 TO 23

The above command is used to designate members 14 to 23 as trussmembers.

MEMBER RELEASE5 START MZ

The MEMBER RELEASE command is used to release the MZmoment at the start joint of member no. 5.

UNIT INCH



This command resets the current length unit to inches.

CONSTANTSE 29000. ALLDEN 0.000283 ALLBETA 90.0 MEMB 3 4

The above command set is used to specify modulus of elasticity,density and beta angle values for various members.

UNIT FT

The length unit is reset to feet using this command.


The above command set is used to designate supports. Here, joint 1is designated as a fixed support and joint 2 is designated as apinned support.

LOADING 1 DEAD AND LIVE LOADSELFWEIGHT Y -1.0JOINT LOAD4 5 FY -15. ; 11 FY -35.MEMB LOAD8 TO 13 UNI Y -0.9 ; 6 UNI GY -1.2

The above command set is used to specify the loadings on thestructure. In this case, only one load case is being used. Selfweightis specified on the entire structure. Joint loads and member loadsare specified on some joints and members.

PERFORM ANALYSIS

This command causes the program to execute the analysis at thispoint.

PARAMETERNSF 0.85 ALLKY 1.2 MEMB 3 4




The above commands are used to specify parameters for steeldesign.

SELECT MEMBER 3 6 9 19

This command will perform selection of members per the AISC(American Institute of Steel Construction) steel design code. Notethat, for each member, the member selection will be performedfrom the table that was originally used for the specification of themember property. In this case, the selection will be from therespective user tables from which the properties were provided. Itmay be noted that properties may be provided (and selection maybe performed) from built-in steel tables and user provided tables inthe same problem.

FINISH





1. STAAD PLANE EXAMPLE FOR USER TABLE 2. UNIT FT KIP 3. JOINT COORDINATES 4. 1 0. 0. ; 2 30 0 ; 3 0 20 0 6 30 20 0 5. 7 0 35 ; 8 30 35 ; 9 7.5 35 ; 10 22.5 35. 6. 11 15 35 ; 12 5. 38. ; 13 25 38 ; 14 10 41 ; 15 20 41 7. 16 15 44 8. MEMBER INCIDENCES 9. 1 1 3 ; 2 3 7 ; 3 2 6 ; 4 6 8 ; 5 3 4 10. 6 4 5 ; 7 5 6 ; 8 7 12 ; 9 12 14 11. 10 14 16 ; 11 15 16 ; 12 13 15 ; 13 8 13 12. 14 9 12 ; 15 9 14 ; 16 11 14 ; 17 11 15 13. 18 10 15 ; 19 10 13 ; 20 7 9 14. 21 9 11 ; 22 10 11 ; 23 8 10 15. START USER TABLE 16. TABLE 1 17. WIDE FLANGE 18. W14X30 19. 8.85 13.84 .27 6.73 .385 291. 19.6 .38 4.0 4.1 20. W21X62 21. 18.3 20.99 .4 8.24 .615 1330 57.5 1.83 0.84 7.0 22. W14X109 23. 32. 14.32 .525 14.605 .86 1240 447 7.12 7.52 16. 24. TABLE 2 25. ANGLES 26. L25255 27. 2.5 2.5 .3125 .489 0 0 28. L40404 29. 4 4 .25 .795 0 0 30. END 31. MEMBER PROPERTIES 32. 1 3 4 UPT 1 W14X109 33. 2 UPT 1 W14X30 ; 5 6 7 UPT 1 W21X62 34. 8 TO 13 UPT 1 W14X30 35. 14 TO 23 UPT 2 L40404 36. MEMBER TRUSS 37. 14 TO 23 38. MEMBER RELEASE 39. 5 START MZ 40. UNIT INCH 41. CONSTANTS 42. E 29000 ALL 43. DEN 0.000283 ALL 44. BETA 90.0 MEMB 3 4 45. UNIT FT 46. SUPPORT 47. 1 FIXED ; 2 PINNED 48. LOADING 1 DEAD AND LIVE LOAD 49. SELFWEIGHT Y -1.0 50. JOINT LOAD 51. 4 5 FY -15. ; 11 FY -35. 52. MEMB LOAD 53. 8 TO 13 UNI Y -0.9 ; 6 UNI GY -1.2 54. PERFORM ANALYSIS






55. PARAMETER 56. CODE AISC 57. NSF 0.85 ALL 58. KY 1.2 MEMB 3 4 59. SELECT MEMB 3 6 9 19




3 ST W14X109 PASS AISC- H1-3 0.376 1 57.34 C -36.02 0.00 20.00 6 ST W21X62 PASS AISC- H2-1 0.826 1 3.83 T 0.00 -185.92 0.00 9 ST W14X30 PASS AISC- H1-2 0.850 1 37.74 C 0.00 -54.32 5.83 19 ST L25255 PASS AISC- H1-1 0.199 1 3.94 C 0.00 0.00 0.00

60. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****





This is an example which demonstrates the calculation of principalstresses on a finite element.

� ��

� ��

� � �

� �

� �

� � � �

�

��

� �

��

��

�

�

Fixed Supports at Joints 1, 2, 3, 4, 5, 9, 13Load intensity = 1 pound/in2 in - Y direction





STAAD SPACE SAMPLE CALCULATION FOR* ELEMENT STRESSES

Every input has to start with the word STAAD. The word SPACEsignifies that the structure is a space frame. (3-D structure)

UNIT KIP FEET


JOINT COORDINATES1 0 0 0 4 3 0 0REPEAT 3 0 0 1

Joint number followed by X, Y and Z coordinates are providedabove. The REPEAT command is used to generate coordinates ofjoints 5 to 16 based on the pattern of joints 1 to 4.

ELEMENT INCIDENCE1 1 5 6 2 TO 3REPEAT 2 3 4

Element connectivities of elements 1 to 3 are defined first, basedon which the connectivities of elements 4 to 9 are generated.

UNIT INCHELEMENT PROPERTIES1 TO 9 THICK 1.0

Elements 1 to 9 have a thickness of 1 inch.

CONSTANTSE CONCRETE ALL

Modulus of Elasticity of all the elements is that of the built-indefault value for concrete.

SUPPORT1 TO 4 5 9 13 FIXED

"Fixed support" conditions exist at the above mentioned joints.



UNIT POUNDLOAD 1ELEMENT LOAD1 TO 9 PRESSURE -1.0

A uniform pressure of 1 pound/sq.in. is applied on all the elementsin the negative local Z direction.

PERFORM ANALYSIS

The above command makes the program proceed with the analysis.

PRINT SUPPORT REACTION

The above command is self-explanatory.

PRINT ELEMENT FORCES LIST 4

Element forces at the centroid of the element are printed using theabove command. The output includes printing of principal stressesin addition to the membrane stresses, shear stresses and bendingmoments about local axes.

FINISH





1. STAAD SPACE SAMPLE CALCULATION FOR 2. * ELEMENT STRESSES 3. UNIT KIP FEET 4. JOINT COORDINATES 5. 1 0 0 0 4 3 0 0 6. REPEAT 3 0 0 1 7. ELEMENT INCIDENCE 8. 1 1 5 6 2 TO 3 9. REPEAT 2 3 4 10. UNIT INCH 11. ELEMENT PROPERTIES 12. 1 TO 9 THICK 1.0 13. CONSTANTS 14. E CONCRETE ALL 15. SUPPORT 16. 1 TO 4 5 9 13 FIXED 17. UNIT POUND 18. LOAD 1 19. ELEMENT LOAD 20. 1 TO 9 PRESSURE -1.0 21. PERFORM ANALYSIS




SUPPORT REACTIONS -UNIT POUN INCH STRUCTURE TYPE = SPACE -----------------


1 1 0.00 -13.19 0.00 -7.36 0.00 7.36 2 1 0.00 69.16 0.00 -872.90 0.00 -21.88 3 1 0.00 305.42 0.00 -2886.48 0.00 64.74 4 1 0.00 280.02 0.00 -2158.50 0.00 -880.65 5 1 0.00 69.16 0.00 21.88 0.00 872.90 9 1 0.00 305.42 0.00 -64.74 0.00 2886.48 13 1 0.00 280.02 0.00 880.65 0.00 2158.50


23. PRINT ELEMENT FORCES LIST 4



ELEMENT FORCES FORCE,LENGTH UNITS= POUN INCH -------------- FORCE OR STRESS = FORCE/WIDTH/THICK, MOMENT = FORCE-LENGTH/WIDTH


4 1 10.77 -10.18 24.61 88.55 33.95 591.68 591.68 0.00 0.00 0.00 TOP : SMAX= 619.26 SMIN= 59.68 TMAX= 279.79 ANGLE= -23.4 BOTT: SMAX= -59.68 SMIN= -619.26 TMAX= 279.79 ANGLE= -23.4


24. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****





Calculation of principal stresses for element 4

Calculations are presented for the top surface only.

FX = 0.0 pound/inch2

FY = 0.0 pound/inch2

FXY = 0.0 pound/inch2

MX = 24.61 pound-inch/inchMY = 88.55 pound-inch/inchMXY = 33.95 pound-inch/inchS = 1/6t2 = 1/6*12 = 0.1667 in2 (Section Modulus)

σx = ��

�+ = +� �

��

� ��

�

�

= 147.63 pounds/in2

σy = ��

�+ = +� �

��

� ��

�

�

= 531.19 pounds/in2

τxy = ��

�+ = +� �

��

� ��

�

�

= 203.66 pounds/in2

� ��

��=

−+

�

�

�

� �σ στ

� �� =−

+�

��

��

� � � ��

= 279.74 pounds/in2

SMAX = � ��

� ��σ σ+

+�

= � � � �

��

��

+ +



= 619.15 pounds/in2

SMIN = � ��

� ��σ σ+

−�

= � � � �

��

��

+ −

= 59.67 pounds/in2

Anglexy

x y

=−

−1

2

21tan

τσ σ

=−

−1

2

2 20366

147 63 531191tan

* .

. .

= -23.36o




NOTES




The MESH GENERATION facility is utilized in this example tomodel a space frame consisting of a slab supported on fourcolumns.




This example illustrates the usage of the MESH GENERATIONfacility on a space frame consisting of a slab supported on 4columns.

STAAD SPACE

Every input file has to start with the word STAAD. The wordSPACE signifies that the structure is a space frame.

UNIT METER KNS

Specifies the units for length and force.

