esuite 1.0 beta

GENERAL

What is eSuite© ?eSuite© is a suite (series) of composite structural analysis tools that can be used for structural sizing, parametric studies, etc.The tools are comparable to those used by large aircraft companies and have a modern user friendly interface.The eSuite© tools show intermediate calculations, can be linked together, and allow for user customization.

Do macros need to be enabled?

In Excel 2003, select "Tools/Options", then select the Security tab. Set "Macro Security..." to Medium. Then restart the file and enable macros.

What files are created during the installation? What files are needed to run the main Excel file?A series of files are copied to the destination directory. The main Excel file will not work if these files are not installed.Do not copy the main Excel file to another machine. Instead, run the full installation.

INPUT / OUTPUT

Can I save the main Excel file?

What are the "Read Data" and "Save Data" buttons for?These buttons should be used to export and import data. Formulas entered into input cells (light blue) will be preserved during import/export.

Against the recommendation, I accidently used the "Save" or "Save As" feature. Could this cause a problem?If the only modification was to the input cells, then a problem should not occur. A more effective way of exporting and importing data is to use the "read data" and "save data" buttons on the upper left.If you also unlocked the sheets and made further modifications, then it is likely that a destructive modification occurred.If you are not sure if a detrimental modification may have occurred, simply reinstall the program.

NAVIGATING

How do I navigate?

Then browse the tabs below. Each tool is color coded and has a unique suffix identifier.For example, showing ePlots© will display multiple tabs. The main tool tab is for data input, while the other tabs show carpet plots. Each ePlots© tab has the suffix "B"

What do the "SHOW" and "HIDE actions do?

Macros must be enabled. Click the test button below to determine if macros are enabled. If a message box does not appear, then macros are disabled.

Using the "Save" or "Save As" feature is not recommended, but is allowed.

First, use the "SHOW" action in the navigation menu to the left.

The "SHOW" option performs two actions. Sheets (tabs) related to the tool will be displayed and the main sheet will be selected.

If the "HIDE" action is performed, the main Excel file will display the adjancent tab. In some cases, this tab may not be the main tab of a tool.

USE

How do I use the tools?The input cells are in light blue, while the the output cells are a darker blue.

COMMENTThe comment indicator should be shown in the cell above. If you cannot see the comment when hovering over the cell with the mouse, then comments are turned off. In Excel 2003, turn comments on by selectiong "Tools/Options", select the "View" tab, and Select "Comment Indicator Only"Full technical documentation on each tool is pending. In addition, the book "Practical Stress Analysis of Composite Aerostructures" by Brian Esp will be released in 2012. Most of the tools are fully documented in the planned publication.

How can I link data from one tool to another?First, "Show" the tools you want to link. Then use the native Excel feature "=" to link the data.For example, you can link the elastic properties from eLaminate© to ePlots© .

Some of the tools generate a lot of data. Do I really need all of that information?Unlike other programs, which "bury" the data, this program provides the information to the user.You may not need this extra information, but it is provided in the event that you do. Many advanced users require intermediate data to check results or better understand the final results.

Can I unlock the sheet?

If you still wish to unlock the sheet, the password is "composites".

THIRD PARTY SOFTWARE

How do eStability© and ePressure© work?These tools are pre and post processors to the open source finite element solver CalculiX. The CalculiX files were created during installation.

How does eBJSFM© work?eBJSFM© is a pre and post processor to the BJSFM fortran code. Improvements and corrections to the original fortran code have been made.A compiled version of BJSFM was created during installation.

FREE AND PRO VERSIONS

Who can use the FREE version?The free version can be used in a non commercial environment (academic or education) without restriction.

What does the PRO version offer?The pro version must be used in a commercial environment.The pro version removes the restrictions of the free version and adds functionality not demonstrated in the free version.

The "SHOW" and "HIDE" actions are

Most input cells have comments

Yes, but this is not recommended. The main Excel file

The free version may be used in a commerical environment for 30 days,

D52

Comment Indictator is switched on.

For example, eCutout© and eBJSFM© can run many load cases in the pro version.

CAPABILITYCan an Excel file have the capability of traditional programs?

Normal use of an Excel is limited in capability. However, by allowing macros to be enabled, the VBA (Visual Basic for Applications) becomes available.VBA is a powerful programming language that dramatically increases Excel's capability.The combination of Excel with VBA yields a powerful tool for engineering tasks.

How does this software compare to other software?All programs have different objectives and capabilities.This program aims to implement practical composite analysis tools in a convenient interface. The software is simple enough to use for a beginner, but has the capabiliy required for an advanced user.In addition, the integration with the finite element solver CalculiX, creates an extremely powerful product.

For example, eStability© has the capability to solve curved panels with arbitrary boundary conditions and loading. Transverse shear deformation is accounted for. Most programs fall short of this functionality.The simple user interface, combined with embedded comments, minimizes learning curve.Finally, this software displays intermediate data, as opposed to providing a "black box" solution. This is useful and necessary for advanced structural analysis.This product is designed for structural analysts who desire a highly function product in a convenient user interface. It is NOT a "push button" analysis solution, but rather is a tool suitable for sizing of aircraft.

KNOWN ISSUESWhy do some tools not work properly for international users?

For some languages, the "comma" and "period" may be reversed from the English system. This creates a problem when passing data to third party programs.To solve this problem, you can either change the language or change the Excel options to adjust the comma and period.

