A User’s Guide to 

LAMPAT and ANSYS 

by Robert l? Kaste 

Approved for public release; distribution is unlimited. 

20020528 073 
The findings in this report are not to be construed as an 

official Department of the Army position unless so 

designated by other authorized documents. 

Citation of manufacturer’s or trade names does not 

constitute an official endorsement or approval of the use 

thereof. 

Destroy this report when it is no longer needed. Do not 

return it to the originator. 
Army Research Laboratory 

Aberdeen Proving Ground, MD 2100.%5069 

ARL-TR-2691 March 2002 

A User’s Guide to 

LAMPAT and ANSYS 

Robert l? Kaste 

Weapons and Materials Research Directorate, ARL 

Approved for public release; distribution is unlimited. 
Abstract 

LAMPAT and ANSYS are analysis tools that can be used together to evaluate 

mechanical integrity of structures of laminar construction. The two codes 

originate from two different areas of analysis. Their default coordinate systems 

have different orientations. To properly examine a structure, the directional 

properties used by LAMPAT must be transformed into the proper input 

coordinate directional properties for ANSYS. This has been done for some time 

already, but as the structures being analyzed become more complex, this 

coordinate system transformation has become a tool requiring some additional 

thought. This report describes using cylindrical and Cartesian coordinate system 

orientations and local element coordinate system results within ANSYS to 

facilitate the analysis of laminate structures with ply layers parallel to curvilinear 

profiles. 

. 
Contents 

List of Figures 

List of Tables 

1. Introduction 

2. Method 

3. Conclusions 

Appendix A. Coordinate Transformations in LAMPAT 

Appendix B. Material Input for Smearing and Coordinate 

Transformation (DBMAT.IN) 

Appendix C. Material Input for ANSYS (MAT.FIL) 19 

Appendix D. ANSYS Input File (MODEL.TXT) 

Appendix E. Data Transfer Macros (MACRO.WRITE) 

Distribution List 

Report Documentation Page 

V 

vii 

1 

4 

7 

9 

15 

25 

33 

41 

47 

. . . 

111 
INTENTIONALLY Lm EL~NK. 
List of Figures 

Figure 1. Typical simple laminate structures. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 

Figure 2. A laminate structure requiring more complex coordinate 

orientations for analysis purposes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 

Figure 3. Alignment of local coordinate systems in ANSYS to facilitate 

analysis and postprocessing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 

Figure 4. Curved cross-section laminate structure. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 

,Figure A-l. Coordinate systems in LAMPAT and ANSYS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 

Figure A-2. Coordinate transformations for consistency within ANSYS 

and LAMPAT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 

Figure A-3. Comparison of default, global Cartesian, and local coordinate 

systems on the element coordinate systems for alignment of laminae 

properties and results . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ..-.............................................. 13 

V 
INTENTIONALLYLEFTBLANK. 

vi 
List of Tables 

Table A-l. Permutations of coordinate rotations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 

vii 
. . . 

VIII 
1. Introduction 

To properly analyze orthotropic larninar composites in structural finite element 

codes such as ANSYS,* it is necessary to align the coordinate systems of the 

laminae with the coordinate system of the analysis code.r This can be 

accomplished using the LAMPAT’ code. 

Typically, relatively simple laminate geometries have been analyzed in ANSYS, 

such as problems with structures wound on cylindrical mandrels or items 

machined from a ply-stacked composite stock, as shown in Figure 1. LAMPAT 

uses the local coordinate system reference for each element for smearing and 

unsmearing the element data. Models of these simple structures can be 

constructed and described with a single global coordinate system, which is the 

local coordinate orientation for all elements. Thus, it is relatively easy to 

properly align the material properties for analysis in ANSYS and LAMPAT. The 

global coordinate system may be cylindrical or Cartesian (Figure 1). ANSYS 

utilizes the element coordinate directions and the smeared properties of the 

elements to perform its analysis on an approximated laminate structure. 

LAMPAT analyzes the effect of the stresses on each element, or approximated 

laminate, to resolve the stresses and strains in the individual plies within that 

laminate. The material properties and orientations of each ply are contained in 

the LAMPAT files. 

This report describes how to use LAMPAT and ANSYS to analyze more complex 

geometry laminate structures. The structure in Figure 2 represents a laminar 

structure that results from ply stacking into a mold or onto a pattern of complex 

geometry to produce a final or near net shape part. The intralaminae coordinate 

referencing must be performed as it was previously, but additional effort is 

required to assure that the laminate is properly oriented, and the resultant 

stresses are referenced to the local coordinate system for each element. 

Using consistent local coordinate directions through the model greatly simplifies 

the postprocessing analysis of the results. Typically, when post-processing data 

from LAMPAT to ANSYS, the failure modes, failure criteria, and safety factors of 

the various regions in the model must be determined to properly observe the 

model’s response to the loading. For example, if a structure like the one in 

* Swanson Analysis Systems, Inc., P.O. Box 65, Johnson Road, Houston, PA 153424065. 

1 Bogetti, T. A., C. I?. R. Hoppel, and B. P. Burns. “A Software Tool for Analyzing and Designing 

Thick Laminated Composite Structures.” ARL-TR-890, U.S. Army Research Laboratory, Aberdeen 

Proving Ground, MD, September 1995. 

2 Bogetti, T. A., C. P. R. Hoppel, and W. H. Drysdale. “Three-Dimensional Effective Property 

and Strength Prediction of Thick Laminated Composite Media.” ARL-TR-911, U.S. Army Research 

Laboratory, Aberdeen Proving Ground, MD, October 1995. 

1 
GLClEAL CLINDERICAL CUURDINATE SYSTEM GLOBAL CARTESIAN CUURIIINATE SYSTEM 

Figure 1. Typical simple laminate structures. 

Figure 2. A laminate structure requiring more complex coordinate orientations for 

analysis purposes. 

Figure 3 is being analyzed as a pressurized container, the radial and hoop loads 

of the structure should probably be observed. If the conventional approach is 

used, hoop stress will be SX in some elements and SY in other elements. Radial 

stresses will behave similarly. Therefore, it will not be sufficient to plot SX to get 

radial stress and SY to get hoop stress, but it will be necessary to plot the failure 

mode to see if the model is behaving properly. This may become difficult in 

structures with complex shapes. If the materials are oriented so that the Y (and 

THETA [O]) direction for all of the elements are aligned, plotting SX will show 

radial stress for all elements, and SY will show hoop stress for all elements. 

It is easier to align the coordinate directions of the materials in the structure and 

observe the structure’s behavior in a few plots, than it is to keep all of the 

regions’ results and conditions and put them together like a puzzle to determine 
PLY IN-PLANE DIRECTIONS 

CIRE Y, THETA, AND Z 

LOCAL COORDINATE SYSTEMS 

YO Jt X0 

z 

yi9 f4-- z 19 Xl? 

GLOBAL CARTESIAN CODRDINATE SYSTEM 

IN ANSYS 

Figure 3. Alignment of local coordinate systems in ANSYS to facilitate analysis and 

postprocessing. 

the structure’s behavior. In global Cartesian coordinates in ANSYS, all elements 

have X, Y, and Z linear directions; stresses in postprocessing will be relative to 

this X-Y-Z order. When cylindrical coordinates are used either globally or 

locally, the order will be R-O-Z. Because LAMPAT uses the element coordinate 

systems for its transformations, it may be important to define them to be other 

than global Cartesian (the default system). This is particularly true when the 

global Cartesian system cannot properly represent the system being analyzed. 

