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  1.      ----------------------------------------------------------------------
  2.          SecPro  - Version F22    Section Properties of Composite Laminates
  3.      ----------------------------------------------------------------------
  4.  
  5.      Laminate filename: KOV005.PRP           BASE: User Defined @ 1.20E+06
  6.  
  7.                                  <<  Laminate Summary  >>
  8.  
  9.         05-12-1987 / A meaningful laminate description of 64 characters
  10.         Groups=  7
  11.         Plies=   7
  12.         Tot.t=   .859
  13.  
  14.      PlyType     ID         t      TE0      TE90      CE0      CE90    Angle
  15.      ========================================================================
  16.      P    MAT_1.5         0.051  8.8E+05   8.8E+05  1.1E+06   1.1E+06    0
  17.      P    CDB-200         0.032  2.5E+06   1.5E+05  2.9E+06   1.7E+06    0
  18.      P    MAT_1.0         0.034  8.8E+05   8.8E+05  1.1E+06   1.1E+06    0
  19.      C    AIREX  R.65     0.625  1.2E+04   1.2E+04  1.2E+04   1.2E+04    0
  20.      P    MAT_1.0         0.034  8.8E+05   8.8E+05  1.1E+06   1.1E+06    0
  21.      P    CDB-200         0.032  2.5E+06   1.5E+05  2.9E+06   1.7E+06    0
  22.      P    MAT_1.5         0.051  8.8E+05   8.8E+05  1.1E+06   1.1E+06    0
  23.  
  24.         Properties listed above have been rounded. See .PRP file for actuals
  25.  
  26.                              << Ply-By-Ply Results >>
  27.  
  28.             Total Laminate t: 0.859    Total Ply Groups:   7
  29.             Width of Section: 1.0E+00
  30.             Core Contribution: Neglected
  31.  
  32.        PLY#    ID          t            A'    Ext->NA       I        Z
  33.        ==================================================================
  34.         1 MAT_1.5         0.051       0.03719  0.42950  0.00608   0.11200
  35.         2 CDB-200         0.032       0.06667  0.37850  0.00877   0.04448
  36.         3 MAT_1.0         0.034       0.02479  0.34650  0.00269   0.13883
  37.         4 AIREX R.65      0.625       0.00227  0.31250  0.00007   0.11237
  38.         5 MAT_1.0         0.034       0.02479  0.34650  0.00269   0.13883
  39.         6 CDB-200         0.032       0.06667  0.37850  0.00877   0.04448
  40.         7 MAT_1.5         0.051       0.03719  0.42950  0.00608   0.11200
  41.  
  42.                              << Overall Laminate Summary >>
  43.  
  44.                 Neutral Axis Location:   0.42950000
  45.            Laminate Moment of Inertia:   0.03507557
  46.              Laminate Section Modulus:   0.08166606
  47.                  Total EI of laminate:   5.92E+04
  48.         Laminate (Rule of Mixtures) E:   3.59E+05
  49.  
  50.         Notes: A' is the transformed sectional area.
  51.                Ext->NA is distance from extreme fiber to the NA of laminate.
  52.                I is moment of inertia of ply - Z is section modulus of ply
  53.                NA is given in units above bottom of ply #7
  54.  
  55.    
  56.  
  57.  
  58.                                A LAMCON .PRP FILE
  59.  
  60.  
  61.  