After using the "HIDE" action, the menu bar dissapears.Upon using the "HIDE" action, the nearest tab is displayed, which may not be the main tab of a tool. In some cases, the tool sub-tabs does not have a menu bar.To resolve this, select a different tab.

Why do some cells show "#######"?This may occur at certain zoom levels. Change the zoom level or expand the column width. The sheet will need to be unprotected first. The password is "composites".

Why do some graphics/number look strange?This occur as certain zoom levels. Change the zoom level slightly to improve the appearance.

Will this program work on the Mac?If you are using Winows on the Mac, then everything should run normally.If you are using the Mac version of Excel, this program may not be compatible.

COMPATIBILITYWhat version of Excel will this program work on?

Making a program that works on the various versions of Excel can be a challenging task. For example, Excel 2007 did not incorporate some of the VBA (Visual Basic for Applications) features that existed in previous versions.This program attempts to only use the most compatible coding and is tested on multiple versions for compatibility.

FUTURE FEATURESWill SI units be supported?

This feature will be supported in the future.

Will OpenOffice be supported?

Support for OpenOffice is not planned.

Are other tools planned?eRadius© A tool to caculate the strength of curved beams is in work. For example, "radius opening" and "radius closing" are common failure modes that should be checked.eBeam© A beam analysis tool is in work.eSandwich© - Sandwich analysis is in work. (PRO edition only)

BETA

What is a Beta Version? Why is this program listed as a Beta?A Beta version is not the final version. The test phase is ongoing and there may be updates and improvements before the final version.

UNINSTALL

How can I uninstall eSuite©?Use the uninstall feature from the control panel or from start menu (if selected during installation).

What files were installed?The only files installed reside in the "C:\eSuite" directory. Additionally, a desktop icon and start menu shortcuts (if selected during installation) were created.

Why does the C:\eSuite directory remain after an uninstall?This occurs because either the user created data files that reside in this directory or eSuite© added temporary analysis files for interface with Calculix and eBJSFM©. You may delete the directory after an uninstall to completely remove the program.

FAQ

eSuite© is a suite (series) of composite structural analysis tools that can be used for structural sizing, parametric studies, etc.The tools are comparable to those used by large aircraft companies and have a modern user friendly interface.The eSuite© tools show intermediate calculations, can be linked together, and allow for user customization.


What files are created during the installation? What files are needed to run the main Excel file?A series of files are copied to the destination directory. The main Excel file will not work if these files are not installed.Do not copy the main Excel file to another machine. Instead, run the full installation.

What are the "Read Data" and "Save Data" buttons for?These buttons should be used to export and import data. Formulas entered into input cells (light blue) will be preserved during import/export.

Against the recommendation, I accidently used the "Save" or "Save As" feature. Could this cause a problem?If the only modification was to the input cells, then a problem should not occur. A more effective way of exporting and importing data is to use the "read data" and "save data" buttons on the upper left.If you also unlocked the sheets and made further modifications, then it is likely that a destructive modification occurred.If you are not sure if a detrimental modification may have occurred, simply reinstall the program.

Then browse the tabs below. Each tool is color coded and has a unique suffix identifier.For example, showing ePlots© will display multiple tabs. The main tool tab is for data input, while the other tabs show carpet plots. Each ePlots© tab has the suffix "B"

What do the "SHOW" and "HIDE actions do?

be enabled. Click the test button below to determine if macros are enabled. If a message box does not appear, then macros are disabled.

Using the "Save" or "Save As" feature is not recommended, but is allowed. Instead, use the "Read Data" and "Save Data" buttons.

First, use the "SHOW" action in the navigation menu to the left. This will will display all sheets (tabs) for that tool.



The input cells are in light blue, while the the output cells are a darker blue.

The comment indicator should be shown in the cell above. If you cannot see the comment when hovering over the cell with the mouse, then comments are turned off. In Excel 2003, turn comments on by selectiong "Tools/Options", select the "View" tab, and Select "Comment Indicator Only"Full technical documentation on each tool is pending. In addition, the book "Practical Stress Analysis of Composite Aerostructures" by Brian Esp will be released in 2012. Most of the tools are fully documented in the planned publication.

How can I link data from one tool to another?First, "Show" the tools you want to link. Then use the native Excel feature "=" to link the data.For example, you can link the elastic properties from eLaminate© to ePlots© .

Some of the tools generate a lot of data. Do I really need all of that information?Unlike other programs, which "bury" the data, this program provides the information to the user.You may not need this extra information, but it is provided in the event that you do. Many advanced users require intermediate data to check results or better understand the final results.

If you still wish to unlock the sheet, the password is "composites".

How do eStability© and ePressure© work?These tools are pre and post processors to the open source finite element solver CalculiX. The CalculiX files were created during installation.

eBJSFM© is a pre and post processor to the BJSFM fortran code. Improvements and corrections to the original fortran code have been made.A compiled version of BJSFM was created during installation.

The free version can be used in a non commercial environment (academic or education) without restriction.

The pro version must be used in a commercial environment.The pro version removes the restrictions of the free version and adds functionality not demonstrated in the free version.

The "SHOW" and "HIDE" actions are filters that provide a convenient way of displaying the individual tools.

Most input cells have comments that provide information about the input. Look for the red comment indicator by the cell.