But ANSYS can only specify an element’s coordinate system as global Cartesian 

or as a LOCAL coordinate system. It is important to align the elementcoordinate systems to best represent the structure under analysis. Mixed 

coordinate systems should be aligned to simplify postprocessing. 

This report describes the method for accomplishing this task. Appendices A-E 

include example input files for implementing this task. The tools required for 

this operation include: (1) LAMPAT for preprocessing (smear) the material 

properties for analyzing and postprocessing the solution (unsmear) results and 

writing the output files, (2) ANSYS for solving the finite-element problem, and 

(3) macros (macro.write and macro.read) for writing and reading files from 

ANSYS and into it. 

3 
2. Method 

To provide a simple example of modeling a structure with complex ply contours, 

a two-dimensional (2-D) cross section is examined. The structures can be 

represented as a series of arc and line segments. Several local cylindrical 

coordinate systems are used to describe these arcs in ANSYS. The local 

cylindrical coordinate system command is of the form: 

LOCAL,KCN,KCS,XC,YC,ZC,THXY,THYZ,THZX,l’ARl,PAR2, 

where KCN is the reference number for the coordinate system (11-N), 

KCS is the type of system (0 Cartesian, 1 cylindrical, 2 spherical, 3 toroidal), 

XC, XY, and XZ are the global Cartesian coordinates for the center of the local 

system, 

THXY is the rotation about local Z (X towards Y), 

THYZ is the rotation about local X (Y towards Z), 

THZX is the rotation about local Y (Z towards X), and 

PAR1 and PAR2 are used for describing elliptical shapes. 

The direction vectors for the Cartesian coordinate systems in ANSYS are X, Y, 

and Z. For cylindrical systems they are R, 0, and Z, where R is the radial 

distance from the center of the system in the YZ plane, 0 is the angle from the X 

axis in the YZ plane, and Z is the distance from the XY plane. 

A curved cross section of a lamina is most easily described with a cylindrical 

local coordinate system, as shown in Figure 4. Thus, the out-of-plane direction 

(3) in the local cylindrical system is X. The zero (1) and transverse (2) directions 

are relative to 0 and Z, which depend on the ply orientation within the laminae. 

For a unidirectional ply, the 1 direction would be 0, the Zdirection Z, and the 

3-direction X in the local cylindrical system. For a continuous layup along the 

pattern surface (Figure 3), the local coordinate systems will all use Y or 0 as the 1 

direction of the ply. This is because the descriptors for the Cartesian and 

cylindrical coordinate systems are given in the orders of X, Y, Z and R, 0, Z, 

respectively. This requires that local coordinate systems be constructed as 

necessary to maintain a continuity of Y and 0 for the adjacent elements in the 

two reference systems (Figure 4). 

With the local coordinate systems (LOCAL) created and referenced (CSYS) to 

construct the proper geometry of the cross section and continuity of the plies, 

these systems must be referenced using the ESYS command while creating the 

4 
Figure 4. Curved cross-section laminate structure. 

mesh (i.e., using an AMESH command). ESYS, KCN assigns a coordinate 

reference system to the element. The default state, ESYS, 0, assigns global 

Cartesian coordinates to the elements. The user may input (KCN) either 0 for 

global Cartesian or a local coordinate system (11-n). The local coordinate system 

must have been previously defined using the LOCAL command. Neither 1,2, or 

3 (global cylindrical, spherical, or toroidal) can be input to the ESYS command. 

Therefore, even for a model that can be built or described using the global 

cylindrical coordinate system, a local cylindrical coordinate system with its 

origin at 0, 0, 0 must be defined and referenced in the ESYS command to 

properly define the material properties at the element coordinate system level. 

Implementing this consistent direction reference will simplify the postprocessing 

of the results. The resultant stresses in ANSYS are provided by default and 

referenced to the global Cartesian reference system. The results can be presented 

relative to other coordinate’s systems using the RSYS command. The format of 

the RSYS command is RSYS, KCN. KCN can be 0 for global Cartesian, 1 for 

global cylindrical, 2 for global spherical, 11-n for local coordinate systems, or 

SOLU (in menu mode: AS CALCULATED) for reference to the element 

coordinate systems defined by the ESYS command. The results for any ANSYS 

analysis can be viewed (or printed) using RSYS (1 or 2, or 3 or 11-n). Only by 

using the ESYS command can the RSYS, SOLU command be used to get results at 

the same time relative to multiple coordinate systems. If the ESYS command is 

not implemented, the results relative to the single-selected coordinate system 

5 
wilI be applied to all elements. If no ESYS command is applied, the elements 

have their default elemental coordinate system, which is global Cartesian. 

The following steps outline a procedure for conducting a laminate structural 

analysis with ANSYS and LAMPAT. 

(1) Build a model in ANSYS using the LOCAL, CSYS, and ESYS commands to 

provide consistent fiber orientation within each ply of the structure (i.e., 

model.txt). In this example, the model.txt file includes all prep7 input, 

except for the material property data, the solution section, and entry into 

post1 including selecting the results set. If the menu mode is used, the 

menu paths for the commands may be obtained from the help menu. Enter 

the command into the “Help on” window in older versions of ANSYS or 

enter help, “command name,” in the command line in newer versions of 

ANSYS. At the bottom of the help page there will be a path(s) to the 

command entry point in the menus. 

(2) Create a material input deck for LAMPAT with the proper ply construction 

and orientations to match the desired directionality in the ANSYS model 

(i.e., 1 = Y, 2 = Z, 3 = X), (matdbin). Note, for these analyses, that the 

1 direction is considered structurally independent. That is, for example, a 

hoop winding is considered a “1” direction or a “0” around the mandrel, 

not a 90” winding as in conventional processing jargon. 

(3) Run LAMPAT as the preprocessor to create a material property input deck 

from matdbin to use in ANSYS (mat.fil). 

(4) To run ANSYS interactively, start ANSYS. Click on Preprocessor. Click on 

Material Props. Click on Read From File. Select mat.fil. Click on File. 

Click on Read Input From . . . . Select model-tit. In this example, the 

model will be run and solved, and ANSYS wilI be waiting in the post1 

postprocessor. 

(5) To get data for postprocessing in LAMPAT (you are still in ANSYS 

postprocessor), click on File. Click on Read Input From . . . . Select 

macro.write. This will create matid.fiI and stress.fil output files. Copy or 

move these files where they can be used with LAMPAT. 

(6) Using the postprocessor mode in LAMPAT, input matdb.in, matid.fil, and 

stress.fil when prompted. Use lampat.fil as the output file. (This file name 

will be used later to read data into ANSYS.) Copy or move lampat.fil to 

where it can be accessed in ANSYS. 

(7) In ANSYS in postl, click on File. Click on Read Input From . . . . Select 

macro.read (this macro reads data from the lampat.fil file). 

6 
(8) In ANSYS, execute the save command (either enter Save in the command 

line, or select the SAVE DB button with the mouse). This will save the 

etable data that is included in the file.db file, not in the result file, file.rst. 

This process creates element table data to use in ANSYS postprocessing. The 

results in these tables will be relative to the local coordinate system for each 

element. Further use of the RSYS command in post1 will not affect the element 

table data plotting (Plot>Results>Contours>Elem table), but it will affect the data 

plotted in the ANSYS results files (Plot>Results>Contours>nodal or elem). 

The macro.write and macro.read files are shown in Appendix E. They were 

written to facilitate the data transfer between ANSYS and LAMPAT. In order for 

all of the LAMPAT data to postprocess in ANSYS via etable data, both the 

macro.write and macro.read files must be utilized. The resultant etable data will 

be SX, SY, SZ, SYZ, SXZ, SXY, SAFE-F, FAIL-M, and CRIT-I’. Three C4, C5, and 

C6 auxiliary files are available. 

