This is "QUICK USER's MANUAL" for LAMINA.exe

 

 

      green ==> info printed out by program

 

      red ==> input required by program ?

 

 

start here

 

>> LAMINA <CR>        !after downloading LAMINA.exe

 

   SOLVE FOR UW/W/U, GIVE 0/1/2 ?

 

>> 0 <CR>               ! SOLVING FOR U AND W

 

 

   GIVE NUMBER OF LAMINA = ?

    MAX IS 5

 

>> 1 <CR>               ! ONLY 1 LAYER IN LAMINA                       

 

      DIFFERENT MATERIALS TO BE USED IN LAMINA ARE'',/,

        SI=1, SIO2=2, SI3N4=3, POLYSI=4, Al=5'',/,

        P+SUBS=7, FUSEDSILICA=8, QUARTZ=9, SAPPHIRE=10'',/,

        TUNGSTEN=11,

 

   GIVE  LAMID()`S FOR 1 LAYERS 

 

    LAM( 1)=?

 

>> 1 <CR>               ! SELECT SILICON AS MATERIAL OF LAYER 1

 

      LAMINA( 1)= 1 ( DI-SILICON )      ! DIAPHRAGM OF SILICON

 

   GIVE THE PLATE SIZE, IN CM ?

 

>> 100E-4 <CR>              ! 100 MICRONS

 

      SI=1, SIO2=2, SI3N4=3, POLY=4, Al=5

      6 UM, 0.4 UM, 0.13 UM,  4 UM , 1 UM

      N+SUB, P+SUB, SILICA,  QUARTZ, SAPPHIRE

      200UM, 200UM,  200UM,   200UM,   200UM

      TUNGSTEN,

        1UM   , 

 

   NEW/DEFAULT    LAMINA  THICKNESSES, 1/0 ?

 

>> 0 <CR>

 

      PRINTS VALUES OF EX, EY ETC. FOR SILICON

 

   ISOTROPIC ? , NO/YES =>   ISO = 0/1 ?

 

>> 1 <CR>               ! ISOTROPIC ==> not a SINGLE CRYSTAL

                        ! easy to compare standard results

 

   GIVE TRANSVERSE LOAD MULT = ?

 

>> 1 <CR>               ! NORMALISED UNIT LOAD

 

   GIVE MESH NUMBER NX , NY = ?  max 20, 20 ?

 

>> 15,15 <CR>              ! 15 MESH POINTS IN X- AND Y-DIRECTION

                        ! FOR A FULL PLATE IT IMPLIES 30 X 30 POINTS

 

   DO YOU WISH TO GIVE IN-PLANE FORCES XN, YN AND XYN

    OR RETAIN STRESS-RESULTANTS   1/0  ?

  

>> 0 <CR>               ! NO EXTERNALLY APPLIED IN-PLANE FORCES

                        ! RETAIN INTERNAL STRESS-RESULTANTS

 

   DO YOU WISH TO GIVE new MOMENTS `NEWMMT`,

    OR RETAIN THOSE developed BY LAMINA   1/0  ?

 

>> 0 <CR>               ! NO EXTERNALLY APPLIED MOMENTS

                        ! MOMENTS developed BY LAMINA RETAINED

 

   X-EDGES FIXED/SUPPORTED/FREE, GIVE 1/2/3  ?

 

>> 1 <CR>               ! X-EDGES FIXED

 

   Y-EDGES FIXED/SUPPORTED/FREE, GIVE 1/2/3  ?

 

>> 1 <CR>               ! Y-EDGES FIXED

 

 

      DISPLAYS SEVERAL INTERMEDIATE RESULTS (WHILE FORMING THE Z-MATRIX)

        ALSO TYPES ON SCREEN the following message several times

        Solving ! Please Wait

 

      then

     

      displays the results

 

     First entry in last row gives the deflection at centre.

 

     -0.1260E-02        ! -ve sign shows deflection downward  

 

 

 

 

   Fortran Pause - Enter command<CR> or <CR> to continue  ?

 

 

>> <CR>                       ! THIS ENDS THE SIMULATION RUN

 

 

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      IT CREATES FOLLOWING FILES

 

 

      FOR007.DAT        ! INTERMEDIATE debug DATA FILE

 

 

      FOR012.DAT        ! THE LAMINA STRUCTURE DETAILS

 

      FOR023.DAT       ! THE RESULTS

 

                        ! U-VALUES (MAXM 10 VALUES PER LINE)

                        ! 1ST VALUE IN LAST LINE IS THE CENTRE VALUE

 

                        ! ONE LINE BLANK SPACING

 

                        ! W-VALUES (MAXM 10 VALUES PER LINE)

                        ! 1ST VALUE IN LAST LINE IS THE CENTRE VALUE

 

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      THE STRESSES ARE YET TO BE IMPLEMENTED

 

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Apte  26-Dec-2000