Yes, but this is not recommended. The main Excel file should not be modified since the "Save Data" and "Read Data" functions may no longer work.

The free version may be used in a commerical environment for 30 days, for evaluation purposes only.

For example, eCutout© and eBJSFM© can run many load cases in the pro version.

Can an Excel file have the capability of traditional programs?Normal use of an Excel is limited in capability. However, by allowing macros to be enabled, the VBA (Visual Basic for Applications) becomes available.VBA is a powerful programming language that dramatically increases Excel's capability.The combination of Excel with VBA yields a powerful tool for engineering tasks.

How does this software compare to other software?All programs have different objectives and capabilities.This program aims to implement practical composite analysis tools in a convenient interface. The software is simple enough to use for a beginner, but has the capabiliy required for an advanced user.In addition, the integration with the finite element solver CalculiX, creates an extremely powerful product.

For example, eStability© has the capability to solve curved panels with arbitrary boundary conditions and loading. Transverse shear deformation is accounted for. Most programs fall short of this functionality.The simple user interface, combined with embedded comments, minimizes learning curve.Finally, this software displays intermediate data, as opposed to providing a "black box" solution. This is useful and necessary for advanced structural analysis.This product is designed for structural analysts who desire a highly function product in a convenient user interface. It is NOT a "push button" analysis solution, but rather is a tool suitable for sizing of aircraft.

Why do some tools not work properly for international users?For some languages, the "comma" and "period" may be reversed from the English system. This creates a problem when passing data to third party programs.To solve this problem, you can either change the language or change the Excel options to adjust the comma and period.

After using the "HIDE" action, the menu bar dissapears.Upon using the "HIDE" action, the nearest tab is displayed, which may not be the main tab of a tool. In some cases, the tool sub-tabs does not have a menu bar.To resolve this, select a different tab.

Why do some cells show "#######"?This may occur at certain zoom levels. Change the zoom level or expand the column width. The sheet will need to be unprotected first. The password is "composites".

Why do some graphics/number look strange?This occur as certain zoom levels. Change the zoom level slightly to improve the appearance.

Will this program work on the Mac?If you are using Winows on the Mac, then everything should run normally.If you are using the Mac version of Excel, this program may not be compatible.

What version of Excel will this program work on?Making a program that works on the various versions of Excel can be a challenging task. For example, Excel 2007 did not incorporate some of the VBA (Visual Basic for Applications) features that existed in previous versions.This program attempts to only use the most compatible coding and is tested on multiple versions for compatibility.

This feature will be supported in the future.

Support for OpenOffice is not planned.

eRadius© A tool to caculate the strength of curved beams is in work. For example, "radius opening" and "radius closing" are common failure modes that should be checked.eBeam© A beam analysis tool is in work.eSandwich© - Sandwich analysis is in work. (PRO edition only)

What is a Beta Version? Why is this program listed as a Beta?A Beta version is not the final version. The test phase is ongoing and there may be updates and improvements before the final version.

Use the uninstall feature from the control panel or from start menu (if selected during installation).

The only files installed reside in the "C:\eSuite" directory. Additionally, a desktop icon and start menu shortcuts (if selected during installation) were created.Why does the C:\eSuite directory remain after an uninstall?

This occurs because either the user created data files that reside in this directory or eSuite© added temporary analysis files for interface with Calculix and eBJSFM©. You may delete the directory after an uninstall to completely remove the program.

eSuite© is a suite (series) of composite structural analysis tools that can be used for structural sizing, parametric studies, etc.


These buttons should be used to export and import data. Formulas entered into input cells (light blue) will be preserved during import/export.

If the only modification was to the input cells, then a problem should not occur. A more effective way of exporting and importing data is to use the "read data" and "save data" buttons on the upper left.

For example, showing ePlots© will display multiple tabs. The main tool tab is for data input, while the other tabs show carpet plots. Each ePlots© tab has the suffix "B"

be enabled. Click the test button below to determine if macros are enabled. If a message box does not appear, then macros are disabled.

Instead, use the "Read Data" and "Save Data" buttons.



The comment indicator should be shown in the cell above. If you cannot see the comment when hovering over the cell with the mouse, then comments are turned off. In Excel 2003, turn comments on by selectiong "Tools/Options", select the "View" tab, and Select "Comment Indicator Only"Full technical documentation on each tool is pending. In addition, the book "Practical Stress Analysis of Composite Aerostructures" by Brian Esp will be released in 2012. Most of the tools are fully documented in the planned publication.

These tools are pre and post processors to the open source finite element solver CalculiX. The CalculiX files were created during installation.

eBJSFM© is a pre and post processor to the BJSFM fortran code. Improvements and corrections to the original fortran code have been made.

modified since the "Save Data" and "Read Data" functions may no longer work.

Normal use of an Excel is limited in capability. However, by allowing macros to be enabled, the VBA (Visual Basic for Applications) becomes available.

This program aims to implement practical composite analysis tools in a convenient interface. The software is simple enough to use for a beginner, but has the capabiliy required for an advanced user.

For example, eStability© has the capability to solve curved panels with arbitrary boundary conditions and loading. Transverse shear deformation is accounted for. Most programs fall short of this functionality.

Finally, this software displays intermediate data, as opposed to providing a "black box" solution. This is useful and necessary for advanced structural analysis.This product is designed for structural analysts who desire a highly function product in a convenient user interface. It is NOT a "push button" analysis solution, but rather is a tool suitable for sizing of aircraft.