  62.         05-12-1987 / Laminate Description up to 64 characters
  63.         Groups=  7
  64.         Plies=   7
  65.         Tot.t=   .859
  66.         Prop=   PSI
  67.         Dist=   IN
  68.         Dens=   LBFT3
  69.         P MAT_1.5                              0.051    0.00
  70.            11.00000E+03   11.00000E+03   87.50000E+04   87.50000E+04
  71.            21.00000E+03   21.00000E+03   11.00000E+05   11.00000E+05
  72.            11.00000E+03   10.00000E+05
  73.            .10000   .00000E+00
  74.         P CDB-200                              0.032    0.00
  75.            28.00000E+03   21.00000E+03   25.00000E+05   15.00000E+04
  76.            33.00000E+03   21.00000E+03   29.00000E+05   17.00000E+05
  77.            12.00000E+03   25.00000E+04
  78.            .22000   .00000E+00
  79.         P MAT_1.0                              0.034    0.00
  80.            11.00000E+03   11.00000E+03   87.50000E+04   87.50000E+04
  81.            21.00000E+03   21.00000E+03   11.00000E+05   11.00000E+05
  82.            11.00000E+03   10.00000E+05
  83.            .10000   .00000E+00
  84.         C       AIREX R.65                      0.625   000.000
  85.            26.0000E+01   26.0000E+01   11.6000E+03   11.6000E+03
  86.            17.0000E+01   17.0000E+01   11.6000E+03   11.6000E+03
  87.            12.8000E+01   43.5000E+02
  88.              .2500     5.00
  89.         P MAT_1.0                              0.034    0.00
  90.            11.00000E+03   11.00000E+03   87.50000E+04   87.50000E+04
  91.            21.00000E+03   21.00000E+03   11.00000E+05   11.00000E+05
  92.            11.00000E+03   10.00000E+05
  93.            .10000   .00000E+00
  94.         P CDB-200                              0.032    0.00
  95.            28.00000E+03   21.00000E+03   25.00000E+05   15.00000E+04
  96.            33.00000E+03   21.00000E+03   29.00000E+05   17.00000E+05
  97.            12.00000E+03   25.00000E+04
  98.            .22000   .00000E+00
  99.         P MAT_1.5                              0.051    0.00
  100.            11.00000E+03   11.00000E+03   87.50000E+04   87.50000E+04
  101.            21.00000E+03   21.00000E+03   11.00000E+05   11.00000E+05
  102.            11.00000E+03   10.00000E+05
  103.            .10000   .00000E+00
  104.       
  105.  
  106.  
  107.                                A LAMCON .LCF FILE
  108.  
  109.  
  110.         05-19-1987
  111.         Groups,       8
  112.         Plies,        8
  113.         Thickness,    .4285 IN
  114.         Mon.Sys,     US Dollars
  115.         Fab. Base,   LB
  116.         Fab. Wgt,    OZSQYD
  117.         Core Base,   TH/SQFT
  118.         Core Dens,   LBFT3
  119.         P   ,   BTI-1800
  120.               0.025,     0.00,    50.00,      1.02,     18.00,     1.0
  121.         P   ,   BTI-1808
  122.               0.048,     0.00,    50.00,      1.07,     18.00,     1.0
  123.         P   ,   BTI-1810
  124.               0.057,     0.00,    50.00,      1.12,     18.00,     1.0
  125.         P   ,   BTI-1815
  126.               0.068,     0.00,    50.00,      1.18,     18.00,     1.0
  127.         P   ,   BTI-2400
  128.               0.032,     0.00,    50.00,      1.25,     24.00,     1.0
  129.         P   ,   BTI-2408
  130.               0.055,     0.00,    50.00,      1.45,     24.00,     1.0
  131.         P   ,   BTI-2410
  132.               0.067,     0.00,    50.00,      1.67,     24.00,     1.0
  133.         P   ,   BTI-2415
  134.               0.077,     0.00,    50.00,      1.78,     24.00,     1.0
  135.         
  136.  
  137.  
  138.        **********************************************
  139.         COPAN/II  PBS  - Bending and Buckling Solutions
  140.        **********************************************
  141.  
  142.         JOB : KOV005.PRP                         7/21   18:11
  143.  
  144.         Units:   PSI   IN
  145.         Total laminate thickness: 0.859
  146.         Plate XY dimensions:      36.000     36.000
  147.         Laminate Orientation to the 1st Side:    0
  148.         Boundary Conditions: Simply Supported
  149.         Distributed Pressure:      3.000
  150.  
  151.           <<  Equivalent Material for Pure Bending  >>
  152.  
  153.         A plate made of the following material and     
  154.         having the same thickness as the above laminate
  155.         will produce bending results identical to the  
  156.         original laminate.
  157.  