3. Conclusions 

The combined use of LAMPAT and ANSYS provides a very powerful tool in 

analyzing laminated structures. LAMPAT’s use of element coordinate systems 

for transforming properties and results requires that care be used in ANSYS to 

properly define the element coordinate systems to represent the structure under 

analysis. The directional properties of the materials must be properly aligned to 

the structure. The local coordinate systems in ANSYS, in conjunction with the 

ANSYS co mmands of ESYS and RSYS, allows for the proper modeling of 

laminate structures that have ply layers following simple or complex contours. 

With proper coordinate system rotations and ESYS and RSYS commands, 

continuous ply orientation along curvilinear profiles can be more easily modeled 

and postprocessed. This permits the stress state of a structure, such as hoop or 

radial stress, to be observed in a single plot in ANSYS when the RSYS, SOLU 

(“RSYS as computed” in menu mode) command has been issued. ANSYS cannot 

assign the global cylindrical as an element’s coordinate system. Even when the 

global cylindrical coordinate system can be utilized to construct the geometry, a 

LOCAL coordinate cylindrical system (with its origin at 0, 0, 0) must be created 

to use as input to the ESYS command. The ESYS command can only accept input 

(KCN) as 0 or n, where n is an integer >lO. 

When analyzing isotropic materials in ANSYS, the ESYS command default to 

global Cartesian is sufficient because the directional properties are all equal. 

Using other coordinate system results, such as the global cylindrical coordinate 

system (RSYS, l), to analyze isotropic materials will also provide the proper 

results. 

7 
INTE~I~NALLY n3r BLANK. 
Appendix A. Coordinate Transformations in LAMPAT 

9 
10 
The rotations of BETA (B), PHI (@), and PSI (‘I’) correlate to the rotation of Y 

towards Z, Z towards X, and X towards Y, as shown in Figures A-l and A-2. 

LAMPAT solves the coordinate rotations only in the order of BETA, PHI, and 

PSI, so there are a limited number of resultant rotations. The permutations are 

shown in Table A-l. The values of 2,4, and 7 are provided only to aid in tracking 

the directional changes caused by the rotations. The values given for EX, EY, and 

EZ represent smeared elastic moduli for a nonisotropic material calculated by 

LAMP4T. The BETA, PHI, PSI (O,O,O) state reflects the results of the calculated 

directional values based on the percentage of fibers from the various fiber 

directions inputted for each laminate, without regard to the laminate’s 

orientation in the structure under analysis. The laminate is oriented to the 

referenced coordinate system with the B, @, and Y terms. Users might configure 

a simple or known case, such as a unidirectional lay up, and make a trial run to 

understand the transformations and orientations used in their models. It may be 

difficult to make simple checks on complex geometry, complex lay up problems 

since concepts such as the 1, 2, and 3 directions become muddled. Figure A-3 

shows the continuity of element coorhinate direction obtained by properly 

assigning coordinate systems. 

X,Y,Z 

REPRESENT STANDARD 

COMPOSITE <LAMPAT> 

CCICIRDINATE DIRECTIONS 

R,Y,f 

REPRESENT STANDARD 

ANSYS 

COORDINATE DIRECTIONS 

X’,Y’,Z’ 

REPRESENT THE 

LOCAL ELEMENT 

COORDINATE DIRECTIONS 

ROTATION q IF BETA B 

MOVES Y’ TOWARDS Z’ 

RDTATIEIN OF PHI * 

MOVES Z’ TOWARDS X’ 

RDTATIIIN OF PSI Y 

MOVES X’ TOWARDS Y’ 

Figure A-l. Coordinate systems in LAMPAT and ANSYS. 

11 
TO GO FROM STANDARD LAMPAT TO STANDARD ANSYS CIIORDINATE SYSTEMS 

THE ROTATION IS 8 = 90, @ = 90, ‘Z’ = 0 

Z START STATE 

t 

IN LAMPAT 

2’ 

A 

8= 90 

Z’ -d- Y’ 

X’ 

a 

4 

Y’ 

Z’ 

X’ 

@= 90 

a 

Y’ 

X’ 

I-, 

END STATE 

Z’ 

TO GO FROM STANDARD LAMPAT TO CYLINDERICAL ANSYS COORDINATE SYSTEMS 

THE ROTATION IS 8 = 90, @ = 90, 2’ = 0 

Figure A-2. Coordinate transformations for consistency within ANSYS and LAMPAT. 

Table A-l. Permutations of coordinate rotations. 

12 
X Iff Y 

2 

GLIIBAL CARTESIAN CIIIIRDINATE SYSTEM GLOBAL AND LOCAL CIXIRDINATE SYSTEMS 

ELEMENT COORDINATE SYSTEMS ARE NOT ELEMENT CDORDINATE SYSTEMS ARE 

CilNTINUOUS AROUND 90 DEGREE FILLET CONTINUOUS AROUND 90 DEGREE FILLET 

Figure A-3. Comparison of default, b olobal Cartesian, and local coordinate systems on the 

element coordinate systems for ali,gnment of laminae properties and results. 

13 
14 
Appendix B. Material Input for Smearing and Coordinate 

Transformation (DBMAT.IN) 

This appendix appears in its original form, without editorial change. 

15 
16 
1.0, 

0.0, 

2.0, 

1.0, 

1.0, 

2.0, 

0.0, 

2.0, 

1.0, 

1.0, 

3.0, 

0.0, 

2.0, 

1.0, 

1.0, 

4.0, 

0.0, 

2.0, 

1.0, 

1.0, 

5.0, 

0.0, 

2.0, 

1.0, 

1.0, 

6.0, 

90.0, 

2.0, 

1.0, 

1.0, 

8 

1 

2.0, 

-90.0, 

2.0, 

0.005, 

0.005, 

2.0, 

-90.0, 

2.0, 

0.005, 

0.005, 

2.0, 

-90.0, 

2.0, 

0.005, 

0.005, 

2.0, 

-90.0, 

2.0, 

0.005, 

0.005, 

2.0, 

90.0, 

2.0, 

0.005, 

0.005, 

2.0, 

90.0, 

2.0, 

0.005, 

0.005, 

1.0, 

10.0, 

0.0, 

0.0, 

0.0, 

90.0, 

10.0, 

0.0, 

0.0, 

0.0, 

90.0, 

10.0, 

0.0, 

0.0, 

0.0, 

90.0, 

10.0, 

0.0, 

0.0, 

0.0, 

90.0, 

10.0, 

90.0, 

0.0, 

0.0, 

90.0, 

10.0, 

90.0, 

0.0, 

0.0, 

90.0, 

0.0 

0.0 

0.0 

-0.0001 

-0.0001 

0.0 

0.0 

0.0 

-0.0001 

-0.0001 

0.0 

0.0 

0.0 

-0.0001 

-0.0001 

0.0 

0.0 

0.0 

-0.0001 

-0.0001 

0.0 

0.0 

0.0 

-0.0001 

-0.0001 

0.0 

0.0 

0.0 

-0.0001 

-0.0001 

2.0, 1.8893-04 ! 

7.15003+06, 2.133+06, 2.133+06 ! 

0.499, 0.306, 0.296 ! 

0.710E+06, 0.980E+06, 0.9803+06 ! 

2.300E-06, 1.8503-05, 1.850E-05 ! 

0.0, 0.0, 0.0 ! (1) 

0.0, 0.0, 0.0 ! 

0.0, 0.0, 0.0 ! 

0.0, 0.0, 0.0 ! 

0.0, 0.0, 0.0 ! 