For some languages, the "comma" and "period" may be reversed from the English system. This creates a problem when passing data to third party programs.

Upon using the "HIDE" action, the nearest tab is displayed, which may not be the main tab of a tool. In some cases, the tool sub-tabs does not have a menu bar.

This may occur at certain zoom levels. Change the zoom level or expand the column width. The sheet will need to be unprotected first. The password is "composites".

Making a program that works on the various versions of Excel can be a challenging task. For example, Excel 2007 did not incorporate some of the VBA (Visual Basic for Applications) features that existed in previous versions.

eRadius© A tool to caculate the strength of curved beams is in work. For example, "radius opening" and "radius closing" are common failure modes that should be checked.

A Beta version is not the final version. The test phase is ongoing and there may be updates and improvements before the final version.

The only files installed reside in the "C:\eSuite" directory. Additionally, a desktop icon and start menu shortcuts (if selected during installation) were created.

This occurs because either the user created data files that reside in this directory or eSuite© added temporary analysis files for interface with Calculix and eBJSFM©.

Full technical documentation on each tool is pending. In addition, the book "Practical Stress Analysis of Composite Aerostructures" by Brian Esp will be released in 2012. Most of the tools are fully documented in the planned publication.

For example, eStability© has the capability to solve curved panels with arbitrary boundary conditions and loading. Transverse shear deformation is accounted for. Most programs fall short of this functionality.

Making a program that works on the various versions of Excel can be a challenging task. For example, Excel 2007 did not incorporate some of the VBA (Visual Basic for Applications) features that existed in previous versions.

Lamina Orthotropic Properties

Material 1 Material 2 Material 3 Material 4

Reference Info

Example

Carbon Fiber

Epoxy

Hot/Wet Click Picture to Enlarge

27,000,000 651,957 164,801 -51,349 -1,418 186 -1,438

1,500,000 164,801 446,559 -51,349 186 1,046 -1,438

0.350 -51,349 -51,349 192,229 -1,438 -1,438 186

1,100,000 -1,418 186 -1,438 160 32 -14

0.0080 186 1,046 -1,438 32 51 -14

1.000E-08 -1,438 -1,438 186 -14 -14 37 Input Value

1.500E-05 Calculated Value

0.050 1.915E-06 -4.646E-07 7.104E-07 2.489E-05 2.776E-05 7.324E-05 Reference Value

0.400 -4.646E-07 2.778E-06 4.042E-07 8.810E-06 -2.690E-05 8.110E-05 Pro Edition Only

7.104E-07 4.042E-07 7.162E-06 4.038E-05 1.945E-04 9.799E-05

Strain Based Lamina Allowalbes or Design Cutoffs 2.489E-05 8.810E-06 4.038E-05 7.684E-03 -3.118E-03 2.871E-03

0.00400 2.776E-05 -2.690E-05 1.945E-04 -3.118E-03 3.033E-02 9.555E-03

-0.00400 7.324E-05 8.110E-05 9.799E-05 2.871E-03 9.555E-03 3.741E-02

0.00600

-0.00700

0.01000

Equivalent Laminate Properties

Stress Based Allowables Basic In-Plane In-Plane Shear Coupling Bending Hygrothermal

108,000 0 0 0 10,879,044 0.099 14,120,338 9.78E-07

-108,000 0 0 0 7,500,041 0.371 3,577,160 1.92E-06

9,000 0 0 0 0.243 0.146 0.406 1.22E-06

-10,500 0 0 0 0.167 0.056 2,900,663 8.29E-02

11,000 0 0 0 2,908,771 1.08E-01

3.31E-02

Applied Loads

500.0 Laminate Mid-Plane Strains/Curvatures Margin of Safety (First Ply Failure if Lamina Allowables are Used) Ply Orientation Summary

100.0 0.001503 Max Strain Max Stress Tsai-Hill Max Fiber Strain Custom % of total

0.0 0.000594 M.S. 0.28 0.29 0.15 0.28 0 33.3

15.0 0.001256 ply no. 5 5 5 5 45 16.7

0.0 0.1363 0.003137 0.003137 0.003137 0.003137 -45 33.3

0.0 -0.0354 -0.002831 -0.002831 -0.002831 -0.002831 90 16.7

200.0 0.1231 0.002733 0.002733 0.002733 0.002733

0.000

total thickness [in] 0.0480

Lamina Mid-Ply Strains Lamina Mid-Ply Strains Lamina Mid-Ply Stresses Lamina Mid-Ply Stesses

Global X,Y System Local 1,2 System Global X,Y System Local 1,2 System

Ply Mat ID z mid [in]

1 1 0 -0.02 -0.001225 -0.001699 -0.001205 -0.001225 -0.001699 -0.001205 -34,190 -3,213 -1,326 -34,190 -3,213 -1,326

2 1 45 -0.012 -0.001633 -0.000483 0.002777 0.000331 -0.002447 0.001151 821 3,352 5,607 7,694 -3,520 1,266

3 1 -45 -0.004 -0.000543 -0.000766 -0.002234 0.000463 -0.001771 0.000223 4,852 4,361 -7,037 11,644 -2,431 245

4 1 90 0.004 -0.000952 0.000450 0.001748 0.000450 -0.000952 -0.001748 -1,199 11,733 1,923 11,733 -1,199 -1,923