  158.         Cxx =8.26E+05  Cxy =4.70E+04  Cxs =0.00E+00
  159.         Cxy =4.70E+04  Cyy =4.32E+05  Cys =0.00E+00
  160.         Cxs =0.00E+00  Cys =0.00E+00  Gxy =4.97E+05
  161.  
  162.  
  163.         <<  Integrated Bending Stiffness  >>
  164.  
  165.         This is the matrix of which the first term
  166.         is for isotropic materials :
  167.            E x H^3  / ( 12 x (1-NU^2)) 
  168.  
  169.         4.36E+04  2.48E+03  0.00E+00  
  170.         2.48E+03  2.28E+04  0.00E+00  
  171.         0.00E+00  0.00E+00  2.63E+04  
  172.  
  173.         Maximum Deflection:   6.309E-01
  174.  
  175.            In-Plane Stress     Shear thru
  176.           Short        Long      Thick.    Group   Type     Thick.    Angle 
  177.        ----------------------------------  ---------------------------------
  178.        -1.802E+03  -2.129E+03  1.9838E+03     1 MAT_1.5_   5.10E-02    0
  179.        -4.719E+03  -3.346E+02  4.3706E+02     2 CDB-200_   3.20E-02    0
  180.        -1.453E+03  -1.718E+03  1.6004E+03     3 MAT_1.0_   3.40E-02    0
  181.         -1.835E+01  -2.169E+01  6.2788E+00     4  AIREX     6.25E-01    0
  182.        1.4534E+03  1.7176E+03  -1.600E+03     5 MAT_1.0_   3.40E-02    0
  183.        4.7192E+03  3.3463E+02  -4.371E+02     6 CDB-200_   3.20E-02    0
  184.        1.8016E+03  2.1291E+03  -1.984E+03     7 MAT_1.5_   5.10E-02    0
  185. 
  186.  
  187.                           Four Records of a Ply .MAT File
  188.  
  189.         KEVLAR ROVING
  190.        N/A
  191.         50
  192.         61000, 57000, 4500000, 4200000
  193.         35000, 37000, 2700000, 2500000
  194.         8000, 800000
  195.         .28, 0
  196.         .042
  197.         4.50
  198.         24
  199.        NULL
  200.        NULL
  201.        * EOR *
  202.         CHOPPED MAT
  203.        N/A
  204.         70
  205.         13000, 13000, 1000000, 1000000
  206.         14000, 14000, 1000000, 1000000
  207.         3000, 5000
  208.         .28, 0
  209.         .03
  210.         .89
  211.         12
  212.        NULL
  213.        NULL
  214.        * EOR *
  215.         XYZ-400
  216.        ACME PLY COMPANY
  217.         55
  218.         3000, 30000, 3000000, 3000000
  219.         30000, 30000, 300, 30
  220.         300, 30000
  221.         .29, 0
  222.         .234
  223.         1.334
  224.         24
  225.        NULL
  226.        NULL
  227.        * EOR *
  228.         ALUMINUM
  229.        T-1100
  230.         05
  231.         20000, 20000, 40000000, 1000000
  232.         20000, 20000, 40000000, 1000000
  233.         3000, 600000
  234.         .25, 0
  235.         .09
  236.         0
  237.         0
  238.        NULL
  239.        NULL
  240.        * EOR *
  241.  
  242.               See pg. 28 for definitions of the above data lines.
  243.       
  244. .R:C
  245.  
  246.  
  247.       ----------------------------------------------------------------------------------------
  248.                    HATMAN  - Sectional Property Report For Stiffened Composite Panels
  249.       ----------------------------------------------------------------------------------------
  250.       HAT FILE: DEMO.HAT                                           REPORT REF: DEMO.REP
  251.  
  252.       PRP files --> ONE, TWO, THREE, FOUR, THREE, TWO           Transformation Base E: 1.2E+06
  253.  