JOINT COORD1 0 0 0 ; 2 4 0 0 ; 3 0 0 4 ; 4 4 0 4REP ALL 1 0 3 0

The x, y and z coordinates of joints 1 to 8 are defined above. Whilethe coordinates of joints 1 to 4 are defined explicitly, thecoordinates for joints 5 to 8 are generated from those of joints 1 to4 using the REPEAT ALL facility.

MEMB INCI1 1 5 4

The incidences (connectivity descriptor) of member 1 is specifiedabove as 1 5 and those for members 2,3 and 4 are generated fromthose of member 1 by successive increments of 1 to the jointnumbers 1 and 5.

DEFINE MESHA JOINT 5B JOINT 6C JOINT 7D JOINT 8

The above 5 lines define a 4-noded SUPERELEMENT from whicha mesh of elements is to be generated. Note that instead ofelaborately defining the coordinates of the four nodes, we havetaken advantage of the fact that the coordinates of these joints (Ato D) have already been defined earlier. Thus joint A is the same as



joint 5 while joint D is the same as joint 8. Alternatively, we couldhave defined the superelement as

A 0 3 0 ; B 4 3 0 ; C 0 3 4 ; D 4 3 4

GENERATE ELEMENT TRIMESH ABDC 4 4

The above two commands are for the following purpose. First, weinitiate the mesh generation process by asking the program toGENERATE TRIangular ELEMENTs. Then, the superelement fromwhich the mesh is to be generated is specified as ABDC. The firstnumber 4 indicates the number of elements along the side AB. Thesecond number 4 indicates the number of elements along the sideBD. Thus, a total of 32 elements will be generated.

MEMB PROP1 TO 4 PRIS YD 0.4ELEMENT PROP5 TO 36 TH 0.2

In the above lines, the properties of the members and elements aredefined.

PRINT MEMB INFOPRINT ELEM INFOFINI

The above commands are self-explanatory.





1. STAAD SPACE 2. UNIT METER KNS 3. JOINT COORD 4. 1 0 0 0 ; 2 4 0 0 ; 3 0 0 4 ; 4 4 0 4 5. REP ALL 1 0 3 0 6. MEMB INCI 7. 1 1 5 4 8. DEFINE MESH 9. A JOINT 5 10. B JOINT 6 11. C JOINT 7 12. D JOINT 8 13. GENER ELEM TRI 14. MESH ABDC 4 4 15. MEMB PROP 16. 1 TO 4 PRIS YD 0.4 17. ELEMENT PROP 18. 5 TO 36 TH 0.2 19. PRINT MEMB INFO


MEMBER START END LENGTH BETA JOINT JOINT (METE) (DEG) RELEASES

1 1 5 3.000 0.00 2 2 6 3.000 0.00 3 3 7 3.000 0.00 4 4 8 3.000 0.00


20. PRINT ELEM INFO

ELEMENT INFORMATION -------------------

ELEMENT INCIDENCES THICK POISS E NO. (METE)

5 5 9 13 0 0.200 0.250 0.00 6 5 13 12 0 0.200 0.250 0.00 7 9 10 14 0 0.200 0.250 0.00 8 9 14 13 0 0.200 0.250 0.00 9 10 11 15 0 0.200 0.250 0.00 10 10 15 14 0 0.200 0.250 0.00 11 11 6 16 0 0.200 0.250 0.00 12 11 16 15 0 0.200 0.250 0.00 13 12 13 18 0 0.200 0.250 0.00 14 12 18 17 0 0.200 0.250 0.00 15 13 14 19 0 0.200 0.250 0.00 16 13 19 18 0 0.200 0.250 0.00 17 14 15 20 0 0.200 0.250 0.00 18 14 20 19 0 0.200 0.250 0.00 19 15 16 21 0 0.200 0.250 0.00



20 15 21 20 0 0.200 0.250 0.00 21 17 18 23 0 0.200 0.250 0.00 22 17 23 22 0 0.200 0.250 0.00 23 18 19 24 0 0.200 0.250 0.00 24 18 24 23 0 0.200 0.250 0.00 25 19 20 25 0 0.200 0.250 0.00 26 19 25 24 0 0.200 0.250 0.00 27 20 21 26 0 0.200 0.250 0.00 28 20 26 25 0 0.200 0.250 0.00 29 22 23 27 0 0.200 0.250 0.00 30 22 27 7 0 0.200 0.250 0.00 31 23 24 28 0 0.200 0.250 0.00 32 23 28 27 0 0.200 0.250 0.00 33 24 25 29 0 0.200 0.250 0.00 34 24 29 28 0 0.200 0.250 0.00 35 25 26 8 0 0.200 0.250 0.00 36 25 8 29 0 0.200 0.250 0.00

******************END OF ELEMENT INFO******************

21. FINI

*************** END OF STAAD-III ***************

**** DATE= TIME= ****





NOTES




This example generates the geometry of a cylindrical tank structureusing the cylindrical coordinate system.




This example creates a cylindrical tank made up of finite elements.The radial direction is in the XY plane and longitudinal direction isalong the Z-axis. Hence, the coordinates in the XY plane aregenerated using the cylindrical coordinate system.

STAAD SPACEUNIT KIP FEETJOINT COORD CYLINDRICAL

Above command instructs the program that the coordinate data thatfollows is in the cylindrical coordinate system (r,theta,z)

1 10 0 0 8 10 315 0

Joint 1 has an 'r' of 10 feet, theta of 0 degrees and Z of 0 ft. Joint 8has an 'r' of 10 feet, theta of 315 degrees and Z of 0 ft. The 315degrees angle is measured contrclockwise from the +ve direction ofthe X-axis. Joints 2 to 7 are generated by equal incrementation thecoordinate values between joints 1 and 8.

REPEAT 2 0 0 8.5

The REPEAT command is used to generate joints 9 through 24 byrepeating twice, the pattern of joints 1 to 8 at Z-increments of 8.5feet for each REPEAT.

PRINT JOINT COORD

The above command is used to print the coordinates of all thejoints in the cartesian coordinate system. Note that even though theinput data was in the cylindrical coordinate system, the output is inthe cartesian coordinate system.

ELEMENT INCIDENCES1 1 2 10 9 TO 7 1 18 8 1 9 16REPEAT ALL 1 8 8

The above 4 lines identify the element incidences of all 16elements. Incidences of element 1 are defined as 1 2 10 9.Incidences of element 2 is generated by incrementing the joint



numbers of element 1 by 1, incidences of element 3 is generatedby incrementing the incidences of element 2 by 1 and so on uptoelement 7. Incidences of element 8 too have been defined above as8 1 9 16. The REPEAT ALL command states that the pattern ofALL the elements defined by the previous 2 lines, namely elements1 to 8, must be REPEATED ONCE with an element numberincrement of 8 and a joint number increment of 8 to generateelements 9 through 16.

PRINT ELEMENT INFO

Above command is self-explanatory.

FINISH





1. STAAD SPACE 2. UNIT KIP FEET 3. JOINT COORD CYLINDRICAL 4. 1 10 0 0 8 10 315 0 5. REPEAT 2 0 0 8.5 6. PRINT JOINT COORD

JOINT COORDINATES ----------------- COORDINATES ARE FEET UNIT

JOINT X Y Z

1 10.000 0.000 0.000 2 7.071 7.071 0.000 3 0.000 10.000 0.000 4 -7.071 7.071 0.000 5 -10.000 0.000 0.000 6 -7.071 -7.071 0.000 7 0.000 -10.000 0.000 8 7.071 -7.071 0.000 9 10.000 0.000 8.500 10 7.071 7.071 8.500 11 0.000 10.000 8.500 12 -7.071 7.071 8.500 13 -10.000 0.000 8.500 14 -7.071 -7.071 8.500 15 0.000 -10.000 8.500 16 7.071 -7.071 8.500 17 10.000 0.000 17.000 18 7.071 7.071 17.000 19 0.000 10.000 17.000 20 -7.071 7.071 17.000 21 -10.000 0.000 17.000 22 -7.071 -7.071 17.000 23 0.000 -10.000 17.000 24 7.071 -7.071 17.000


7. ELEMENT INCIDENCES 8. 1 1 2 10 9 TO 7 1 1 9. 8 8 1 9 16 10. REPEAT ALL 1 8 8 11. PRINT ELEMENT INFO

ELEMENT INFORMATION -------------------

ELEMENT INCIDENCES THICK POISS E NO. (FEET)

1 1 2 10 9 0.000 0.250 0.00 2 2 3 11 10 0.000 0.250 0.00 3 3 4 12 11 0.000 0.250 0.00 4 4 5 13 12 0.000 0.250 0.00



5 5 6 14 13 0.000 0.250 0.00 6 6 7 15 14 0.000 0.250 0.00 7 7 8 16 15 0.000 0.250 0.00 8 8 1 9 16 0.000 0.250 0.00 9 9 10 18 17 0.000 0.250 0.00 10 10 11 19 18 0.000 0.250 0.00 11 11 12 20 19 0.000 0.250 0.00 12 12 13 21 20 0.000 0.250 0.00 13 13 14 22 21 0.000 0.250 0.00 14 14 15 23 22 0.000 0.250 0.00 15 15 16 24 23 0.000 0.250 0.00 16 16 9 17 24 0.000 0.250 0.00

******************END OF ELEMENT INFO******************

12. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****





NOTES




This example illustrates the modeling of tension-only membersusing the MEMBER TENSION command.




This example has been created to illustate the commandspecification for a structure with members capable of carryingtensile force only. It is important to note that the analysis can bedone for only 1 load case at a time. This is because, a particularmember may not necessarily be under tension for all the load cases.

STAAD PLANE

The input data is initiated with the word STAAD. This structure isa PLANE frame.

UNIT FEET KIP

Units for the commands to follow are defined above.

SET NL 2

This input file contains analysis for 2 primary load cases. Hence,the original structure geometry is restored after the first analysis.This restoration is done with the help of the CHANGE commandprovided below. Whenever a CHANGE command is used, the SETNL command above must also be provided to instruct the programthat there are multiple analyses involved and correspondingly,multiple load cases are to be expected.

JOINT COORDINATES1 0 0;2 0 10;3 0 20;4 15 20;5 15 10;6 15 0

Joint coordintes of joints 1 to 6 are defined above.

MEMBER INCIDENCES1 1 2 56 1 5;7 2 6;8 2 4;9 3 5;10 2 5

Incidences of members 1 to 10 are defined.

MEMBER TENSION6 TO 9

Members 6 to 9 are defined as TENSION members. Hence for eachload case, if during the analysis, any of the members 6 to 9 is foundto be carrying compressive force, it is disabled from the structureand the analysis is carried out again with the modified structure.