243.003+03, 7.00E+03, 8.503+03 ! (2) 

177.003+03, 30.603+03, 35.003+03 ! 

, 

I 

! 

I 

I 

I 

, 

! 

! 

! 

! 

I 

I 

, 

! 

I 

I 

! 

I 

! 

! 

! 

! 

NO. OF REGIONS IN THE DATABASE 

NO. OF MATERIALS IN DATABASE 

REG-ID, FAIL CRT, ITERS, ITEXT 

BETA-(X), PHI:(Y), SI-(Z), --- 

NPLY, REG-TYP, ---, --- 

MAT-ID, THICKNESS, ANGLE, TEMP 

MAT-ID, THICKNESS, ANGLE, TEMP 

REG-ID, FAIL-CRT, ITERS, ITEXT 

BETA-(X), PHI-(Y), SI-(Z), --- 

NPLY, REG-TYP, ---, --- 

MAT-ID, THICKNESS, ANGLE, TEMP 

MAT-ID, THICKNESS, ANGLE, TEMP 

REG-ID, FAIL-CRT, ITERS, ITEXT 

BETA-(X), PHI-(Y), SI-(Z), --- 

NPLY, REG-TYP. ---, --- 

MAT-ID, THICKNESS, ANGLE, TEMP 

MAT-ID, THICKNESS, ANGLE, TEMP 

REG-ID, FAIL-CRT, ITERS, ITEXT 

BETA-(X), PHI-(Y), SI-(Z), --- 

NPLY, REG-TYP, ---, --- 

MAT-ID, THICKNESS, ANGLE, TEMP 

MAT-ID, THICKNESS, ANGLE, TEMP 

REG_ID. FAIL-CRT, ITERS, ITEXT 

! BETA-(X), PHI-(Y), SIT(Z), --- 

! NPLY, REG-TYP, ---, --- 

! MAT ID, THICKNESS, ANGLE, TEMP 

! MATIID, THICKNESS, ANGLE, TEMP 

! REG ID, 

! BETA_(X), 

! NPLY, 

! MAT ID, 

! MAT-ID, - 

FAIL-CRT, ITERS, ITEXT 

PHI-.(Y), SI-(Z), --- 

REG-TYP, ---, --- 

THICKNESS, ANGLE, TEMP 

THICKNESS, ANGLE, TEMP 

MAT-ID, MAT-TYPE, 

El, E2. 

NU23, Nu13, 

G23, G13, 

Al, JQ, 

vi-, vM2, 

m4. VM5, 

VM7, m8, 

--- --- 

--- _-- 

XlT, X2T, 

XlC, x2c. 

-DENS(SZ-GLASS/ 

E3 EPOXY) 

Nu12 

G12 

A3 

VM3 VON MISES 

VM6 

VI49 

--- 

X3T MAXIMUM 

X3C STRESS 

15.703+03, 17.00E+03, 15.703+03 ! X23, x13, x12 

17 
0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0340, 0.0033, 0.0040 

0.0248, 0.0144, 0.0164 

0.0221, 0.0173, 0.0160 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

7.15003+06, 2.13E+06, 2.133+06 

0.499, 0.306, 0.296 

0.710E+06, O.Y80E+06, O.Y80E+06 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

0.0, 0.0, 0.0 

I --_ 

! -__ 

! (3) YlT, 

I YlC, 

, Y23, 

! --- 

I --- 

! (4) XLT, 

1 XLC, 

I MLl, 

1 MTl, 

, MSl, 

! (5) XlT, 

I X2T, 

1 s12, 

! --- 

I --_ 

! (6) El, 

I NU23, 

1 G23, 

, K, 

! YlT, 

! (7) FEl, 

t FE4, 

I FE7, 

! FElO, 

I FE13, 

! (8) ml, 

! HA4, 

I HA7, 

I HAlO, 

1 HA13, 

-_- 

Y2T, 

Y2C, 

Y13, 

--- 

_-- 

XTT , 

XTC, 

MLZ, 

MT2, 

MS2, 

XlC, 

x2c, 

F12, 

_-- 

_-- 

E2, 

NU13, 

G13, 

ALPHA, 

YlC, 

FE2, 

FES, 

FE8, 

FEll, 

FE14, 

H=, 

m5, 

H=, 

HAll, 

HA14, 

-_- 

-__ 

Y3T MAXIMUM 

Y3C STRAIN 

Y12 

--_ 

--- 

HPD HYDROSTATIC 

S PRESSURE 

LTP 

TTP 

STP 

--- TSAI-WU 

--- 

F23 

___ 

--- 

E3 CHRISTENSEN 

NUl.2 

G12 

--- 

FE3 FENG 

FE6 

FEY 

FE12 

FE15 

HA3 MODIFIED 

HA6 HASHIN 

HAY 

HA12 

HA15 
Appendix C. Material Input for ANSYS (MAT.FIL) 

This appendix appears in its original form, without editorial change. 

19 
20 
/COM, LAMPAT (VERSION 4.1) MATERIAL FILE FOR ANSYS 5.5 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EX , 1 , 1, 0.1130000E+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EY , 1 I 1, 0.71500003+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EZ , 1 I 1, 0.21300003+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,KUXY, 1 I 1, 0.3060000E+00, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,GXY , 1 I 1, 0.98000003+06, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,GYZ, 1 , 1, 0.98000003+06, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,GXZ , 1 I 1, 0.70999993+06, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,PRXY, 1 I 1, 0.48360843-01, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,PRYZ, 1 , 1, 0.29600013+00, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,PRXZ, 1 I 1, 0.26472773+00, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EX , 2 I 1, 0.1130000E+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EY , 2 I 1, 0.71500003+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EZ , 2 , 1, 0.21300003+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,NUXY, 2 , 1, 0.3060000E+00, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,GXY , 2 , 1, 0.98000003+06, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,GYZ, 2 , 1, 0.98000003+06, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,GXZ , 2 , 1, 0.70999993+06, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

21 
MPDATA,PRXY, 2 , 1, 0.48360843-01, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,PRYZ, 2 , 1, 0.29600013+00, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,PRXZ, 2 I 1, 0.26472773+00, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EX , 3 I 1, 0.1130000E+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EY , 3 I 1, 0.71500003+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EZ , 3 I 1, 0.21300003+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,NUXY, 3 I 1, 0.3060000E+00, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,GXY , 3 I 1, 0.98000003+06, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,GYZ, 3 I 1, 0.98000003+06, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,GXZ , 3 , 1, 0.70999993+06, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,PRXY, 3 I 1, 0.48360843-01, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,PRYZ, 3 , 1, 0.29600013+00, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,PRXZ, 3 , 1, O-26472773+00, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EX , 4 I 1, 0.1130000E+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EY , 4 I 1, 0.71500003+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EZ , 4 I 1, 0.21300003+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,NUXY, 4 , 1, 0.3060000E+00, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,GXY , 4 , 1, 0.9800000E+06, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

22 
MPDATA,GYZ, 4 , 1, 0.98000003+06, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,GXZ , 4 I 1, 0.70999993+06, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,PRXY, 4 I 1, 0.48360843-01, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,PRYZ, 4 , 1, 0.2960001E+00, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,PRX.Z, 4 I 1, O-26472773+00, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EX , 5 , 1, 0.1130000E+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EY , 5 I 1, 0.71500003+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EZ , 5 I 1, 0.21300003+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,NUXY, 5 I 1, 0.3060000E+00, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,GXY , 5 , 1, 0.98000003+06, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,GYZ, 5 I 1, 0.9800000E+06, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,GXZ , 5 I 1, 0.70999993+06, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,PRXY, 5 I 1, 0.48360843-01, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,PRYZ, 5 8 1, 0.29600013+00, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,PRXZ, 5 , 1, O-26472773+00, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EX , 6 , 1, 0.1130000E+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EY , 6 t 1, 0.71500003+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