  254.                                       (A)       (y)      (A')      (A'*y)      (A'y^2)   (bd^3/12)
  255.       Component ID     t     b        Area     Dist.     Area'     Moment          Iy           Ig
  256.       =============================================================================================
  257.       [A] Base Plate: ONE.PRP   t=0.116
  258.       S-500          0.016 24.000     0.384    0.008     1.760     0.0141     0.00011    0.0000082
  259.       G-900          0.024 24.000     0.576    0.076     5.760     0.4378     0.03327    0.0000276
  260.       S-500          0.016 24.000     0.384    0.108     1.760     0.1901     0.02053    0.0000082
  261.       [B] Left Flange: TWO.PRP   t=0.116
  262.       S-500          0.016  4.000     0.064    0.124     0.293     0.0364     0.00451    0.0000014
  263.       G-900          0.024  4.000     0.096    0.192     0.960     0.1843     0.03539    0.0000046
  264.       S-500          0.016  4.000     0.064    0.224     0.293     0.0657     0.01472    0.0000014
  265.       [C] Left Web: THREE.PRP   t=0.116
  266.       S-500          5.000  0.016     0.080    2.732     0.367     1.0017     2.73674    0.1666667
  267.       G-900          5.000  0.024     0.120    2.732     1.200     3.2784     8.95659    0.2500000
  268.       G-450          5.000  0.012     0.060    2.732     0.600     1.6392     4.47829    0.1250000
  269.       S-500          5.000  0.016     0.080    2.732     0.367     1.0017     2.73674    0.1666667
  270.       [D] Top Hat: FOUR.PRP   t=0.120
  271.       G-450          0.012  4.000     0.048    5.238     0.480     2.5142    13.16959    0.0000006
  272.       G-450          0.012  4.000     0.048    5.346     0.480     2.5661    13.71826    0.0000006
  273.       [E] Right Web: THREE.PRP   t=0.116
  274.       S-500          5.000  0.016     0.080    2.732     0.367     1.0017     2.73674    0.1666667
  275.       KS-400         5.000  0.012     0.060    2.732     0.265     0.7240     1.97791    0.1250000
  276.       G-900          5.000  0.024     0.120    2.732     1.200     3.2784     8.95659    0.2500000
  277.       G-450          5.000  0.012     0.060    2.732     0.600     1.6392     4.47829    0.1250000
  278.       [F] Right Flange: TWO.PRP   t=0.116
  279.       S-500          0.016  4.000     0.064    0.124     0.293     0.0364     0.00451    0.0000014
  280.       G-900          0.024  4.000     0.096    0.140     0.960     0.1344     0.01882    0.0000046
  281.       KS-400         0.012  4.000     0.048    0.158     0.212     0.0335     0.00529    0.0000006
  282.       S-500          0.016  4.000     0.064    0.208     0.293     0.0610     0.01269    0.0000014
  283.  
  284.                                 [D]                       
  285.                               ========                    
  286.                              ==      ==                   
  287.                             ==        ==                  
  288.                        [C] ==          == [E]             
  289.                           ==            ==                
  290.                          ==              ==               
  291.                 [B] ======                ====== [F]       
  292.             --------------------------------------------  
  293.                                 [A]                       
  294.             --------------------------------------------  
  295.          
  296.  
  297.  
  298.       ----------------------------------------------------------------------------------------
  299.                    HATMAN  - Sectional Property Report For Stiffened Composite Panels
  300.       ----------------------------------------------------------------------------------------
  301.       HAT FILE: DEMO.HAT                                           REPORT REF: DEMO.REP
  302.  
  303.       PRP files --> ONE, TWO, THREE, FOUR, THREE, TWO           Transformation Base E: 1.2E+06
  304.  
  305.                                                                  