MEMBER PROPERTY1 TO 10 TA ST W12X26

All members are WIDE FLANGE sections whose properties areobtained from the built in AISC table.

UNIT INCHCONSTANTSE 29000.0 ALLDEN 0.000283 ALLSUPPORT1 PINNED6 PINNED

Above commands are self-explanatory.

LOAD 1JOINT LOAD2 FX 153 FX 10

Load 1 is defined above and consists of joint loads at joints 2 and3.

PERFORM ANALYSIS

An analysis is carried out for load case 1.

CHANGEMEMBER TENSION6 TO 9

One or more among the members 6 to 9 may have been disabled inthe above analysis. The CHANGE command restores the originalstructure to prepare it for the analysis for the next primary loadcase. The member tension command is specified to make themembers to be tension carrying members for the analysis.

LOAD 2JOINT LOAD4 FX -105 FX -15




Load case 2 is described above.


Load combination involves the algebraic addition of the results ofload cases 1 and 2, each with a multiplication factor of 1.0. Sincethis is a matter of simple addition/subtraction of numbers, aseparate analysis is not required for load combinations. But such anarithmetic operation can be triggered only when the programencounters a PERFORM ANALYSIS statement. Hence, it isgrouped alongwith LOAD 2.

PERFORM ANALYSISCHANGELOAD LIST 1 2 3PRINT ANALYSIS RESULTSFINI

Note that the CHANGE command is re-specified to re-activate themembers which have been switched off. The load list command isspecified to obtain results for all load cases. Above commands areself-explanatory.




1. STAAD PLANE 2. UNIT FEET KIP 3. SET NL 2 4. JOINT COORDINATES 5. 1 0 0 ; 2 0 10 ; 3 0 20 ; 4 15 20 ; 5 15 10 ; 6 15 0 6. MEMBER INCIDENCES 7. 1 1 2 5 8. 6 1 5 ; 7 2 6 ; 8 2 4 ; 9 3 5 ; 10 2 5 9. MEMBER TENSION 10. 6 TO 9 11. MEMBER PROPERTY AMERICAN 12. 1 TO 10 TA ST W12X26 13. UNIT INCH 14. CONSTANTS 15. E 29000.0 ALL 16. DEN 0.000283 ALL 17. SUPPORT 18. 1 PINNED 19. 6 PINNED 20. LOAD 1 21. JOINT LOAD 22. 2 FX 15 23. 3 FX 10 24. PERFORM ANALYSIS



25. CHANGE 26. MEMBER TENSION 27. 6 TO 9 28. LOAD 2 29. JOINT LOAD 30. 4 FX -10 31. 5 FX -15 32. LOAD COMBINATION 3 33. 1 1.0 2 1.0 34. PERFORM ANALYSIS 35. CHANGE 36. LOAD LIST 1 2 3 37. PRINT ANALYSIS RESULTS






1 1 0.00000 0.00000 0.00000 0.00000 0.00000 -0.00063 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00039 3 0.00000 0.00000 0.00000 0.00000 0.00000 -0.00023 2 1 0.06284 0.00373 0.00000 0.00000 0.00000 -0.00030 2 -0.04313 -0.01262 0.00000 0.00000 0.00000 0.00028 3 0.01971 -0.00889 0.00000 0.00000 0.00000 -0.00002 3 1 0.09720 0.00387 0.00000 0.00000 0.00000 -0.00018 2 -0.08926 -0.01613 0.00000 0.00000 0.00000 0.00029 3 0.00794 -0.01226 0.00000 0.00000 0.00000 0.00011 4 1 0.08926 -0.01613 0.00000 0.00000 0.00000 -0.00029 2 -0.09720 0.00387 0.00000 0.00000 0.00000 0.00018 3 -0.00794 -0.01226 0.00000 0.00000 0.00000 -0.00011 5 1 0.04313 -0.01262 0.00000 0.00000 0.00000 -0.00028 2 -0.06284 0.00373 0.00000 0.00000 0.00000 0.00030 3 -0.01971 -0.00889 0.00000 0.00000 0.00000 0.00002 6 1 0.00000 0.00000 0.00000 0.00000 0.00000 -0.00039 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00063 3 0.00000 0.00000 0.00000 0.00000 0.00000 0.00023

SUPPORT REACTIONS -UNIT KIP INCH STRUCTURE TYPE = PLANE -----------------


1 1 -24.91 -23.33 0.00 0.00 0.00 0.00 2 0.09 23.33 0.00 0.00 0.00 0.00 3 -24.82 0.00 0.00 0.00 0.00 0.00 6 1 -0.09 23.33 0.00 0.00 0.00 0.00 2 24.91 -23.33 0.00 0.00 0.00 0.00 3 24.82 0.00 0.00 0.00 0.00 0.00

MEMBER END FORCES STRUCTURE TYPE = PLANE ----------------- ALL UNITS ARE -- KIP INCH


1 1 1 -6.90 0.27 0.00 0.00 0.00 0.00 2 6.90 -0.27 0.00 0.00 0.00 31.91 2 1 23.33 -0.09 0.00 0.00 0.00 0.00 2 -23.33 0.09 0.00 0.00 0.00 -10.84 3 1 16.43 0.18 0.00 0.00 0.00 0.00 2 -16.43 -0.18 0.00 0.00 0.00 21.07

2 1 2 -0.25 0.21 0.00 0.00 0.00 6.42 3 0.25 -0.21 0.00 0.00 0.00 18.81 2 2 6.48 -0.44 0.00 0.00 0.00 -26.33 3 -6.48 0.44 0.00 0.00 0.00 -26.08 3 2 6.24 -0.23 0.00 0.00 0.00 -19.92 3 -6.24 0.23 0.00 0.00 0.00 -7.27

3 1 3 9.79 -0.25 0.00 0.00 0.00 -18.81 4 -9.79 0.25 0.00 0.00 0.00 -26.08 2 3 9.79 0.25 0.00 0.00 0.00 26.08 4 -9.79 -0.25 0.00 0.00 0.00 18.81 3 3 19.58 0.00 0.00 0.00 0.00 7.27 4 -19.58 0.00 0.00 0.00 0.00 -7.27

4 1 4 6.48 0.44 0.00 0.00 0.00 26.08 5 -6.48 -0.44 0.00 0.00 0.00 26.33 2 4 -0.25 -0.21 0.00 0.00 0.00 -18.81 5 0.25 0.21 0.00 0.00 0.00 -6.42 3 4 6.24 0.23 0.00 0.00 0.00 7.27 5 -6.24 -0.23 0.00 0.00 0.00 19.92



5 1 5 23.33 0.09 0.00 0.00 0.00 10.84 6 -23.33 -0.09 0.00 0.00 0.00 0.00 2 5 -6.90 -0.27 0.00 0.00 0.00 -31.91 6 6.90 0.27 0.00 0.00 0.00 0.00 3 5 16.43 -0.18 0.00 0.00 0.00 -21.07 6 -16.43 0.18 0.00 0.00 0.00 0.00

6 1 1 -29.62 0.00 0.00 0.00 0.00 0.00 5 29.62 0.00 0.00 0.00 0.00 0.00 2 1 0.00 0.00 0.00 0.00 0.00 0.00 5 0.00 0.00 0.00 0.00 0.00 0.00 3 1 -29.62 0.00 0.00 0.00 0.00 0.00 5 29.62 0.00 0.00 0.00 0.00 0.00

7 1 2 0.00 0.00 0.00 0.00 0.00 0.00 6 0.00 0.00 0.00 0.00 0.00 0.00 2 2 -29.62 0.00 0.00 0.00 0.00 0.00 6 29.62 0.00 0.00 0.00 0.00 0.00 3 2 -29.62 0.00 0.00 0.00 0.00 0.00 6 29.62 0.00 0.00 0.00 0.00 0.00

8 1 2 -11.24 0.00 0.00 0.00 0.00 0.00 4 11.24 0.00 0.00 0.00 0.00 0.00 2 2 0.00 0.00 0.00 0.00 0.00 0.00 4 0.00 0.00 0.00 0.00 0.00 0.00 3 2 -11.24 0.00 0.00 0.00 0.00 0.00 4 11.24 0.00 0.00 0.00 0.00 0.00

9 1 3 0.00 0.00 0.00 0.00 0.00 0.00 5 0.00 0.00 0.00 0.00 0.00 0.00 2 3 -11.24 0.00 0.00 0.00 0.00 0.00 5 11.24 0.00 0.00 0.00 0.00 0.00 3 3 -11.24 0.00 0.00 0.00 0.00 0.00 5 11.24 0.00 0.00 0.00 0.00 0.00

10 1 2 24.30 -0.42 0.00 0.00 0.00 -38.33 5 -24.30 0.42 0.00 0.00 0.00 -37.18 2 2 24.30 0.42 0.00 0.00 0.00 37.18 5 -24.30 -0.42 0.00 0.00 0.00 38.33 3 2 48.59 0.00 0.00 0.00 0.00 -1.15 5 -48.59 0.00 0.00 0.00 0.00 1.15


38. FINI

*************** END OF STAAD-III ***************

**** DATE= TIME= ****





NOTES




A space frame structure is subjected to a sinusoidal loading. Thecommands necessary to describe the sine function are demonstratedin this example. Time History analysis is performed on this model.




STAAD SPACE*EXAMPLE FOR HARMONIC LOADING GENERATOR

Every STAAD3 input file has to begin with the word STAAD.The word SPACE signifies that the structure is a space frame andthe geometry is defined through X, Y and Z axes. The remainder ofthe words form a title to identify this project.

UNIT KIP FEET


JOINT COORDINATES1 0 0 0 ; 2 15 0 0 ; 3 15 0 15 ; 4 0 0 155 0 20 0 ; 6 7.5 20 0 ; 7 15 20 0 ; 8 15 20 7.59 15 20 15 ; 10 7.5 20 15 ; 11 0 20 1512 0 20 7.5

The joint number followed by the X, Y and Z coordinates arespecified above.

Semicolon characters (;) are used as line separators to facilitateinput of multiple items of data in one line.

MEMBER INCIDENCES1 1 5 ; 2 2 7 ; 3 3 9 ; 4 4 11 ; 5 5 6 ; 6 6 77 7 8 ; 8 8 9 ; 9 9 10 ; 10 10 11 ; 11 11 12 ; 12 12 5

The members are defined by the joints they are connected to.

UNIT INCHMEMBER PROPERTIES1 TO 12 PRIS YD 12 ZD 12

Members 1 to 12 are defined as PRISmatic sections with width anddepth values of 12 inches. Note that the UNIT command isspecified to change the units for input from FEET to INCHes.