MPDATA,EZ , 6 , 1, 0.2130000E+07, 

MPTEMP 

MPTEMP, 1, 0.0000000E+00, 

23 
MPDATA,NUXY, 

MPTEMP 

MPTEMP, 1, 

MPDATA,GXY , 

MPTEMP 

MPTEMP, 1, 

MPDATA,GYZ, 

MPTEMP 

MPTEMP, 1, 

MPDATA,GXZ , 

MPTEMP 

MPTEMP, 1, 

MPDATA,PRYiY, 

MPTEMP 

MPTEMP, 1, 

MPDATA,PRYZ, 

MPTEMP 

MPTEMP, 1, 

MPDATA,PRXZ, 

6 , 1, 0.3060000E+00, 

0.0000000E+00, 

6 r 1, 0.98000003+06, 

0.0000000E+00, 

6 , 1, 0.98000003+06, 

0.0000000E+00, 

6 , 1, 0.70999993+06, 

O.b000000E+00, 

6 , 1, 0.48360843-01, 

0.0000000E+00, 

6 , 1, 0.29600013+00, 

0.0000000E+00, 

6 , 1, O-26472773+00, 

24 
Appendix D. ANSYS Input File (MODEL.TXT) 

This appendix appears in its original form, without editorial change. 

25 
INTENTIONALLY cm BLmK. 

26 
If using the menu mode, the menu paths for the commands may be 

obtained through the help menu. Enter the command into the “Help on” 

window; a path(s) to the command entry point in the menus will be at the 

bottom of the help page. 

/title, LAYUP: O/90 

! DEFINE MATERIAL PROPERTIES 

! CHOOSE ELEMENT TYPE Z-D STRUCTm 

et,l,42,,,0 

et,2,42,,,0 

et,3,42,,,0 

et,4,42,,,0 

et,5,42,,,0 

et,6,42,,,0 

! CREATE LOCAL COORDINATE SYSTEMS 

! MENU PATH FOR LOCAL: Utility Menu >WorkPlane aLocal Coordinate Systems 

! Xreate Local CS 

local,ll,l,-l,-l,O 

local,l2,1,1,-l,O 

local,l3,1,1,1,0 

local,l4,1,-l,l,O 

loca1,15,0,0,0,0,90,O,O, 

!BUILD MODEL 

!CREATE GEOMETRY 

!ASSIGN KEYPOINTS 

!NOTE MODEL COULD HAVE BEEN BUILT BY SYMETRIES 

! CREATE MODEL KEYPOINTS 

csys, 11 

k,1,.5,270 

csys,l2 

k,2,.5,270 

k,3,.5,0 

csys,l3 

k,4,.5,0 

k,5,.5,90 

csys,ll 

k,6,.5,90 

k,7,.5,180 

csys,11 

k,8,.5,180 

k,9,1,270 

csys,l2 

k,10,1,270 

k,ll,l,O 

csys,l3 

k,12,1,0 

27 
k,13,1,90 

csys,14 

k,14,1,90 

k,15,1,180 

csys, 11 

k,16,1,180 

!DEFINE LINES 

csys, 11 

1,8,1,16 

1,16,9,16 

csys,12 

1,2,3,16 

1,10,11,16 

csys,13 

1,4,5,16 

1,12,13,16 

csys,14 

1,6,7,16 

1,14,15,16 

csys ‘ 0 

1,1,2,40 

1,9,10,40 

1,3,4,40 

1,11,12,40 

1,5,6,40 

1,13,14,40 

1,7,8,40 

1,15,16,40 

1,1,9,10 

1,2,10,10 

1,3,11,10 

1,4,12,10 

1,5,13,10 

1,6,14,10 

1,7,15,10 

1,8,16,10 

!CREATE AREAS 

a,9,10,2,1 

a,10,11,3,2 

a,ll,l2,4,3 

a,l2,13,5,4 

a,13,14,6,5 

a,14,15,7,6 

a,15,16,8,7 

a,16,9,1,8 

!ASSIGN ELEMENT TYPE, MATERIALS, ELEMENT COORDINATE SYSTEMS 

!CREATE MESH 

! MENU PATHS FOR ESYS: 

28 
! Main Menu >Preprocessor aCreate >Elements >Elem Attributes 

! or Main Menu >Preprocessor >Define >Default Attribs 

esys, 11 

mat,1 

tse,l 

amesh, 

esys, 12 

mat,2 

type,2 

amesh, 

esys,13 

mat,3 

tnx,3 

amesh, 

esys,14 

mat,4 

type,4 

amesh, 

esys,l5 

mat,5 

tme,5 

amesh,1,5,4 

esys, 0 

mat,6 

tse,6 

amesh,3,7,4 

esys, 0 

! CONNECT THE MESHED AREA ELEMENTS TOGETHER 

! AND COMBINE COMMON NODES 

nummrg,node 

! CREATE (SAVE) file.db 

save 

! LEAVE PREP7 

fini 

!ENTER SOLUTION PHASE 

/solu 

!USE AUTOMATIC TIME STEPPING FOR NON-LINEAR PROBLEMS. 

autots,on 

! CONSTRAIN STRUCTURE IN SPACE 

csys, 0 

nsel,s,loc,y,-1.5,1.5 

nsel,r,loc,x,o 

d,all,ux,o 

nsel,all 

nsel,s,loc,y,O 

nsel,r,loc,x,-1.5,1.5 

d,all,uy,O 

29 
nsel,all 

! APPLY INTERNAL PRESSURE TO STRUCTURE 

csys, 11 

nsel,s,loc,x,.5 

sf,all,pres,lOOO 

nsel,all 

csys,12 

nsel,s,loc,x,.5 

sf,all,pres,lOOO 

nsel,all 

csys,13 

nsel,s,loc,x,.5 

sf,all,pres,lOOO 

.nsel,all 

csys,14 

nsel,s,loc,x,.5 

sf,all,pres,lOOO 

nsel,all 

csys, 0 

nsel,s,loc,x,-1.5,1.5 

nsel,r,loc,y,-1,l 

sf,all,pres,lOOO 

nsel,all 

csys, 0 

nsel,s,loc,x,-1,l 

nsel,r,loc,y,-1.5,l.S 

sf,all,pres,lOOO 

nsel,all 

csys, 0 

!SOLVE THE PROBLEM 

solve 

! REWRITE file.db INCLUDING SOLUTION COMMANDS 

save 

! LEAVE SOULUTION PHASE 

fini 

30 
! ENTER POST PROCESSOR 

/post1 

! INPUT RESULT SET 

set,l,l 

! PRESENT RESULTS IN ELEMENT COORDINATE SYSTEMS 

! MENU PATHS FOR RSYS: 

! Main Menu > General Postproc > Options for Outp 

! or Utility > List >Results> Options 

rsys,solu 

! PLOT AREAS 

aplo 

! (WAIT IN INTERACTIVE MODE) 

! BEGIN POSTPROCESSING PROCEDURE FOR LAMPAT BY CREATING 

! MATID.FIL AND STRESS.FIL FILES. 

! AFTER READING IN THE MACRO.WRITE, POSTPROCESSING IN LAMPAT, 

! AND WRITING THE ETABLE DATA WITH MACRO.REAO, 

! SAVE THE DATA BY WRITING TO file.db (ENTER SAVE IN THE COMMAND LINE 

! OR SELECT THE SAVE DB BUTTON WITH THE MOUSE). THE ETABLE DATA IS 

! WRITTEN INTO THE file.db, NOT THE file.rst FILE. 