5 1 0 0.012 0.003137 -0.002831 0.002733 0.003137 -0.002831 0.002733 83,778 -2,617 3,006 83,778 -2,617 3,006

6 1 -45 0.02 0.002728 -0.001615 0.000719 0.000197 0.000916 0.004343 8,439 -1,116 -2,173 5,835 1,488 4,778

E1 [psi]

E2 [psi]

n12 [in/in]

G12 [psi]

tply [in]

a1 [in/in/F]

a2 [in/in/F]

b1 [in/in]

b2 [in/in]

e1t [in/in]

e1c [in/in]

e2t [in/in]

e2c [in/in]

g6s [in/in]

F1t [psi] Èx [psi] `hsx Èxb [psi] àx [in/in/F]

F1c [psi] Èy [psi] `hxs Èyb [psi] ày [in/in/F]

F2t [psi] `nxy [in/in] `hys `nxyb [psi] àxy [in/in/F]

F2c [psi] `nyx [in/in] `hsy `Gxyb [psi] `bx [in/in]

F6 [psi] `Gxy [psi] `by [in/in]

`bxy [in/in]

Nx [lb/in]

Ny [lb/in] ex0 [in/in] ply q

Nxy [lb/in] ey0 [in/in]

Mx [in-lb/in] gxy0 [in/in]

My [in-lb/in] kx [rad/in] e1

Mxy [in-lb/in] ky [rad/in] e2

Temp D [deg F] kxy [rad/in] g12

Moisture D [%]

q [deg] ex ey gxy e1 e2 g12 sx sy sxy s1 s2 s12

=A

B

B

D

=a

bT

b

d=

-1A

B

B

D

C6

This section is used to describe materials, but is not required.

C11

Input lamina elastic properties. 2-D orthoropic lamina with 4 independent elastic constants.

J11

The [A] matrix represents the laminate's in-plane stiffness properties.

M11

The [B] matrix represents the coupling between axial and bending.

M14

The [D] matrix represents the laminate's bending properties.

C15

Ply thickness

C16

Input coefficients of thermal expansion. Not required if thermal loading is not applied.

C18

Input coefficents of moisture expansion. Not required if moisture expansion load is not applied).

J18

The 6x6 matrix represents the [a], [b], and [d] matrices.

C22

Input either lamina based strain allowables or design strain cutoffs. Strain cutoffs may be used to account for notched laminates, etc.

C29

This section calculates the equivalent stress based strengths. They are converted from the strain allowable inputs above. Used as reference only. If strengths are to be directly input, the sheet can be modified such that the strain based allowables are functions of the stress based allowables. C22 to C26 are always the final values used.

I29

The "equivalent" properties are most valid when the laminate is symmetric.

M29

The equivalent bending properties represent the bending stiffness if the material were isotropic, with moment of inertia (1/12)bt3

O29

"Equivalent" coefficients of thermal expansions and coefficients of moisture expansion. Most valid for symmetric laminates.

C36

Input "running" or "line" loads and "running moments".

H36

All M.S. calculations are based on the mid-ply stresses/strains. The Marin of Safety is defined as the (Factor of Safety - 1) and a M.S. > 0.0 indicates acceptance while a M.S. < 0.0 indicates failure. Outer and inner fiber stresses/strains should be considered for thin laminates or thick layers. This can be calculated through spreadsheet modification as outer layer strains/stress are provided in the "Intermediate" tab. If lamina based strain allowables are used then the M.S. represents first ply failurel. *Note that unnotched failure predictions and material allowables may not be useful for laminates with holes, bolted joints, where impact damage tolerance is necessary, etc. Design strain cutoffs may be used to represent laminates with holes, bolted joints, impact tolerance, etc.

F37

The total laminate mid-plane strains and curvatures are shown here. The total hygrothermal strains are included so the result is a total strain.

I38

Max strain failure criterion for the 1, 2, and 1-2 direction failure modes. The minimum margin of any of the 3 failure modes is reported.

J38

Similar to the Max Strain failure criterion, but uses a stress based approach. The major difference between the two is due to the effect of Poisson's ratio.

L38

This failure criterion is the same as the max-strain, but only reports the margin in the 1-direction (fiber direction). This failure criterion disregards potentially subcritical failures in the matrix.

M38

A custome failure criterion may be used by modifying the "Intermediate" tab.

C42

Input the temperature gradient (T - T0), where T0 is the stress free temperature. For example, if the stress free temperature was assumed to be at 300.0F and the laminate is analyzed at 75.0F, then the input would be -225.0F.

F47

Global X,Y mid-ply strains. For hygrothermal loading, the related stress free strains are subtracted and not accounted for in the failure criteria. The result is an "effective strain" that can used to evaluate failure. For example, a laminate of all 0 degree plies would have finite strain upon thermal loading, but the individual lamina strains related to failure would be zero.

C50

Simply add a Mat ID entry for every lamina and the ply count will be automatically updated. Be sure not to have any blank rows between entries or the calculations will not be valid.

D50

Enter the corresponding ply angle. There must be a ply angle for every Mat ID entry.