SUPPORTS1 TO 4 PINNED



The supports at joints 1 to 4 are declared as pinned supports.

CONSTANTSE 3150 ALLDENSITY 0.0868E-3 ALL

The modulus of elasticity (E) and density are specified followingthe command CONSTANTS.

DEFINE TIME HISTORYTYPE 1 FORCE* FOLLOWING LINES FOR HARMONIC LOADING*GENERATORFUNCTION SINEAMP 6.2831 FRE 60 CYCLES 100 STEP 0.02*ARRIVAL TIMES0.0DAMPING 0.075

There are two stages in the command specification required for atime-history analysis. The first stage is defined above. Here, theparameters of the sinusoidal loading are provided. STAAD canaccept upto 6 different data sets each of which describe a forcingfunction or a ground motion.

Each data set is individually identified by the number that followsthe TYPE command. In this file, only one data set is defined, whichis apparent from the fact that only one TYPE is defined.

The word FORCE that follows the TYPE 1 command signifies thatthis data set is for a forcing function.

The command FUNCTION SINE indicates that instead of providingthe data set as TIME-FORCE pairs, a sinusoidal function, whichdescribes the variation of force with time, is provided.

The parameters of the sine function, such as FREQUENCY,AMPLITUDE, and number of CYCLES of application are thendefined. STAAD internally generates discrete TIME-FORCE pairsof data from the sine function in steps of time defined by the value




that follows the STEP option. The arrival time value indicates therelative value of time at which the force begins to act upon thestructure. The modal damping ratio for the structure is set to 0.075.

LOAD 1MEMBER LOAD5 6 7 8 9 10 11 12 UNI GY -1.0

The above data describe a static load case. A uniformly distributedload of 1.0 kip/ft acting in the negative global Y direction isapplied on some members.

LOAD 2SELFWEIGHT X 1.0SELFWEIGHT Y 1.0SELFWEIGHT Z 1.0JOINT LOAD8 12 FX 4.08 12 FY 4.08 12 FZ 4.0TIME LOAD8 12 FX 1 1

This is the second stage of command specification for time historyanalysis. This involves the application of the time varying loads onthe structure. The masses that constitute the mass matrix of thestructure are specified in the form of selfweight and joint load.

Following that, the "TIME LOAD" is applied. The forcingfunction described by the TYPE 1 load is applied on joints 8 and12 and it starts to act starting at a time defined by the 1st arrivaltime number.



PERFORM ANALYSISPRINT ANALYSIS RESULTS

The above commands are self explanatory.

FINI





1. STAAD SPACE EXAMPLE FOR HARMONIC LOADING GENERATOR 2. UNIT KIP FEET 3. JOINT COORDINATES 4. 1 0 0 0 ; 2 15 0 0 ; 3 15 0 15 ; 4 0 0 15 5. 5 0 20 0 ; 6 7.5 20 0 ; 7 15 20 0 ; 8 15 20 7.5 6. 9 15 20 15 ; 10 7.5 20 15 ; 11 0 20 15 7. 12 0 20 7.5 8. MEMBER INCIDENCES 9. 1 1 5 ; 2 2 7 ; 3 3 9 ; 4 4 11 ; 5 5 6 ; 6 6 7 10. 7 7 8 ; 8 8 9 ; 9 9 10 ; 10 10 11 ; 11 11 12 ; 12 12 5 11. UNIT INCH 12. MEMBER PROPERTIES 13. 1 TO 12 PRIS YD 12 ZD 12


14. SUPPORTS 15. 1 TO 4 PINNED 16. CONSTANTS 17. E 3150 ALL 18. DENSITY 0.0868E-3 ALL 19. DEFINE TIME HISTORY 20. TYPE 1 FORCE 21. * FOLLOWING LINES FOR HARMONIC LOADING GENERATOR 22. FUNCTION SINE 23. AMPLITUDE 6.2831 FREQUENCY 60 CYCLES 100 STEP 0.02 24. * 25. ARRIVAL TIMES 26. 0.0 27. DAMPING 0.075 28. LOAD 1 29. MEMBER LOAD 30. 5 6 7 8 9 10 11 12 UNI GY -1.0 31. LOAD 2 32. SELFWEIGHT X 1.0 33. SELFWEIGHT Y 1.0 34. SELFWEIGHT Z 1.0 35. JOINT LOAD 36. 8 12 FX 4.0 37. 8 12 FY 4.0 38. 8 12 FZ 4.0 39. TIME LOAD 40. 8 12 FX 1 1 41. PERFORM ANALYSIS







1 1.203 0.83119 2 1.205 0.82986 3 1.453 0.68843

MASS PARTICIPATION FACTORS IN PERCENT --------------------------------------

MODE X Y Z SUMM-X SUMM-Y SUMM-Z

1 99.90 0.00 0.00 99.904 0.000 0.000 2 0.00 0.00 99.91 99.904 0.000 99.905 3 0.00 0.00 0.00 99.904 0.000 99.905




1 1 0.00000 0.00000 0.00000 -0.01047 0.00000 0.01047 2 0.00000 0.00000 0.00000 0.00000 0.00012 -0.00982 2 1 0.00000 0.00000 0.00000 -0.01047 0.00000 -0.01047 2 0.00000 0.00000 0.00000 0.00000 0.00012 -0.00982 3 1 0.00000 0.00000 0.00000 0.01047 0.00000 -0.01047 2 0.00000 0.00000 0.00000 0.00000 -0.00012 -0.00982 4 1 0.00000 0.00000 0.00000 0.01047 0.00000 0.01047 2 0.00000 0.00000 0.00000 0.00000 -0.00012 -0.00982 5 1 0.00118 -0.09524 0.00118 0.02102 0.00000 -0.02102 2 1.73233 0.00209 0.00005 0.00000 0.00012 -0.00200 6 1 0.00000 -1.56145 0.00118 0.02102 0.00000 0.00000 2 1.73236 0.00000 0.00000 0.00000 -0.00006 0.00094 7 1 -0.00118 -0.09524 0.00118 0.02102 0.00000 0.02102 2 1.73233 -0.00209 -0.00005 0.00000 0.00012 -0.00200 8 1 -0.00118 -1.56145 0.00000 0.00000 0.00000 0.02102 2 1.74557 -0.00210 0.00000 0.00000 0.00000 -0.00200 9 1 -0.00118 -0.09524 -0.00118 -0.02102 0.00000 0.02102 2 1.73233 -0.00209 0.00005 0.00000 -0.00012 -0.00200 10 1 0.00000 -1.56145 -0.00118 -0.02102 0.00000 0.00000 2 1.73236 0.00000 0.00000 0.00000 0.00006 0.00094 11 1 0.00118 -0.09524 -0.00118 -0.02102 0.00000 -0.02102 2 1.73233 0.00209 -0.00005 0.00000 -0.00012 -0.00200 12 1 0.00118 -1.56145 0.00000 0.00000 0.00000 -0.02102 2 1.74557 0.00210 0.00000 0.00000 0.00000 -0.00200

SUPPORT REACTIONS -UNIT KIP INCH STRUCTURE TYPE = SPACE -----------------


1 1 5.95 180.00 5.95 0.00 0.00 0.00 2 1.48 -3.94 0.00 0.00 0.00 0.00 2 1 -5.95 180.00 5.95 0.00 0.00 0.00 2 1.48 3.94 0.00 0.00 0.00 0.00 3 1 -5.95 180.00 -5.95 0.00 0.00 0.00 2 1.48 3.94 0.00 0.00 0.00 0.00 4 1 5.95 180.00 -5.95 0.00 0.00 0.00 2 1.48 -3.94 0.00 0.00 0.00 0.00




MEMBER END FORCES STRUCTURE TYPE = SPACE ----------------- ALL UNITS ARE -- KIP INCH


1 1 1 180.00 -5.95 5.95 0.00 0.00 0.00 5 -180.00 5.95 -5.95 0.00 -1428.41 -1428.41 2 1 -3.94 1.48 0.00 0.00 0.00 -0.09 5 3.94 -1.48 0.00 0.00 0.02 354.81

2 1 2 180.00 5.95 5.95 0.00 0.00 0.00 7 -180.00 -5.95 -5.95 0.00 -1428.41 1428.41 2 2 3.94 1.48 0.00 0.00 0.00 -0.09 7 -3.94 -1.48 0.00 0.00 -0.02 354.81

3 1 3 180.00 5.95 -5.95 0.00 0.00 0.00 9 -180.00 -5.95 5.95 0.00 1428.41 1428.41 2 3 3.94 1.48 0.00 0.00 0.00 -0.09 9 -3.94 -1.48 0.00 0.00 0.02 354.81

4 1 4 180.00 -5.95 -5.95 0.00 0.00 0.00 11 -180.00 5.95 5.95 0.00 1428.41 -1428.41 2 4 -3.94 1.48 0.00 0.00 0.00 -0.09 11 3.94 -1.48 0.00 0.00 -0.02 354.81

5 1 5 5.95 90.00 0.00 0.00 0.00 1428.41 6 -5.95 0.00 0.00 0.00 0.00 2621.59 2 5 -0.14 -3.94 -0.25 -0.01 22.25 -354.83 6 0.14 3.94 0.25 0.01 0.00 0.00

6 1 6 5.95 0.00 0.00 0.00 0.00 -2621.59 7 -5.95 90.00 0.00 0.00 0.00 -1428.41 2 6 0.14 -3.94 -0.25 -0.01 0.00 0.00 7 -0.14 3.94 0.25 0.01 22.25 -354.83

7 1 7 5.95 90.00 0.00 0.00 0.00 1428.41 8 -5.95 0.00 0.00 0.00 0.00 2621.59 2 7 -0.25 0.00 0.66 0.00 -22.25 0.03 8 0.25 0.00 -0.66 0.00 -37.28 0.04

8 1 8 5.95 0.00 0.00 0.00 0.00 -2621.59 9 -5.95 90.00 0.00 0.00 0.00 -1428.41 2 8 -0.25 0.00 -0.66 0.00 37.28 -0.04 9 0.25 0.00 0.66 0.00 22.25 -0.03

9 1 9 5.95 90.00 0.00 0.00 0.00 1428.41 10 -5.95 0.00 0.00 0.00 0.00 2621.59 2 9 0.14 3.94 0.25 0.01 -22.25 354.83 10 -0.14 -3.94 -0.25 -0.01 0.00 0.00

10 1 10 5.95 0.00 0.00 0.00 0.00 -2621.59 11 -5.95 90.00 0.00 0.00 0.00 -1428.41 2 10 -0.14 3.94 0.25 0.01 0.00 0.00 11 0.14 -3.94 -0.25 -0.01 -22.25 354.83

11 1 11 5.95 90.00 0.00 0.00 0.00 1428.41 12 -5.95 0.00 0.00 0.00 0.00 2621.58 2 11 0.25 0.00 -0.66 0.00 22.25 -0.03 12 -0.25 0.00 0.66 0.00 37.28 -0.04

12 1 12 5.95 0.00 0.00 0.00 0.00 -2621.58 5 -5.95 90.00 0.00 0.00 0.00 -1428.41 2 12 0.25 0.00 0.66 0.00 -37.28 0.04 5 -0.25 0.00 -0.66 0.00 -22.25 0.03




43. FINI

*************** END OF STAAD-III ***************

**** DATE= TIME= ****





NOTES




This example illustrates the usage of commands necessary toautomatically generate spring supports for a slab on grade. Theslab is subjected to pressure loading. Analysis of the structure isperformed.