  306.       Component ID     Angle     x      y       E      Trans.    
  307.       ============================================================
  308.       [A] Base Plate: ONE.PRP
  309.       S-500            0      24.000  0.016   5.5E+06    4.583
  310.       G-450            0      24.000  0.012   1.2E+07   10.000
  311.       G-900            0      24.000  0.024   1.2E+07   10.000
  312.       KS-400           0      24.000  0.012   5.3E+06    4.417
  313.       G-900            0      24.000  0.024   1.2E+07   10.000
  314.       G-450            0      24.000  0.012   1.2E+07   10.000
  315.       S-500            0      24.000  0.016   5.5E+06    4.583
  316.       [B] Left Flange: TWO.PRP
  317.       S-500            0       4.000  0.016   5.5E+06    4.583
  318.       G-450            0       4.000  0.012   1.2E+07   10.000
  319.       G-900            0       4.000  0.024   1.2E+07   10.000
  320.       KS-400           0       4.000  0.012   5.3E+06    4.417
  321.       G-900            0       4.000  0.024   1.2E+07   10.000
  322.       G-450            0       4.000  0.012   1.2E+07   10.000
  323.       S-500            0       4.000  0.016   5.5E+06    4.583
  324.       [C] Left Web: THREE.PRP
  325.       S-500           45       5.000  0.016   5.5E+06    4.583
  326.       G-450           50       5.000  0.012   1.2E+07   10.000
  327.       G-900           60       5.000  0.024   1.2E+07   10.000
  328.       KS-400          70       5.000  0.012   5.3E+06    4.417
  329.       G-900           80       5.000  0.024   1.2E+07   10.000
  330.       G-450           90       5.000  0.012   1.2E+07   10.000
  331.       S-500            0       5.000  0.016   5.5E+06    4.583
  332.       [D] Top Hat: FOUR.PRP
  333.       G-450           10       4.000  0.012   1.2E+07   10.000
  334.       G-450           60       4.000  0.012   1.2E+07   10.000
  335.       G-450          -60       4.000  0.012   1.2E+07   10.000
  336.       G-450            0       4.000  0.012   1.2E+07   10.000
  337.       [E] Right Web: THREE.PRP
  338.       S-500           45       5.000  0.016   5.5E+06    4.583
  339.       G-450           50       5.000  0.012   1.2E+07   10.000
  340.       G-900           60       5.000  0.024   1.2E+07   10.000
  341.       KS-400          70       5.000  0.012   5.3E+06    4.417
  342.       G-900           80       5.000  0.024   1.2E+07   10.000
  343.       G-450           90       5.000  0.012   1.2E+07   10.000
  344.       S-500            0       5.000  0.016   5.5E+06    4.583
  345.       [F] Right Flange: TWO.PRP
  346.       S-500            0       4.000  0.016   5.5E+06    4.583
  347.       G-450            0       4.000  0.012   1.2E+07   10.000
  348.       G-900            0       4.000  0.024   1.2E+07   10.000
  349.       KS-400           0       4.000  0.012   5.3E+06    4.417
  350.       G-900            0       4.000  0.024   1.2E+07   10.000
  351.       G-450            0       4.000  0.012   1.2E+07   10.000
  352.       S-500            0       4.000  0.016   5.5E+06    4.583
  353. 
  354.  
  355.  
  356.       ----------------------------------------------------------------------------------------
  357.                   HATMAN - Sectional Property Report For Stiffened Composite Panels
  358.       ----------------------------------------------------------------------------------------
  359.       HAT FILE: DEMO.HAT                                           REPORT REF: DEMO.REP
  360.  
  361.       PRP files --> ONE, TWO, THREE, FOUR, THREE, TWO           Transformation Base E: 1.2E+06
  362.  
  363.                         H A T    S E C T I O N    S U M M A R Y                        
  364.       =================================================================================
  365.  
  366.           Cross-Sectional Area:     43.4
  367.           SUMMATIONS
  368.                  Ply Moments  :     53.0
  369.                           Iy  :    203.4
  370.                           Ig  :      2.4
  371.  
  372.           Moment of Inertia about N/A :  141.030
  373.                Distance from NA to XX :    1.221
  374.           Distance from NA to Extreme :    4.131
  375.                 Total Section Modulus :   34.141
  376.  
  377.  
  378.                                                              
  379.                                  ========                    
  380.                                 ==      ==                   
  381.                                ==        ==                  
  382.                               ==          ==                 
  383.     NA  ---- - ---- - ---- - ==-- - ---- - == ---- - ----    
  384.                             ==              ==               
  385.                        ======                ======           
  386.                 --------------------------------------------  
  387.                                                            
  388.        X - - -  -------------------------------------------- - - -  X
  389.           Extreme fiber may be top or bottom of section dependent upon
  390.           the location of the neutral axis.
  391.  
  392.