31 
INTENTIONALLY Lm-r m.mix. 

32 
Appendix E. Data Transfer Macros (MACRO.WRITE) 

This appendix appears in its original form, without editorial change. 

33 
34 
Macro Write. This is used to write ANSYS data into files for use in LAMPAT. 

Associate materials and stresses with element numbers are included. 

/corn 

/corn 

/corn MACRO FOR STRESS - - - - - - - - - - - 

/corn 

/corn 

*get,numelem,elem,,count 

*dim,elenum,array,numelem,l,l 

*do,i,l,numelem 

elenum(i)=i 

*enddo 

etable,sx,s,x 

etable,sy,s,y 

etable,sz,s,z 

etable,syz,s,yz 

etable,sxz,s,xz 

etable,sxy,s,xy 

*dim,esx,array,numelem,l,l 

*dim,esy,array,numelem,l,l 

*dim,esz,array,numelem,l,l 

*dim,esyz,array,numelem,l,l 

*dim,esxz,array,numelem,l,l 

*dim,esxy,array,numelem,l,l 

*vget,esx(l),elem,l,etab,sx 

*vget,esy(l),elem,l,etab,sy 

*vget,esz(l),elem,l,etab,sz 

*vget,esyz(l),elem,l,etab,syz 

*vget,esxz(l),elem,l,etab,sxz 

*vget,esxy(l),elem,l,etab,sxy 

*cfopen,stress,fil 

*~rite,elenum(l),esx~l~,esy~l~,esz~l~,esy~~l~,esx~~~~~esxY~l~ 

/corn The following format line may vary from one LAMPAT version 

/corn to another. Be sure to be consistent and large enough for 

/corn your model. 

(f6.0,/,6e13.5) 

*cfclose 

/corn 

/corn 

/corn MACRO FOR STRAIN - - - - - - - - - - - 

/corn 

/corn 

/corn Users might want to remove the macro for 

/corn the strain section. Its output was not 

/corn used in this example. It may consume 

35 
/corn a significant amount of time for a large model. 

etable,ex,epto,x 

etable,ey,epto,y 

etable,ez,epto,z 

etable,eyz,epto,yz 

etable,exz,epto,xz 

etable,exy,epto,xy 

*dim,epsx,array,numelem,l,l 

*dim,epsy,array,numelem,l,l 

*dim,epsz,array,numelem,l,l 

*dim,epsyz,array,numelem,l,l 

*dim,epsxz,array,numelem,l,l 

*dim,epsxy,array,numelem,l,l 

*vget,epsx(l),elem,l,etab,ex 

*vget,epsy(l),elem,l,etab,ey 

*vget,epsz(l),elem,l,etab,ez 

*vget,epsyz(l),elem,l,etab,eyz 

*vget,epsxz(l),elem,l,etab,exz 

*vget,epsxy(l),elem,l,etab,exy 

*cfopen,strain,fil 

*~rite,elenum(l),epsx~l),epsy~l~,epsz(l~,epsy~~~~~ePsx~~~~~ePsxY~~~ 

/corn The following format line may vary from one LAMPAT version 

/corn to another. Be sure to be consistent and large enough for 

/corn your model. 

(f6.0,/,6e13.5) 

*cfclose 

/corn 

/corn 

/corn MACRO FOR MATERIAL ID - - - - - - - - - 

/corn 

/corn 

*cfopen,matid,fil 

*do,i,l,numelem 

*get,ml,elem,i,attr,mat 

*vwrite,i,ml 

(2f13.5) 

*enddo 

*cfclose 

MACRO.READ 

This is used to read LAMPAT data into ANSYS for postprocessing. It transfers 

stresses, strains, failure mode, safety factor, ply failure, and XXXX into element 

data tables (etable). 

/corn 

36 
/corn 

/corn MACRO FOR READING - - - - - - - - - - - 

/corn 

/corn 

*get,numelem,elem,,count 

numtot=numelem*7 

*dim,elenum,array,numelem,I,I 

*do,i,l,numelem 

elenum(i)=i 

*enddo 

*dim,a,array,numtot,l,l 

*dim,al,array,numelem,I,l 

*dim,a2,array,numelem,l,l 

*dim,a3,array,numelem,l,l 

*dim,a4,array,numelem,l,l 

*dim,a5,array,numelem,l,l 

*dim,a6,array,numelem,l,l 

*vread,a(l),lampat,fil 

/corn The following format line may vary from one LAMPAT version 

/corn to another. Be sure to be consistent and large enough for 

/corn your model. 

(f6.0,/,6e13.5) 

*do,i,l,numelem 

k=(i-1)*7 

aI(i)=a(k+2) 

a2(i)=a(k+3) 

a3(i)=a(k+4) 

a4(i)=a(k+S) 

a5(i)=a(k+6) 

a6(i)=a(k+7) 

*enddo 

*do,i,l,numelem 

desol,i,all,eppl,x,al(i) 

desol,i,all,eppl,y,a2(i) 

desol,i,all,eppl,z,a3(i) 

desol,i,all,eppl,yz,a4(i) 

desol,i,all,eppl,xz,a5(i) 

desol,i,all,eppl,xy,a6(i) 

*enddo 

etable,safe-f,eppl,x 

etable,fail-m,eppl,y 

etable,crit-p,eppl,z 

etable,c4,eppl,yz 

etable,c5,eppl,xz 

etable,c6,eppl,xy 

37 
Macro.read uses the standard LAMPAT code processing data file, which 

is named lampat.fil prior to executing this macro. This macro writes information 

(safety factor data, failure mode data, and ply failure data) into etable data as 

plastic strain. To examine the plastic strain in the model, this must be done prior 

to executing the macro. The following is an alternative macro that uses the 

ANSYS smisc data terms as portals for the LAMPAT results. 

/corn 

/corn 

/corn MACRO FOR READING - - - - - - - - - - - 

/corn 

/corn 

*get,numelem,elem,,count 

numtot=numelem*7 

*dim,elenum,array,numelem,l,l 

*do,i,l,numelem 

elenum(i)=i 

*enddo 

*dim,a,array,numtot,l,l 

*dim,al,array,numelem,l,l 

*dim,a2,array,numelem,l,l 

*dim,a3,array,numelem,l,l 

*dim,a4,array,numelem,l,l 

*dim,aS,array,numelem,l,l 

*dim,a6,array,numelem,l,l 

*vread,a(l),lampat.fil 

/corn The following format line may vary from one LAMPAT version 

/corn to another. Be sure to be consistent and large enough for 

/corn your model. 

(f6.0,/,6e13.5) 

*do,i,l,numelem 

k=(i-1)*7 

al(i)=a(k+2) 

a2(i)=a(k+3) 

a3(i)=a(k+4) 

/corn Since a4, a5, and a6 are currently not used, they are not read. 

/corn To save time, remove them in the LAMPAT code to save time 

/corn when running large models. 

*enddo 

/corn The selection of the variable term used to 

/corn read data into the element data tables in 

/corn ANSYS varies with the element type used (i.e. 