The numbers shown in the diagram below are the element numbers.




STAAD SPACE SLAB ON GRADE

Every STAAD3 input file has to begin with the word STAAD. Theword SPACE signifies that the structure is a space frame and thegeometry is defined through X, Y and Z axes. The remainder of thewords form a title to identify this project.

UNIT FEET KIP


JOINT COORDINATES1 0.0 0.0 40.02 0.0 0.0 36.03 0.0 0.0 28.1674 0.0 0.0 20.3335 0.0 0.0 12.56 0.0 0.0 6.57 0.0 0.0 0.0REPEAT ALL 3 8.5 0.0 0.0REPEAT 3 8.0 0.0 0.0REPEAT 5 6.0 0.0 0.0REPEAT 3 8.0 0.0 0.0REPEAT 3 8.5 0.0 0.0

For joints 1 through 7, the joint number followed by the X, Y and Zcoordinates are specified above. The coordinates of these joints isused as a basis for generating 21 more joints by incrementing the Xcoordinate of each of these 7 joints by 8.5 feet, 3 times. REPEATcommands are used to generate the remaining joints of thestructure. The results of the generation may be visually verified bydrawing the structure in STAAD-POST.

ELEMENT INCIDENCES1 1 8 9 2 TO 6REPEAT 16 6 7

The incidences of element number 1 is defined and the data is usedas a basis for generating the 2nd through the 6th element. The



incidence pattern of the first 6 elements is then used to generatethe incidences of 96 more elements using the REPEAT command.

UNIT INCHELEMENT PROPERTIES1 TO 102 TH 5.5

The thickness of elements 1 to 102 is specified as 5.5 inchesfollowing the command ELEMENT PROPERTIES.

UNIT FEETCONSTANTSE 420000. ALLPOISSON 0.12 ALL

The modulus of elasticity (E) and density are specified followingthe command CONSTANTS. Units for length are changed to FEETto facilitate the input of E.

SUPPORTS1 TO 126 ELASTIC MAT DIRECTION Y SUB 10.0

The above command is used to instruct STAAD to generatesupports with springs which are effective in the global Y direction.The subgrade reaction of the soil is specified as 10 kip/cu.ft. Theprogram will determine the area under the influence of each jointand multiply of influence area by the subgrade reaction to arrive atthe spring stiffness for the "FY" degree of freedom at the joint. Allthe remaining degrees of freedom at the joint are considered to befixed.

PRINT SUPP INFO

This command will enable us to obtain the details of the supportconditions which were generated by the program.

LOAD 1 WEIGHT OF MAT & EARTHELEMENT LOAD1 TO 102 PR GY -1.55




The above data describe a static load case. A pressure load of 1.55kip/ft acting in the negative global Y direction is applied on all theelements.

LOAD 2 'COLUMN LOAD-DL+LL'JOINT LOADS1 2 FY -217.8 9 FY -109.5 FY -308.76 FY -617.422 23 FY -410.29 30 FY -205.26 FY -542.727 FY -1085.443 44 50 51 71 72 78 79 FY -307.547 54 82 FY -264.248 55 76 83 FY -528.392 93 FY -205.099 100 FY -410.0103 FY -487.0104 FY -974.0113 114 FY -109.0120 121 FY -217.0124 FY -273.3125 FY -546.6

Load case 2 consists of several joint loads acting in the negativeglobal Y direction.

LOADING COMBINATION 101 TOTAL LOAD1 1. 2 1.

A load combination case, identified with load case number 101, isspecified above. It instructs STAAD3 to algebraically add theresults of load cases 1 and 2.

PERFORM ANALYSIS

The analysis is initiated using the above command.



LOAD LIST 101PRINT JOINT DISPLACEMENTS LIST 33 56PRINT ELEMENT STRESSES LIST 34 67

Joint displacements for joints 33 and 56, and element stresses forelements 34 and 67, for load case 101, is obtained with the help ofthe above commands.

PLOT STRESS FILE

The above plot command enables STAAD3 to create filescontaining the element stress information so that they may begraphically viewed in STAAD-POST.

FINISH

The STAAD3 run is terminated.





1. STAAD SPACE SLAB ON GRADE 2. UNIT FEET KIP 3. JOINT COORDINATES 4. 1 0.0 0.0 40.0 5. 2 0.0 0.0 36.0 6. 3 0.0 0.0 28.167 7. 4 0.0 0.0 20.333 8. 5 0.0 0.0 12.5 9. 6 0.0 0.0 6.5 10. 7 0.0 0.0 0.0 11. REPEAT ALL 3 8.5 0.0 0.0 12. REPEAT 3 8.0 0.0 0.0 13. REPEAT 5 6.0 0.0 0.0 14. REPEAT 3 8.0 0.0 0.0 15. REPEAT 3 8.5 0.0 0.0 16. ELEMENT INCIDENCES 17. 1 1 8 9 2 TO 6 18. REPEAT 16 6 7 19. UNIT INCH 20. ELEMENT PROPERTIES 21. 1 TO 102 TH 5.5 22. UNIT FEET 23. CONSTANTS 24. E 420000. ALL 25. POISSON 0.12 ALL 26. SUPPORTS 27. 1 TO 126 ELASTIC MAT DIRECTION Y SUBGRADE 10.0 28. PRINT SUPP INFO

SUPPORT INFORMATION (1=FIXED, 0=RELEASED) ------------------- UNITS FOR SPRING CONSTANTS ARE KIP FEET DEGREES

JOINT FORCE-X/ FORCE-Y/ FORCE-Z/ MOM-X/ MOM-Y/ MOM-Z/ KFX KFY KFZ KMX KMY KMZ

1 1 0 1 0 1 0 0.0 85.0 0.0 0.0 0.0 0.0

2 1 0 1 0 1 0 0.0 251.4 0.0 0.0 0.0 0.0 3 1 0 1 0 1 0 0.0 332.9 0.0 0.0 0.0 0.0 4 1 0 1 0 1 0 0.0 332.9 0.0 0.0 0.0 0.0 5 1 0 1 0 1 0 0.0 294.0 0.0 0.0 0.0 0.0 6 1 0 1 0 1 0 0.0 265.6 0.0 0.0 0.0 0.0 7 1 0 1 0 1 0 0.0 138.1 0.0 0.0 0.0 0.0 8 1 0 1 0 1 0 0.0 170.0 0.0 0.0 0.0 0.0 9 1 0 1 0 1 0 0.0 502.9 0.0 0.0 0.0 0.0



10 1 0 1 0 1 0 0.0 665.8 0.0 0.0 0.0 0.0 11 1 0 1 0 1 0 0.0 665.8 0.0 0.0 0.0 0.0 12 1 0 1 0 1 0 0.0 587.9 0.0 0.0 0.0 0.0 13 1 0 1 0 1 0 0.0 531.3 0.0 0.0 0.0 0.0 14 1 0 1 0 1 0 0.0 276.3 0.0 0.0 0.0 0.0 15 1 0 1 0 1 0 0.0 170.0 0.0 0.0 0.0 0.0 16 1 0 1 0 1 0 0.0 502.9 0.0 0.0 0.0 0.0 17 1 0 1 0 1 0 0.0 665.8 0.0 0.0 0.0 0.0 18 1 0 1 0 1 0 0.0 665.8 0.0 0.0 0.0 0.0 19 1 0 1 0 1 0 0.0 587.9 0.0 0.0 0.0 0.0 20 1 0 1 0 1 0 0.0 531.3 0.0 0.0 0.0 0.0 21 1 0 1 0 1 0 0.0 276.3 0.0 0.0 0.0 0.0 22 1 0 1 0 1 0 0.0 165.0 0.0 0.0 0.0 0.0 23 1 0 1 0 1 0 0.0 488.1 0.0 0.0 0.0 0.0 24 1 0 1 0 1 0 0.0 646.3 0.0 0.0 0.0 0.0 25 1 0 1 0 1 0 0.0 646.3 0.0 0.0 0.0 0.0 26 1 0 1 0 1 0 0.0 570.6 0.0 0.0 0.0 0.0 27 1 0 1 0 1 0 0.0 515.6 0.0 0.0 0.0 0.0 28 1 0 1 0 1 0 0.0 268.1 0.0 0.0 0.0 0.0 29 1 0 1 0 1 0 0.0 160.0 0.0 0.0 0.0 0.0 30 1 0 1 0 1 0 0.0 473.3 0.0 0.0 0.0 0.0 31 1 0 1 0 1 0 0.0 626.7 0.0 0.0 0.0 0.0 32 1 0 1 0 1 0 0.0 626.7 0.0 0.0 0.0 0.0 33 1 0 1 0 1 0 0.0 553.3 0.0 0.0 0.0 0.0 34 1 0 1 0 1 0 0.0 500.0 0.0 0.0 0.0 0.0 35 1 0 1 0 1 0 0.0 260.0 0.0 0.0 0.0 0.0 36 1 0 1 0 1 0 0.0 160.0 0.0 0.0 0.0 0.0 37 1 0 1 0 1 0 0.0 473.3 0.0 0.0 0.0 0.0 38 1 0 1 0 1 0 0.0 626.7 0.0 0.0 0.0 0.0 39 1 0 1 0 1 0 0.0 626.7 0.0 0.0 0.0 0.0 40 1 0 1 0 1 0 0.0 553.3 0.0 0.0 0.0 0.0 41 1 0 1 0 1 0 0.0 500.0 0.0 0.0 0.0 0.0 42 1 0 1 0 1 0 0.0 260.0 0.0 0.0 0.0 0.0 43 1 0 1 0 1 0 0.0 140.0 0.0 0.0 0.0 0.0