E50

Z position of the mid surface of each lamina.

eLaminate©Margin of Safety

Max Strain Max Stress

Min - All Load Cases

Loads 0.00 0.00

Case Min - Each Case

1 500.0 50.0 100.0 0.0 0.0 0.0 200.0 0.02 500.0 55.0 200.0 0.0 0.0 0.0 200.0 0.03 500.0 60.0 300.0 0.0 0.0 0.0 200.0 0.04 500.0 65.0 -100.0 0.0 0.0 0.0 200.0 0.05 500.0 -100.0 0.0 5.0 0.0 0.0 200.0 0.06 500.0 -200.0 10.0 10.0 0.0 0.0 200.0 0.07 500.0 -300.0 30.0 -15.0 0.0 0.0 200.0 0.08 500.0 -400.0 50.0 -20.0 0.0 0.0 200.0 0.09 500.0 100.0 0.0 -30.0 0.0 0.0 200.0 0.0

101112131415161718192021222324252627282930313233343536373839404142434445464748495051525354555657585960616263646566676869707172737475767778798081828384858687888990

Nx [lb/in] Ny [lb/in] Nxy [lb/in] Mx [in-lb/in] My [in-lb/in] Mxy [in-lb/in] Temp D, [deg F] Moisture D [%]

C7

Enter each load case. For each load case, there must be a value in each location. Blanks are not permitted.

919293949596979899

100101102103104105106107108109110111112113114115116117118119120121122123124125126127128129130131132133134135136137138139140141142143144145146147148149150151152153154155156157158159160161162163164165166167168169170171172173174175176177178179180181182183184185186187188189190191192193194195

196197198199200201202203204205206207208209210211212213214215216217218219220221222223224225226227228229230231232233234235236237238239240241242243244245246247248249250251252253254255256257258259260261262263264265266267268269270271272273274275276277278279280281282283284285286287288289290291292293294295296297298299300301

302303304305306307308309310311312313314315316317318319320321322323324325326327328329330331332333334335336337338339340341342343344345346347348349350351352353354355356357358359360361362363364365366367368369370371372373374375376377378379380381382383384385386387388389390391392393394395396397398399400401402403404405406407

408409410411412413414415416417418419420421422423424425426427428429430431432433434435436437438439440441442443444445446447448449450451452453454455456457458459460461462463464465466467468469470471472473474475476477478479480481482483484485486487488489490491492493494495496497498499500501502503504505506507508509510511512513

514515516517518519520521522523524525526527528529530531532533534535536537538539540541542543544545546547548549550551552553554555556557558559560561562563564565566567568569570571572573574575576577578579580581582583584585586587588589590591592593594595596597598599600601602603604605606607608609610611612613614615616617618619

620621622623624625626627628629630631632633634635636637638639640641642643644645646647648649650651652653654655656657658659660661662663664665666667668669670671672673674675676677678679680681682683684685686687688689690691692693694695696697698699700701702703704705706707708709710711712713714715716717718719720721722723724725

726727728729730731732733734735736737738739740741742743744745746747748749750751752753754755756757758759760761762763764765766767768769770771772773774775776777778779780781782783784785786787788789790791792793794795796797798799800801802803804805806807808809810811812813814815816817818819820821822823824825826827828829830831

832833834835836837838839840841842843844845846847848849850851852853854855856857858859860861862863864865866867868869870871872873874875876877878879880881882883884885886887888889890891892893894895896897898899900901902903904905906907908909910911912913914915916917918919920921922923924925926927928929930931932933934935936937

938939940941942943944945946947948949950951952953954955956957958959960961962963964965966967968969970971972973974975976977978979980981982983984985986987988989990991992993994995996997998999

1000

Margin of Safety

Tsai-Hill Max Strain - Fiber Custom


0.00 0.00 0.00

Min - Each Case

Input Value

Output Value

Parameters

Ex [psi] 12,000,000.00 44,000 a [in] 0.125

Ey [psi] 9,000,000.00 15,000 b [in] 1.000 Started

vxy [in/in] 0.30 4,000 0.000

Gxy [psi] 3,000,000.00 W [in] 200.0

FWC 1.000

Max of Stresses [psi] Max of Strains [in/in]

#VALUE! #VALUE! #VALUE! #VALUE! #VALUE! #VALUE!

Min of Stresses [psi] Min of Strains [in/in]

#VALUE! #VALUE! #VALUE! #VALUE! #VALUE! #VALUE!

x [in] y [in]

0 0.125 0.000 #VALUE! #VALUE! #VALUE! #VALUE! #VALUE! #VALUE!



















95 -0.011 0.125 #VALUE! #VALUE! #VALUE! #VALUE! #VALUE! #VALUE!


















185 -0.125 -0.011 #VALUE! #VALUE! #VALUE! #VALUE! #VALUE! #VALUE!

















270 0.000 -0.125 #VALUE! #VALUE! #VALUE! #VALUE! #VALUE! #VALUE!





Elastic Properties (Laminate)

Remote Applied Stresses

sx* [psi]

sy* [psi]

txy* [psi] d0 [in]

Global System (x,y) - Recovery Point @ d 0

sx sy txy ex ey gxy

sx sy txy ex ey gxy

q [deg] sx sy txy ex ey gxy

C5

Input the in-plane elastic properties after choosing from the material type below. You MUST have the appropriate entries for the given material type. Isotropic - 2 elastic constants Orthotropic - 4 elastic constants Anisotropic - 6 elastic constants + thickness

F5

Remote applied stresses at the infinite external boundary.