/corn SOLID 42). If the user wants to get 

/corn results on the smisc data, other terms should 

/corn be used. Alternatively, if the user postprocesses 

38 
/corn the ANSYS data (i.e. smisc values) 

/corn prior to reading in the lampat results (that 

/corn is prior to executing macro.read), the results 

/corn will not be corrupted by this read in data. 

etable,safe-f,smisc,l 

etable,fail-m,smisc,Z 

etable,crit-p,smisc,3 

*do,i,l,numelem 

detab,i,safe-f,al(i) 

detab,i,fail-m,a2(i) 

detab,i,crit-p,a3(i) 

*enddo 

39 
INTENTIONALLYLEETBLANK. 

40 
NO. OF 

COPIES 

2 

1 

1 

1 

ORGANIZATION 

DEFENSE TECHNICAL 

INFORMATION CENTER 

DTIC OCA 

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HQDA 

DAM0 FDT 

400 ARMY PENTAGON 

WASHINGTON DC 20310-0460 

OSD 

OUSD(A&T)/ODDR&E(R) 

DR R J TREW 

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WASHINGTON DC 20301-3800 

COMMANDING GENERAL 

US ARMY MATERIEL CMD 

AMCRDA TF 

5001 EISENHOWER AVE 

ALEXANDRIA VA 22333-0001 

INST FOR ADVNCD TCHNLGY 

THE UNIV OF TEXAS AT AUSTIN 

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MATH SC1 CTR EXCELLENCE 

MADN MATH 

THAYER HALL 

WEST POINT NY 109961786 

DIRECTOR 

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41 
NO. OF 

COPIES ORGANIZATION 

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3 DIRECTOR 

US ARMY RESEARCH LAB 

AMSRL OF’ SD TL 

2800 POWDER MILL RD 

ADELI’HI MD 20783-1145 

1 DM’Y ASST SECY FOR R&T 

SARD l-T 

THE PENTAGON 

RM 3EA79 

WASHINGTON DC 20301-7100 

1 COMMANDER 

US ARMY MATERIEL CMD 

AMXMI INT 

5001 EISENHOWER AVE 

ALEXANDRIA VA 22333-0001 

4 COMMANDER 

US ARMY ARDEC 

AMSTA AR CC 

G PAYNE 

J GEHBAUER 

C BAULIEU 

H OPAT 

PICATINNY ARSENAL NJ 

07806-5000 

2 COMMANDER 

US ARMY ARDEC 

AMSTA AR AE WW 

E BAKER 

J PEARSON 

PICATINNY ARSENAL NJ 

07806-5000 

1 COMMANDER 

US ARMY ARDEC 

AMSTA AR FSE 

PICATINNY ARSENAL NJ 

07806-5000 

NO. OF 

COPIES ORGANIZATION 

1 COMMANDER 

US ARMY ARDEC 

AMSTA AR TD 

C SPINELLI 

PICATINNY ARSENAL NJ 

0780&5000 

6 COMMANDER 

US ARMY ARDEC 

AMSTA AR CCH A 

W ANDREWS 

S MUSALLI 

R CARR 

M LUCIANO 

E LOGSDEN 

T LOUZEIRO 

PICATINNY ARSENAL NJ 

078065000 

1 COMMANDER 

US ARMY ARDEC 

AMSTA AR CCH I’ 