44 1 0 1 0 1 0 0.0 414.2 0.0 0.0 0.0 0.0 45 1 0 1 0 1 0 0.0 548.3 0.0 0.0 0.0 0.0 46 1 0 1 0 1 0 0.0 548.3 0.0 0.0 0.0 0.0 47 1 0 1 0 1 0 0.0 484.1 0.0 0.0 0.0 0.0 48 1 0 1 0 1 0 0.0 437.5 0.0 0.0 0.0 0.0 49 1 0 1 0 1 0 0.0 227.5 0.0 0.0 0.0 0.0 50 1 0 1 0 1 0 0.0 120.0 0.0 0.0 0.0 0.0 51 1 0 1 0 1 0 0.0 355.0 0.0 0.0 0.0 0.0 52 1 0 1 0 1 0 0.0 470.0 0.0 0.0 0.0 0.0 53 1 0 1 0 1 0 0.0 470.0 0.0 0.0 0.0 0.0 54 1 0 1 0 1 0 0.0 415.0 0.0 0.0 0.0 0.0 55 1 0 1 0 1 0 0.0 375.0 0.0 0.0 0.0 0.0 56 1 0 1 0 1 0 0.0 195.0 0.0 0.0 0.0 0.0 57 1 0 1 0 1 0 0.0 120.0 0.0 0.0 0.0 0.0 58 1 0 1 0 1 0 0.0 355.0 0.0 0.0 0.0 0.0 59 1 0 1 0 1 0 0.0 470.0 0.0 0.0 0.0 0.0 60 1 0 1 0 1 0 0.0 470.0 0.0 0.0 0.0 0.0 61 1 0 1 0 1 0 0.0 415.0 0.0 0.0 0.0 0.0 62 1 0 1 0 1 0 0.0 375.0 0.0 0.0 0.0 0.0 63 1 0 1 0 1 0 0.0 195.0 0.0 0.0 0.0 0.0 64 1 0 1 0 1 0 0.0 120.0 0.0 0.0 0.0 0.0 65 1 0 1 0 1 0 0.0 355.0 0.0 0.0 0.0 0.0 66 1 0 1 0 1 0 0.0 470.0 0.0 0.0 0.0 0.0 67 1 0 1 0 1 0 0.0 470.0 0.0 0.0 0.0 0.0 68 1 0 1 0 1 0 0.0 415.0 0.0 0.0 0.0 0.0 69 1 0 1 0 1 0 0.0 375.0 0.0 0.0 0.0 0.0 70 1 0 1 0 1 0 0.0 195.0 0.0 0.0 0.0 0.0 71 1 0 1 0 1 0 0.0 120.0 0.0 0.0 0.0 0.0 72 1 0 1 0 1 0 0.0 355.0 0.0 0.0 0.0 0.0 73 1 0 1 0 1 0 0.0 470.0 0.0 0.0 0.0 0.0 74 1 0 1 0 1 0 0.0 470.0 0.0 0.0 0.0 0.0 75 1 0 1 0 1 0 0.0 415.0 0.0 0.0 0.0 0.0 76 1 0 1 0 1 0 0.0 375.0 0.0 0.0 0.0 0.0 77 1 0 1 0 1 0 0.0 195.0 0.0 0.0 0.0 0.0



78 1 0 1 0 1 0 0.0 140.0 0.0 0.0 0.0 0.0 79 1 0 1 0 1 0 0.0 414.2 0.0 0.0 0.0 0.0 80 1 0 1 0 1 0 0.0 548.3 0.0 0.0 0.0 0.0 81 1 0 1 0 1 0 0.0 548.3 0.0 0.0 0.0 0.0 82 1 0 1 0 1 0 0.0 484.1 0.0 0.0 0.0 0.0 83 1 0 1 0 1 0 0.0 437.5 0.0 0.0 0.0 0.0 84 1 0 1 0 1 0 0.0 227.5 0.0 0.0 0.0 0.0 85 1 0 1 0 1 0 0.0 160.0 0.0 0.0 0.0 0.0 86 1 0 1 0 1 0 0.0 473.3 0.0 0.0 0.0 0.0 87 1 0 1 0 1 0 0.0 626.7 0.0 0.0 0.0 0.0 88 1 0 1 0 1 0 0.0 626.7 0.0 0.0 0.0 0.0 89 1 0 1 0 1 0 0.0 553.3 0.0 0.0 0.0 0.0 90 1 0 1 0 1 0 0.0 500.0 0.0 0.0 0.0 0.0 91 1 0 1 0 1 0 0.0 260.0 0.0 0.0 0.0 0.0 92 1 0 1 0 1 0 0.0 160.0 0.0 0.0 0.0 0.0 93 1 0 1 0 1 0 0.0 473.3 0.0 0.0 0.0 0.0 94 1 0 1 0 1 0 0.0 626.7 0.0 0.0 0.0 0.0 95 1 0 1 0 1 0 0.0 626.7 0.0 0.0 0.0 0.0 96 1 0 1 0 1 0 0.0 553.3 0.0 0.0 0.0 0.0 97 1 0 1 0 1 0 0.0 500.0 0.0 0.0 0.0 0.0 98 1 0 1 0 1 0 0.0 260.0 0.0 0.0 0.0 0.0 99 1 0 1 0 1 0 0.0 165.0 0.0 0.0 0.0 0.0 100 1 0 1 0 1 0 0.0 488.1 0.0 0.0 0.0 0.0 101 1 0 1 0 1 0 0.0 646.3 0.0 0.0 0.0 0.0 102 1 0 1 0 1 0 0.0 646.3 0.0 0.0 0.0 0.0 103 1 0 1 0 1 0 0.0 570.6 0.0 0.0 0.0 0.0 104 1 0 1 0 1 0 0.0 515.6 0.0 0.0 0.0 0.0 105 1 0 1 0 1 0 0.0 268.1 0.0 0.0 0.0 0.0 106 1 0 1 0 1 0 0.0 170.0 0.0 0.0 0.0 0.0 107 1 0 1 0 1 0 0.0 502.9 0.0 0.0 0.0 0.0 108 1 0 1 0 1 0 0.0 665.8 0.0 0.0 0.0 0.0 109 1 0 1 0 1 0 0.0 665.8 0.0 0.0 0.0 0.0 110 1 0 1 0 1 0 0.0 587.9 0.0 0.0 0.0 0.0 111 1 0 1 0 1 0 0.0 531.3 0.0 0.0 0.0 0.0




112 1 0 1 0 1 0 0.0 276.3 0.0 0.0 0.0 0.0 113 1 0 1 0 1 0 0.0 170.0 0.0 0.0 0.0 0.0 114 1 0 1 0 1 0 0.0 502.9 0.0 0.0 0.0 0.0 115 1 0 1 0 1 0 0.0 665.8 0.0 0.0 0.0 0.0 116 1 0 1 0 1 0 0.0 665.8 0.0 0.0 0.0 0.0 117 1 0 1 0 1 0 0.0 587.9 0.0 0.0 0.0 0.0 118 1 0 1 0 1 0 0.0 531.3 0.0 0.0 0.0 0.0 119 1 0 1 0 1 0 0.0 276.3 0.0 0.0 0.0 0.0 120 1 0 1 0 1 0 0.0 85.0 0.0 0.0 0.0 0.0 121 1 0 1 0 1 0 0.0 251.4 0.0 0.0 0.0 0.0 122 1 0 1 0 1 0 0.0 332.9 0.0 0.0 0.0 0.0 123 1 0 1 0 1 0 0.0 332.9 0.0 0.0 0.0 0.0 124 1 0 1 0 1 0 0.0 294.0 0.0 0.0 0.0 0.0 125 1 0 1 0 1 0 0.0 265.6 0.0 0.0 0.0 0.0 126 1 0 1 0 1 0 0.0 138.1 0.0 0.0 0.0 0.0


29. LOAD 1 'WEIGHT OF MAT & EARTH' 30. ELEMENT LOAD 31. 1 TO 102 PR GY -1.55 32. LOAD 2 'COLUMN LOAD-DL+LL' 33. JOINT LOADS 34. 1 2 FY -217. 35. 8 9 FY -109. 36. 5 FY -308.7 37. 6 FY -617.4 38. 22 23 FY -410. 39. 29 30 FY -205. 40. 26 FY -542.7 41. 27 FY -1085.4 42. 43 44 50 51 71 72 78 79 FY -307.5 43. 47 54 82 FY -264.2 44. 48 55 76 83 FY -528.3 45. 92 93 FY -205.0 46. 99 100 FY -410.0 47. 103 FY -487.0 48. 104 FY -974.0 49. 113 114 FY -109.0 50. 120 121 FY -217.0 51. 124 FY -273.3 52. 125 FY -546.6 53. LOADING COMBINATION 101 TOTAL LOAD 54. 1 1. 2 1. 55. PERFORM ANALYSIS



** WARNING : PRESSURE LOAD ON "PLANE STRESS" ELEMENT 2 IS IGNORED. **



56. LOAD LIST 101 57. PRINT JOINT DISPLACEMENTS LIST 33 56



33 101 0.00000 -4.73107 0.00000 -0.03221 0.00000 0.06208 56 101 0.00000 -5.62691 0.00000 0.07125 0.00000 0.03192


58. PRINT ELEMENT STRESSES LIST 34 67

ELEMENT FORCES FORCE,LENGTH UNITS= KIP FEET -------------- FORCE OR STRESS = FORCE/WIDTH/THICK, MOMENT = FORCE-LENGTH/WIDTH


34 101 -6.22 -8.28 0.83 4.63 10.63 539.95 539.95 0.00 0.00 0.00 TOP : SMAX= 386.38 SMIN= -230.58 TMAX= 308.48 ANGLE= -39.9 BOTT: SMAX= 230.58 SMIN= -386.38 TMAX= 308.48 ANGLE= -39.9

67 101 71.92 7.69 15.09 9.75 21.67 1136.72 1136.72 0.00 0.00 0.00 TOP : SMAX= 978.22 SMIN= -268.81 TMAX= 623.51 ANGLE= 41.5 BOTT: SMAX= 268.81 SMIN= -978.22 TMAX= 623.51 ANGLE= 41.5


59. PLOT STRESS FILE 60. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****





NOTES




The structure in this example consists of "SOLID" finite elements.This input file contains commands for specifying solid elements.Analysis is performed on this structure.