H5

The dimensions of the ellipse. Click the "Display Graphic" icon for details. If a and b are equal, the result with be a circle with a radius of a. The standard edition allows for a circular cutout. The pro edition allows for an elliptical cutout.

H6

Pro edition only. The standard edition only allows for a circular cutout of radius "a".

J6

The calculation mode can be changed here. When entering initial data, it may be more efficient to turn off automatic calculation. Automatic calculation mode must be started in order to view updated results.

H7

The characteristic dimension, d0, is the dimension from the edge of the hole. Local stresses and strains, shown below, are recovered at the physical location of d0. For example, a d0 of 0.0 would represent the hole edge. A very large d0 would indicate a position far away from the hole. d0 values are usually considered to be different for tension and compression and are specific to a given material system and layup.

H8

The "Width" of the plate is the smallest of either the actual width or height. Enter a very large value to simulate an infinite plate.

H9

The finite width correction factor amplifies the stresses. This solution employs the correction factor typically used for isotropic materials, but often exptrapolated to orthotropic or anisotropic materials. See the technical documentation for more information. The largest value of either a or b is used for conservatism. A value of 1.00 represents an infinite plate.

H10

The local stresses and strains to the cutout are shown in this section.

D13

Choose the type of material. Orthotropic properties for symmetric and balanced laminates may be obtained with eLaminate. Choosing anisotropic is the slowest, while isotropic is the fastest.

E18

Enter exactly 73 positions around the hole, in degrees. By default, results are reported at every 5 degrees between 0 and 360. Theta is measured from the global-x direction. Click the "display graphic" for more information.















2 2

2

0.0130 0.0

-0.0100 45.0

0.0200 -20.0

-0.0200 90.0

0.0200

Margin of Safety

(Max Strain)

###

Click Picture to Enlarge

Strength Properties (Lamina)

Rotation Angles for Strength Prediction

e1t [in/in] q1 [deg]

e1c [in/in] q2 [deg]

e2t [in/in] q3 [deg]

e2c [in/in] q4 [deg]

g12s [in/in]

P5

If strength prediction is desired, enter the lamina strain allowables in each direction.

S5

The margin of safety is calculated by rotating the global strains in each of the four direction. This represents the local 1-2 system strains for each potential lamina.

Q14

The margin of safety is calculated for each of the four rotated angles, at each angle around the cutout (default is every 5 degress from 0 to 360). The max strain failure criterion is used and the failure modes in the 1, 2, and shear direction are considered. The minimum value around the entire cutout is reported. Margin of Safety = Factor of Safety - 1.

x [in] y [in]

0.000 1.000 #VALUE! #VALUE! #VALUE!







































sx sy txy

B4

(Optional) Enter x,y positions manually to determine stress and strain components. A stress profile may be otained in this worksheet.

#VALUE! #VALUE! #VALUE!







































ex ey gxy

Loads

Case

1 30000.0 1000.0 -10000.02 31000.0 2000.0 -9000.03 32000.0 3000.0 -8000.04 33000.0 4000.0 -7000.05 34000.0 5000.0 -6000.06 35000.0 6000.0 -5000.07 36000.0 7000.0 -4000.08 37000.0 8000.0 -3000.09 38000.0 9000.0 -2000.0

10 39000.0 10000.0 -1000.011 40000.0 11000.0 0.012 41000.0 12000.0 1000.013 42000.0 13000.0 2000.014 43000.0 14000.0 3000.015 44000.0 15000.0 4000.01617181920212223242526272829303132333435363738

sx* [psi] sy

* [psi] txy* [psi]

C7

Enter each load case. For each load case, there must be a value in each of the 3 columns. Blanks are not permitted.

394041424344454647484950515253545556575859606162636465666768697071727374757677787980818283848586

87888990919293949596979899

100101102103104105106107108109110111112113114115116117118119120121122123124125126127128129130131132133134135136

137138139140141142143144145146147148149150151152153154155156157158159160161162163164165166167168169170171172173174175176177178179180181182183184185186187

188189190191192193194195196197198199200201202203204205206207208209210211212213214215216217218219220221222223224225226227228229230231232233234235236237238

239240241242243244245246247248249250251252253254255256257258259260261262263264265266267268269270271272273274275276277278279280281282283284285286287288289

290291292293294295296297298299300301302303304305306307308309310311312313314315316317318319320321322323324325326327328329330331332333334335336337338339340

341342343344345346347348349350351352353354355356357358359360361362363364365366367368369370371372373374375376377378379380381382383384385386387388389390391

392393394395396397398399400401402403404405406407408409410411412413414415416417418419420421422423424425426427428429430431432433434435436437438439440441442

443444445446447448449450451452453454455456457458459460461462463464465466467468469470471472473474475476477478479480481482483484485486487488489490491492493

494495496497498499500501502503504505506507508509510511512513514515516517518519520521522523524525526527528529530531532533534535536537538539540541542543544

545546547548549550551552553554555556557558559560561562563564565566567568569570571572573574575576577578579580581582583584585586587588589590591592593594595

596597598599600601602603604605606607608609610611612613614615616617618619620621622623624625626627628629630631632633634635636637638639640641642643644645646

647648649650651652653654655656657658659660661662663664665666667668669670671672673674675676677678679680681682683684685686687688689690691692693694695696697

698699700701702703704705706707708709710711712713714715716717718719720721722723724725726727728729730731732733734735736737738739740741742743744745746747748