J LUTZ 

PICATINNY ARSENAL NJ 

078065000 

1 COMMANDER 

US ARMY ARDEC 

AMSTA AR FSF T 

C LIVECCHIA 

PICATINNY ARSENAL NJ 

0780&5000 

1 COMMANDER 

US ARMY ARDEC 

AMSTA ASF 

PICATINNY ARSENAL NJ 

078065000 

1 COMMANDER 

US ARMY ARDEC 

AMSTA AR QAC T C 

C PATEL 

PICATINNY ARSENAL NJ 

07806-5000 

1 COMMANDER 

US ARMY ARDEC 

AMSTA AR M 

D DEMELLA 

PICATINNY ARSENAL NJ 

07806-5000 

42 
NO. OF 

COPIES ORGANIZATION 

2 COMMANDER 

US ARMY ARDEC 

AMSTA AR FSP G 

M SCHIKSNIS 

D CARLUCCI 

PICATINNY ARSENAL NJ 

07806-5000 

1 COMMANDER 

US ARMY ARDEC 

AMSTA AR FSP A 

I=’ KISATSKY 

PICATINNY ARSENAL NJ 

07806-5000 

2 COMMANDER 

US ARMY ARDEC 

AMSTA AR CCH C 

H CHANIN 

S CHICO 

PICATINNY ARSENAL NJ 

0780~.%5000 

1 COMMANDER 

US ARMY ARDEC 

AMSTA AR QAC T 

D RIGOGLIOSO 

PICATINNY ARSENAL NJ 

07806-5000 

1 COMMANDER 

US ARMY ARDEC 

AMSTA AR WET 

T SACHAR 

BLDG 172 

PICATINNY ARSENAL NJ 

078065000 

1 US ARMY ARDEC 

INTELLIGENCE SPECIALIST 

AMSTA AR WEL F 

M GUERRIERE 

PICATINNY ARSENAL NJ 

07806-5000 

NO. OF 

COPIES ORGANIZATION 

9 COMMANDER 

US ARMY ARDEC 

AMSTA AR CCH B 

P DONADIA 

F DONLON 

I’ VALENTI 

C KNUTSON 

G EUSTICE 

S PATEL 

G WAGNECZ 

R SAYER 

F CHANG 

PICATINNY ARSENAL NJ 

07806-5000 

6 COMMANDER 

US ARMY ARDEC 

AMSTA AR CCL 

F PUZYCKI 

R MCHUGH 

D CONWAY 

E JAROSZEWSKI 

R SCHLENNER 

M CLUNE 

PICATINNY ARSENAL NJ 

07806-5000 

5 PM ARMS 

SFAE GCSS SD 

COL SLEDGE 

M DEVINE 

W DEMASSI 

J PRITCHARD 

S HROWNAK 

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07806-5000 

2 PEO FIELD ARTILLERY SYS 

SFAE FAS PM 

H GOLDMAN 

T MCWILLIAMS 

PICATINNY ARSENAL NJ 

07806-5000 

1 COMMANDER 

US ARMY ARDEC 

AMSTA AR WEA 

J BRESCIA 

PICATINNY ARSENAL NJ 

07806-5000 

43 
NO. OF 

COPIES ORGANIZATION 

1 DIRECTOR 

AIR FORCE RESEARCH LAB 

MLLMD 

D MIRACLE 

2230 TENTH ST 

WRIGHT PATTERSON AEB OH 

454337817 

2 COMMANDER 

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AVIATION APPLIED TECH DIR 

J SCHUCK 

F-T EUSTIS VA 23604-5577 

1 BENET LABORATORIES 

AMSTA AR CCB 

E KATHE 

WATERVLIET NY 12189-4050 

1 DIRECTOR 

US ARMY AMCOM 

SFAE AV RAM TV 

D CALDWELL 

BLDG 5300 

REDSTONE ARSENAL AL 

35898 

1 NAVAL SURFACE WARFARE CTR 

DAHLGREN DIV CODE GO6 

DAHLGREN VA 22448 

1 US ARMY COLD REGIONS 

RSCH & ENGRNG LAB 

I’ DUTTA 

72 LYME RD 

HANOVER NH 03755 

1 USA SBCCOM PM SOLDIER SPT 

AMSSB PM RSS A 

J CONNORS 

KANSAS ST 

NATICK MA 01760-5057 

2 OFC OF NAVAL RESEARCH 

D SIEGEL CODE 351 

J KELLY 

800 N QUINCY ST 

ARLINGTON VA 22217-5660 

NO. OF 

COPIES ORGANIZATION 

1 NAVAL SURFACE WARFARE CTR 

TECH LIBRARY CODE 323 

17320 DAHLGREN RD 

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1 NAVAL SURFACE WARFARE CTR 

CRANE DIVISION 

M JOHNSON CODE 2OH4 

LOUISVILLE KY 402145245 

2 NAVAL SURFACE WARFARE CTR 

U SORATHIA 

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17320 DAHLGREN RD 

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DIV N85 

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2000 NAVY PENTAGON 

WASHINGTON DC 20350-2000 

8 NAVAL SURFACE WARFARE CTR 

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R D COOPER CODE G32 

J FRAYSSE CODE G33 

E ROWE CODE G33 

T DURAN CODE G33 

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DAHLGREN VA 22448 

44 
NO. OF 

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2 NAVAL SURFACE WARFARE CTR 

CARDEROCK DIVISION 

R CRANE CODE 2802 

C WILLIAMS CODE 6553 

3A LEGGETT CIR 

BETHESDA MD 20054-5000 

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2941 P ST RM 136 

WRIGHT PATTERSON AFB OH 

45433-7750 

1 AFRL MLSS 

R THOMSON 

2179 12TH ST RM 122 

WRIGHT PATTERSON AFB OH 

45433-7718 

2 AFRL 

F ABRAMS 

J BROWN 

BLDG 653 

2977 P ST STE 6 

WRIGHT PATTERSON AFB OH 

45433-7739 

1 WATERWAYS EXPERIMENT 

D SCOTT 

3909 HALLS FERRY RD SC C 

VICKSBURG MS 39180 

1 OSD 

JOINT CCD TEST FORCE 

OSD JCCD 

R WILLIAMS 

3909 HALLS FERRY RD 

VICKSBURG MS 29180-6199 

3 NASA LANGLEY RSCH CTR 

AMSRL VS 

W ELBER MS 266 

F BARTLETT JR MS 266 

G FARLEY MS 266 

HAMPTON VA 23681-0001 

1 DIRECTOR 

DEFENSE INTLLGNC AGNCY 

TA5 

K CRELLING 

WASHINGTON DC 20310 

NO. OF 

COPIES ORGANIZATION 

1 NATIONAL COMPOSITE CENTER 

T CORDELL 

2000 COMPOSITE DR 

KETTERING OH 45420 

1 OFC DEPUTY UNDER SEC DEFNS 

J THOMPSON 

CRYSTAL SQ 4 STE 501 

1745 JEFFERSON DAVIS HWY 

ARLINGTON VA 22202 

5 UNJV OF DELAWARE 

Cl-R FOR COMPOSITE MTRLS 

J GILLESPIE 

M SANTARE 

S YARLAGADDA 

S ADVANI 

D HEIDER 

201 SPENCER LABORATORY 

NEWARK DE 19716 

2 DIRECTOR 

USARL 

AMSRL WM MB 

M BERMAN 

A FRYDMAN 

2800 POWDER MILL RD 

ADELPHI MD 20783-1197 

ABERDEEN PROVING GROUND 

53 DIR USARL 

AMSRL CI 

AMSRL CI S 

A MARK 

AMSRL CS IO FI 

M ADAMSON 

AMSRL SL BA 

AMSRL SL BL 

D BELY 

R HENRY 

AMSRL SL BG 

AMSRL SL I 

AMSRL WM 

J SMITH 

D VIECHNICKI 

G HAGNAUER 

J MCCAULEY 

AMSRL WM B 

A HORST 

45 
NO. OF 

COPIES ORGANIZATION 

AMSRL WM BA 

D LYON 

AMSRL WM BC 

I’ PLOSTINS 

J NEWILL 

S WILKERSON 

AMSRL WM BF 

J LACETERA 

AMSRL WM BR 

AMSRL WM EG 

E SCHMIDT 

AMSRL WM MA 

L GHIORSE 

S MCKNIGHT 

AMSRL WM MB 

B FINK 

J BENDER 

T BOGETTI 

L BURTON 

K BOYD 

B CHEESEMAN 

R DOOLEY 

W DRYSDALE 

G GAZONAS 

D GRANVILLE 

D HOPKINS 

C HOPPEL 

R KASTE (4 CPS) 

D LI 

R LIEB 

B POWERS 

D SPAGNUOLO 

AMSRL WM T 

B BURNS 

M ZOLTOSKI 

AMSRL WM TA 

W GILLICH 

T HAVEL 

J RUNYEON 

M BURKINS 

E HORWATH 

B GOOCH 

W BRUCHEY 

M NORMANDIA 

AMSRL WM TC 

R COATES 

t 

. 

46 
REPORT DOCUMENTATION PAGE Form Approved 

OMB No. 0704-0188 

Pubk repormg burden for ths cokctm 01 mfomatlon IS ertmated 1.3 average 1 hour per response, mcludmg me wne for mwcwing instructions, searclung existing dsta source*, 

gathering and mainbdnlng the data needed, and mmplethg and mvimlng the collection of information. Send mmmmk regarding this burden estimate or any other aspect 01 this 

collection of information, includhg nuggestlons for reducing this burden. to WashIngton Headquarters Services, Directorals for lnbmmtion Operations and Reports. 1215 Jefierson 

Davis Highwsy suite (2~ Adinqton, VA 222~~-4302. and to the Office of MSWSCWMM and BUdqet PSPCWO~* Reduction PmiKU07M9188). Wa~hinqton. DC 205%. 

1. AGENCY USE ONLY (Leave blank) 2. REPORT DATE 3. REPORT TYPE AND DATES COVERED 

March 2002 Final, January 1999-December 1999 

4. TITLE AND SUBTITLE 5. FUNDING NUMBERS 

A User’s Guide to LAMI’AT and ANSYS 622618AH80 

6. AUTHOR(S) 

Robert P. Kaste 

7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS 

U.S. Army Research Laboratory 

ATTN: AMSRL-WM-MB 

Aberdeen Proving Ground, MD 21005-5069 

8. PERFORMING ORGANIZATION 

REPORT NUMBER 

ARL-TR-269 1 

9. SPONSORING/MONlTORING AGENCY NAMES(S) AND ADDRESS 10.SPONSORING’MONITORlNG 

AGENCY REPORT NUMBER 

11. SUPPLEMENTARY NOTES 

12a. DISTRIBUTION/AVAILABlLlTY STATEMENT 

Approved for public release; distribution is unlimited. 

12b. DISTRIBUTION CODE 

13. ABSTRACT(Maximum 200 words) 

LAMPAT and ANSYS are analysis tools that can be used together to evaluate the mechanical integrity of structure! 

of laminar construction. The two codes originate from two different areas of analysis. Their default coordinate system: 

have different orientations. To properly examine a structure, the directional properties used by LAMPAT must be 

transformed into the proper input coordinate directional properties for ANSYS. This has been done for some time 

already, but as the structures being analyzed become more complex, this coordinate system transformation has become a 

tool requiring some additional thought. This report describes using of cylindrical and Cartesian coordinate system 

srientations and local element coordinate system results within ANSYS to facilitate the analysis of laminate structures 

with ply layers parallel to curvilinear profiles. 

14. SUBJECT TERMS 

ANSYS, LAMPAT, orthotropic materials, structural finite element analysis 

15. NUMBER OF PAGES 

43 

16. PRICE CODE 

17. SECURITY CLASSIFICATION 18. SECURITY CLASSIFICATION 19. SECURITY CLASSIFICATION 20. LIMITATION OF ABSTRACT 

OF REPORT OF THIS PAGE OF ABSTRACT 

UNCLASSIFIED UNCLASSIFIED UNCLASSIFIED UL 

s.,-.m rr.Tn c+lnrlrrrA Enrm cm!? ,Ff‘a\, -Lea, -La”-33”” 47 Y.“ll”Yl” I “I.ll L”” \’ a.,.. - .a-, 

Prescribed by ANSI Std. 239-l 8 298-l 02