STAAD SPACE*EXAMPLE PROBLEM USING SOLID ELEMENTS

Every STAAD3 input file has to begin with the word STAAD. Theword SPACE signifies that the structure is a space frame and thegeometry is defined through X, Y and Z axes. The remainder of thewords form a title to identify this project.

UNIT KNS MET


JOINT COORDINATES 1 0.0 0.0 2.0 4 0.0 3.0 2.0 5 1.0 0.0 2.0 8 1.0 3.0 2.0 9 2.0 0.0 2.0 12 2.0 3.0 2.0 21 0.0 0.0 1.0 24 0.0 3.0 1.0 25 1.0 0.0 1.0 28 1.0 3.0 1.0 29 2.0 0.0 1.0 32 2.0 3.0 1.0 41 0.0 0.0 0.0 44 0.0 3.0 0.0 45 1.0 0.0 0.0 48 1.0 3.0 0.0 49 2.0 0.0 0.0 52 2.0 3.0 0.0

The joint number followed by the X, Y and Z coordinates arespecified above.

ELEMENT INCIDENCES SOLID 1 1 5 6 2 21 25 26 22 TO 3 4 21 25 26 22 41 45 46 42 TO 6 1 1 7 5 9 10 6 25 29 30 26 TO 9 1 1 10 25 29 30 26 45 49 50 46 TO 12 1 1

The incidences of solid elements are defined above. The wordSOLID is used to signify that these are solid elements as opposedto plate or shell elements. Each element has 8 nodes. Each linecontains the data for generating 3 elements. For example, elementnumber 1 is first defined by all of its 8 nodes. Then, increments of1 to the joint number and 1 to the element number (the defaults) areused for generating incidences for elements 2 and 3. Similarly,



incidences of elements 4, 7 and 10 are defined while those of 5, 6,8, 9, 11 and 12 are generated.

CONSTANTSE 2.1E7 ALLPOIS 0.25 ALLDENSITY 7.5 ALL

The material constants such as E (Modulus of Elasticity), Poisson'sRatio, and Density are specified following the commandCONSTANTS above.

PRINT ELEMENT INFO SOLID LIST 1 TO 5

This command will enable us to obtain, in a tabular form, thedetails of the incidences and material property values of elements 1to 5.

SUPPORTS1 5 9 21 25 29 41 45 49 PINNED

The supports at the above mentioned joints are declared as pinnedsupports.

LOAD 1SELF Y -1.0JOINT LOAD28 FY -1000.0

The above data describe a static load case. It consists of selfweightloading and a joint load, both in the negative global Y direction.

LOAD 2JOINT LOADS2 TO 4 22 TO 24 42 TO 44 FX 100.0

Load case 2 consists of several joint loads acting in the positiveglobal X direction.




LOAD COMB 101 1.0 2 1.0

A load combination case, identified with load case number 10, isspecified above. It instructs STAAD/Pro to algebraically add theresults of load cases 1 and 2.

PERFORM ANALYSISPRINT JOINT DISPLACEMENTS LIST 8PRINT SUPPORT REACTIONS

The above commands are self explanatory.

PRINT ELEMENT STRESS SOLID LIST 4 6

This command requests the program to provide the element stressresults of elements 4 and 6. The results will be printed for all theload cases. The word SOLID is used to signify that these are solidelements as opposed to plate or shell elements.

FINISH

The STAAD/Pro run is terminated.




1. STAAD SPACE EXAMPLE PROBLEM USING SOLID ELEMENTS 2. UNIT KNS MET 3. SET CO 26 4. JOINT COORDINATES 5. 1 0.0 0.0 2.0 4 0.0 3.0 2.0 6. 5 1.0 0.0 2.0 8 1.0 3.0 2.0 7. 9 2.0 0.0 2.0 12 2.0 3.0 2.0 8. 21 0.0 0.0 1.0 24 0.0 3.0 1.0 9. 25 1.0 0.0 1.0 28 1.0 3.0 1.0 10. 29 2.0 0.0 1.0 32 2.0 3.0 1.0 11. 41 0.0 0.0 0.0 44 0.0 3.0 0.0 12. 45 1.0 0.0 0.0 48 1.0 3.0 0.0 13. 49 2.0 0.0 0.0 52 2.0 3.0 0.0 14. ELEMENT INCIDENCES SOLID 15. 1 1 5 6 2 21 25 26 22 TO 3 16. 4 21 25 26 22 41 45 46 42 TO 6 1 1 17. 7 5 9 10 6 25 29 30 26 TO 9 1 1 18. 10 25 29 30 26 45 49 50 46 TO 12 1 1 19. CONSTANTS 20. E 2.1E7 ALL 21. POIS 0.25 ALL 22. DENSITY 7.5 ALL 23. PRINT ELEMENT INFO SOLID LIST 1 TO 5

ELEMENT NODE-1 NODE-2 NODE-3 NODE-4 NODE-5 NODE-6 NODE-7 NODE-8

1 1 5 6 2 21 25 26 22 2 2 6 7 3 22 26 27 23 3 3 7 8 4 23 27 28 24 4 21 25 26 22 41 45 46 42 5 22 26 27 23 42 46 47 43

MATERIAL PROPERTIES. -------------------- ALL UNITS ARE - KNS MET

ELEMENT YOUNGS'S MODULUS MODULUS OF RIGIDITY DENSITY ALPHA

1 2.1000000E+07 8.4000000E+06 7.5000E+00 0.0000E+00 2 2.1000000E+07 8.4000000E+06 7.5000E+00 0.0000E+00 3 2.1000000E+07 8.4000000E+06 7.5000E+00 0.0000E+00 4 2.1000000E+07 8.4000000E+06 7.5000E+00 0.0000E+00 5 2.1000000E+07 8.4000000E+06 7.5000E+00 0.0000E+00

24. SUPPORTS 25. 1 5 9 21 25 29 41 45 49 PINNED 26. LOAD 1 27. SELF Y -1.0 28. JOINT LOAD 29. 28 FY -1000.0 30. LOAD 2 31. JOINT LOADS 32. 2 TO 4 22 TO 24 42 TO 44 FX 100.0 33. LOAD COMB 10 34. 1 1.0 2 1.0 35. PERFORM ANALYSIS






36. PRINT JOINT DISPLACEMENTS LIST 8

JOINT DISPLACEMENT (CM RADIANS) STRUCTURE TYPE = SPACE ------------------


8 1 0.0000 -0.0010 -0.0006 0.0000 0.0000 0.0000 2 0.0184 0.0002 0.0000 0.0000 0.0000 0.0000 10 0.0184 -0.0008 -0.0005 0.0000 0.0000 0.0000



SUPPORT REACTIONS -UNIT KNS MET STRUCTURE TYPE = SPACE -----------------


1 1 18.31 76.41 -18.31 0.00 0.00 0.00 2 -75.95 -232.03 43.99 0.00 0.00 0.00 10 -57.64 -155.62 25.68 0.00 0.00 0.00 5 1 0.00 135.24 -37.89 0.00 0.00 0.00 2 -57.66 12.24 -0.78 0.00 0.00 0.00 10 -57.66 147.48 -38.67 0.00 0.00 0.00 9 1 -18.31 76.41 -18.31 0.00 0.00 0.00 2 -83.19 225.85 -45.67 0.00 0.00 0.00 10 -101.50 302.26 -63.98 0.00 0.00 0.00 21 1 37.89 135.24 0.00 0.00 0.00 0.00 2 -171.47 -452.82 0.00 0.00 0.00 0.00 10 -133.58 -317.58 0.00 0.00 0.00 0.00 25 1 0.00 243.40 0.00 0.00 0.00 0.00 2 -122.98 9.27 0.00 0.00 0.00 0.00 10 -122.98 252.67 0.00 0.00 0.00 0.00 29 1 -37.89 135.24 0.00 0.00 0.00 0.00 2 -171.96 431.42 0.00 0.00 0.00 0.00 10 -209.85 566.66 0.00 0.00 0.00 0.00 41 1 18.31 76.41 18.31 0.00 0.00 0.00 2 -75.95 -232.03 -43.99 0.00 0.00 0.00 10 -57.64 -155.62 -25.68 0.00 0.00 0.00 45 1 0.00 135.24 37.89 0.00 0.00 0.00 2 -57.66 12.24 0.78 0.00 0.00 0.00 10 -57.66 147.48 38.67 0.00 0.00 0.00 49 1 -18.31 76.41 18.31 0.00 0.00 0.00 2 -83.19 225.85 45.67 0.00 0.00 0.00 10 -101.50 302.26 63.98 0.00 0.00 0.00


38. PRINT ELEMENT STRESS SOLID LIST 4 6



ELEMENT STRESSES UNITS= KNS MET ------------------------------------------------------------------------------- NODE/ NORMAL STRESSES SHEAR STRESSES ELEMENT LOAD CENTER SXX SYY SZZ SXY SYZ SZX -------------------------------------------------------------------------------

4 1 CENTER -40.982 -268.750 -40.982 -9.224 -9.224 4.834 S1= -35.419 S2= -45.816 S3= -269.479 SE= 229.039 DC= 0.706 -0.056 0.706 -0.707 0.000 0.707 4 2 CENTER 22.131 456.612 91.740 236.205 12.171 -14.576 S1= 560.346 S2= 93.580 S3= -83.442 SE= 576.051 DC= 0.402 0.916 0.011 -0.099 0.031 0.995 4 10 CENTER -18.851 187.862 50.758 226.981 2.948 -9.742 S1= 333.938 S2= 51.174 S3= -165.343 SE= 433.657 DC= 0.541 0.841 -0.010 -0.033 0.033 0.999

6 1 CENTER -41.390 -253.750 -41.390 -103.395 -103.395 -4.853 S1= 29.296 S2= -36.537 S3= -329.289 SE= 330.621 DC= 0.628 -0.459 0.628 -0.707 0.000 0.707 6 2 CENTER -182.565 42.940 -4.118 81.413 -6.950 -29.645 S1= 72.592 S2= -4.169 S3= -212.165 SE= 255.188 DC= 0.319 0.925 -0.207 -0.054 0.236 0.970 6 10 CENTER -223.955 -210.810 -45.508 -21.982 -110.345 -34.498 S1= 11.618 S2= -205.616 S3= -286.275 SE= 266.868 DC= -0.091 -0.435 0.896 0.862 -0.485 -0.149

39. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****





NOTES




This example demonstrates the usage of compression-onlymembers. Since the structural condition is load dependent, thePERFORM ANALYSIS command is specified twice, once for eachprimary load case.




STAAD PLANE*EXAMPLE FOR COMPRESSION-ONLY MEMBERS

Every STAAD input file has to begin with the word STAAD. Theword PLANE signifies that the structure is a plane frame and thegeometry is defined through X and Y axes. The remainder of thewords form a title to identify this project.