749750751752753754755756757758759760761762763764765766767768769770771772773774775776777778779780781782783784785786787788789790791792793794795796797798799

800801802803804805806807808809810811812813814815816817818819820821822823824825826827828829830831832833834835836837838839840841842843844845846847848849850

851852853854855856857858859860861862863864865866867868869870871872873874875876877878879880881882883884885886887888889890891892893894895896897898899900901

902903904905906907908909910911912913914915916917918919920921922923924925926927928929930931932933934935936937938939940941942943944945946947948949950951952

953954955956957958959960961962963964965966967968969970971972973974975976977978979980981982983984985986987988989990991992993994995996997998999

1000

Margin of Safety

Max Strain


0.10

Min - Each Case

0.290.290.300.300.300.290.280.260.240.210.190.170.150.130.10

Lamina Orthotropic Properties

Material 1 Material 2 Material 3

Reference Info

Example Input Value

Carbon Fiber Calculated Value

Epoxy Reference Value

Hot/Wet Pro Only

27,000,000

1,500,000

0.350

1,100,000

Strain Based Allowalbes or Design Cutoffs

0.01000

-0.01500

Stress Based Allowables

104,000 0 0

-156,000 0 0

Bearing and Fastener Strengths

Fbr [psi] 75,000

Fs [lb] 2,800

Applied Loads Geometry Knockdowns

6500.0 Width [in] 10.00 1.00

1000.0 Bolt Diam [in] 0.25 1.00

400.0 Equivalent Properties 1.00

Pf [lb] 2700.0 10,400,000 1.00

20.0 10,400,000 1.00

0.300 1.00

total thickness [in] 0.2000 4,000,000 1.00

Ply (Ref Label) Mat ID

1 1 0 0.05 Failure Input2 1 45 0.05 0.020

3 1 -45 0.05

4 1 90 0.05 M.S.

0.39 Bearing Check

0.04 Fastener Check

#VALUE! Bearing-Bypass : Max Strain Criterion

#VALUE! Bearing-Bypass : Max Stress Criterion

E1 [psi]

E2 [psi]

n12 [in/in]

G12 [psi]

e1t [in/in]

e1c [in/in]

F1t [psi]

F1c [psi]

Nx [lb/in] KFWC

Ny [lb/in] KCSK

Nxy [lb/in] KFAST

`Ex [psi] KEDGE

Bearing Angle [q] `Ey [psi] K5

`nxy [in/in] K6

`Gxy [psi] K7

q [deg] tply_total [in]

d0, [in]

q

x

y

W

D

d0

Pbr

Nx Nx

Ny

Ny

Nxy

Nxy

q

x

y

W

D

d0

Pbr

Nx Nx

Ny

Ny

Nxy

Nxy

C7

This section is used to describe materials, but is not required.

C12

Input lamina elastic properties. 2-D orthoropic lamina with 4 independent elastic constants.

C18

Input laminate based strain allowables. This should be an "unnotched strength" since the local stresses will be calculated.

C23

This section calculates the equivalent stress based strengths. They are converted from the strain allowable inputs above. Used as reference only. If strengths are to be directly input, the sheet can be modified such that the strain based allowables are functions of the stress based allowables. C18 to C21 are always the final values used.

B27

Bearing strength of laminate

B28

Fastener strength. Often times number if far less than the rated shear strength to account for the effects of fastener bending.

I31

The knockdown factors are incorporated in the M.S. reported on this sheet.

C32

Input bypass loads as "running" or "line" loads.

E32

Input the width. Valid range is W/D > 4.0 Enter 0.0 for an infinite plate. BJSFM accounts for the finite width effect due to bearing load, which has a significant impact. BJSFM does not account for the finite width effect due to bypass, which is less significant than due to bearing. If desired, this may be adjusted for by manually modifying the applied loads.

H32

The finite width correction factor for the open hole solution component is added since this is not part of the original BJSFM code. For W/D > 4, the isotropic FWC is a good approximation for anisotropic/orthotropic materials. The FWC applied in this manner is slightly conservative since it is applied to the combined bearing-bypass stress field.

C35

Input Bearing Load (Fastener Load) and Bearing Angle

E35

The "equivalent" properties are most valid when the laminate is symmetric.

C41

Simply add a Mat ID entry for every lamina and the ply count will be automatically updated. Be sure not to have any blank rows between entries or the calculations will not be valid.

D41

Enter the corresponding ply angle. Up to 8 orientations are allowed. Enter the thickness of all plies in each direction used. Each orientation is used only ONE time. For example, if there are 4 plies in the 0 degree direction, enter 0 only time, but use the total thickness of all 0 plies. There must be a ply angle for every Mat ID entry. The angle 9.99 is reserved and cannot be used.

E41

Enter to the TOTAL thickness in each direction. BJSFM does not account for stacking sequence effects and all laminates are assumed to be symmetric. No bending moments are accounted for.

I42

Input the "characteristic dimension" d0 here. The M.S. will be reported at the stresses/strains at a distance d0 from the hole edge. Valid range is 0.0 or greater.

I44

The M.S. (Margin of Safety) = Factor of Safety - 1. The max stress criterion is applied at the laminate level, not the ply level. The max strain criterion is applied at the laminate/lamina level since the strains are the same for either approach. Recommend max strain criterion to avoid confusion.

esuite 1.0 beta

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