UNIT FEET KIP


SET NL 2

This command is provided in order to convey to the program thatthis input file contains load cases following the PERFORMANALYSIS command. The number 2 indicates that the totalnumber of primary load cases in this file is 2.

JOINT COORDINATES1 0 0 ; 2 0 10 ; 3 0 20 ; 4 15 20 ; 5 15 10 ; 6 15 0

The joint number followed by the X and Y coordinates arespecified above. Semicolon characters (;) are used as lineseparators to facilitate input of multiple items of data in one line.

MEMBER INCIDENCES1 1 2 56 1 5 ; 7 2 6 ; 8 2 4 ; 9 3 5 ; 10 2 5

The members are defined by the joints they are connected to.

MEMBER COMPRESSION6 TO 9

The list of members that are to be declared as being capable ofcarrying compressive forces only are specified with the help of theabove commands.



MEMBER PROPERTY1 TO 10 TA ST W12X26

Members 1 to 10 are defined as standard W12X26 sections fromthe American steel table.

UNIT INCHCONSTANTSE 29000.0 ALLDEN 0.000283 ALL

The material constants such as E (Modulus of Elasticity) andDensity are specified following the command CONSTANTS. Notethat the length units have been changed from feet to inch tofacilitate the input of these values.

SUPPORT1 6 PINNED

The supports at joints 1 and 6 are declared as pinned.

LOAD 1JOINT LOAD2 FX 153 FX 10

The above data describe a static load case. Joint loads are appliedin the positive global X direction at joints 2 and 3.

PERFORM ANALYSIS

The above structure is analyzed for load case 1.

CHANGE

During the process of the above analysis, some of the members mayhave been inactivated as a result of them being subjected to tensileforces. These members now have to be re-activated for any furtherprocesses. This is done with the help of the CHANGE command.




MEMBER COMPRESSION6 TO 9

The MEMBER COMPRESSION command and the list of suchmembers is re-declared since the previous declaration becameinvalid following the completion of the first analysis.

LOAD 2JOINT LOAD4 FX -105 FX -15

In load case 2, joint loads are applied in the negative global Xdirection at joints 4 and 5.


All load combination commands have to be provided along with thelast primary load case. The above command instructs STAAD toretrieve the results of load cases 1 and 2 from the data base andalgebraically add them.

PERFORM ANALYSISCHANGE

Any compression-only members that were inactivated during thesecond analysis (due to the fact that they were subjected to tensileaxial forces) are re-activated with the CHANGE command.

LOAD LIST ALL

At the end of any analysis, only those load cases for which theanalysis was done most recently, are recognized as the "active"load cases. The LOAD LIST ALL command enables all the loadcases in the structure to be made active for further processing.




Above command is self explanatory. Joint displacements, supportreactions and member forces are written to the output file.

FINISH

The STAAD/Pro run is terminated.





1. STAAD PLANE EXAMPLE FOR COMPRESSION-ONLY MEMBERS 2. UNIT FEET KIP 3. SET NL 2 4. JOINT COORDINATES 5. 1 0 0 ; 2 0 10 ; 3 0 20 ; 4 15 20 ; 5 15 10 ; 6 15 0 6. MEMBER INCIDENCES 7. 1 1 2 5 8. 6 1 5 ; 7 2 6 ; 8 2 4 ; 9 3 5 ; 10 2 5 9. MEMBER COMPRESSION 10. 6 TO 9 11. MEMBER PROPERTY AMERICAN 12. 1 TO 10 TA ST W12X26 13. UNIT INCH 14. CONSTANTS 15. E 29000.0 ALL 16. DEN 0.000283 ALL 17. SUPPORT 18. 1 6 PINNED 19. LOAD 1 20. JOINT LOAD 21. 2 FX 15 22. 3 FX 10 23. PERFORM ANALYSIS



24. CHANGE 25. MEMBER COMPRESSION 26. 6 TO 9 27. LOAD 2 28. JOINT LOAD 29. 4 FX -10 30. 5 FX -15 31. LOAD COMBINATION 3 32. 1 1.0 2 1.0 33. PERFORM ANALYSIS 34. CHANGE 35. LOAD LIST ALL 36. PRINT ANALYSIS RESULTS





1 1 0.00000 0.00000 0.00000 0.00000 0.00000 -0.00041 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00051 3 0.00000 0.00000 0.00000 0.00000 0.00000 0.00010 2 1 0.04313 0.01262 0.00000 0.00000 0.00000 -0.00025 2 -0.05087 -0.00373 0.00000 0.00000 0.00000 0.00024 3 -0.00774 0.00889 0.00000 0.00000 0.00000 -0.00001 3 1 0.07773 0.01618 0.00000 0.00000 0.00000 -0.00022 2 -0.07763 -0.00382 0.00000 0.00000 0.00000 0.00015 3 0.00010 0.01237 0.00000 0.00000 0.00000 -0.00007 4 1 0.07763 -0.00382 0.00000 0.00000 0.00000 -0.00015 2 -0.07773 0.01618 0.00000 0.00000 0.00000 0.00022 3 -0.00010 0.01237 0.00000 0.00000 0.00000 0.00007 5 1 0.05087 -0.00373 0.00000 0.00000 0.00000 -0.00024 2 -0.04313 0.01262 0.00000 0.00000 0.00000 0.00025 3 0.00774 0.00889 0.00000 0.00000 0.00000 0.00001 6 1 0.00000 0.00000 0.00000 0.00000 0.00000 -0.00051 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00041 3 0.00000 0.00000 0.00000 0.00000 0.00000 -0.00010

SUPPORT REACTIONS -UNIT KIP INCH STRUCTURE TYPE = PLANE -----------------


1 1 -0.13 -23.33 0.00 0.00 0.00 0.00 2 24.87 23.33 0.00 0.00 0.00 0.00 3 24.73 0.00 0.00 0.00 0.00 0.00 6 1 -24.87 23.33 0.00 0.00 0.00 0.00 2 0.13 -23.33 0.00 0.00 0.00 0.00 3 -24.73 0.00 0.00 0.00 0.00 0.00

MEMBER END FORCES STRUCTURE TYPE = PLANE ----------------- ALL UNITS ARE -- KIP INCH


1 1 1 -23.33 0.13 0.00 0.00 0.00 0.00 2 23.33 -0.13 0.00 0.00 0.00 15.99 2 1 6.90 -0.22 0.00 0.00 0.00 0.00 2 -6.90 0.22 0.00 0.00 0.00 -26.12 3 1 -16.43 -0.08 0.00 0.00 0.00 0.00 2 16.43 0.08 0.00 0.00 0.00 -10.13

2 1 2 -6.58 0.24 0.00 0.00 0.00 13.06 3 6.58 -0.24 0.00 0.00 0.00 15.98 2 2 0.15 -0.12 0.00 0.00 0.00 -2.53 3 -0.15 0.12 0.00 0.00 0.00 -11.53 3 2 -6.43 0.12 0.00 0.00 0.00 10.53 3 6.43 -0.12 0.00 0.00 0.00 4.45

3 1 3 0.12 -0.15 0.00 0.00 0.00 -15.98 4 -0.12 0.15 0.00 0.00 0.00 -11.53 2 3 0.12 0.15 0.00 0.00 0.00 11.53 4 -0.12 -0.15 0.00 0.00 0.00 15.98 3 3 0.23 0.00 0.00 0.00 0.00 -4.45 4 -0.23 0.00 0.00 0.00 0.00 4.45

4 1 4 0.15 0.12 0.00 0.00 0.00 11.53 5 -0.15 -0.12 0.00 0.00 0.00 2.53 2 4 -6.58 -0.24 0.00 0.00 0.00 -15.98 5 6.58 0.24 0.00 0.00 0.00 -13.06 3 4 -6.43 -0.12 0.00 0.00 0.00 -4.45 5 6.43 0.12 0.00 0.00 0.00 -10.53




5 1 5 6.90 0.22 0.00 0.00 0.00 26.12 6 -6.90 -0.22 0.00 0.00 0.00 0.00 2 5 -23.33 -0.13 0.00 0.00 0.00 -15.99 6 23.33 0.13 0.00 0.00 0.00 0.00 3 5 -16.43 0.08 0.00 0.00 0.00 10.13 6 16.43 -0.08 0.00 0.00 0.00 0.00

6 1 1 0.00 0.00 0.00 0.00 0.00 0.00 5 0.00 0.00 0.00 0.00 0.00 0.00 2 1 29.62 0.00 0.00 0.00 0.00 0.00 5 -29.62 0.00 0.00 0.00 0.00 0.00 3 1 29.62 0.00 0.00 0.00 0.00 0.00 5 -29.62 0.00 0.00 0.00 0.00 0.00

7 1 2 29.62 0.00 0.00 0.00 0.00 0.00 6 -29.62 0.00 0.00 0.00 0.00 0.00 2 2 0.00 0.00 0.00 0.00 0.00 0.00 6 0.00 0.00 0.00 0.00 0.00 0.00 3 2 29.62 0.00 0.00 0.00 0.00 0.00 6 -29.62 0.00 0.00 0.00 0.00 0.00

8 1 2 0.00 0.00 0.00 0.00 0.00 0.00 4 0.00 0.00 0.00 0.00 0.00 0.00 2 2 11.59 0.00 0.00 0.00 0.00 0.00 4 -11.59 0.00 0.00 0.00 0.00 0.00 3 2 11.59 0.00 0.00 0.00 0.00 0.00 4 -11.59 0.00 0.00 0.00 0.00 0.00

9 1 3 11.59 0.00 0.00 0.00 0.00 0.00 5 -11.59 0.00 0.00 0.00 0.00 0.00 2 3 0.00 0.00 0.00 0.00 0.00 0.00 5 0.00 0.00 0.00 0.00 0.00 0.00 3 3 11.59 0.00 0.00 0.00 0.00 0.00 5 -11.59 0.00 0.00 0.00 0.00 0.00

10 1 2 -9.54 -0.32 0.00 0.00 0.00 -29.05 5 9.54 0.32 0.00 0.00 0.00 -28.65 2 2 -9.54 0.32 0.00 0.00 0.00 28.65 5 9.54 -0.32 0.00 0.00 0.00 29.05 3 2 -19.08 0.00 0.00 0.00 0.00 -0.40 5 19.08 0.00 0.00 0.00 0.00 0.40


37. FINISH

*************** END OF STAAD-III ***************

**** DATE= TIME= ****



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