*HEADING
 NAFEMS R0031/3, three-layer sandwich shell under normal pressure loading [SC6R]
*NODE
   1, 0., 0., -0.403
   9, 5., 0., -0.403
  81, 0., 5., -0.403
  89, 5., 5., -0.403
1001, 0., 0., 0.403
1009, 5., 0., 0.403
1081, 0., 5., 0.403
1089, 5., 5., 0.403
*NGEN
   1,   9,1
1001,1009,1
*NSET,NSET=BOT1,GEN,UNSORT
  1,9,1
*NSET,NSET=BOT2,GEN,UNSORT
1001,1009,1
*NSET,NSET=BOT,UNSORT
BOT1,BOT2
*NGEN
  81,  89,1
1081,1089,1
*NSET,NSET=TOP,GEN,UNSORT
  81,89,1
1081,1089,1
*NSET,NSET=LEFT1,GEN,UNSORT
   1,  81,10
*NSET,NSET=LEFT2,GEN,UNSORT
1001,1081,10
*NSET,NSET=LEFT,UNSORT
LEFT1,LEFT2
*NSET,NSET=ZBC,GEN
   1,  81,10
1001,1081,10
*NSET,NSET=ZBC
BOT1
BOT2
*NSET,NSET=RIGHT,GEN,UNSORT
   9,  89,10
1009,1089,10
*NFILL,NSET=NALL
BOT,TOP,8,10
*ELEMENT,TYPE=SC6R,ELSET=ELALL
1,1,2,11,1001,1002,1011
2,2,12,11,1002,1012,1011
*ELGEN,ELSET=ELALL
1,8,1,2,8,10,16
2,8,1,2,8,10,16
*ELSET,ELSET=OUTPUT
 128,
 127,
1128,
1127, 
*NSET,NSET=NOUT
89,
1089, 
*SHELL SECTION,ELSET=ELALL,COMPOSITE,THICKNESS MODULUS=1E8,POISSON=0.0
.028,3,FACE
.75,3,CORE
.028,3,FACE
*MATERIAL,NAME=FACE
*ELASTIC,TYPE=ENGINEERING CONSTANTS
 10.E6,4.E6,4.E6,.3,.3,.3,1.875E6,1.875E6,
 1.875E6,
*MATERIAL,NAME=CORE
*ELASTIC,TYPE=ENGINEERING CONSTANTS
 10.,10.,10.,0.,0.,0.,10.,3.E4,
 1.2E4,
*EQUATION
2
 BOT1,2,1.0, BOT2,2,1.0
2
LEFT1,1,1.0,LEFT2,1,1.0
*BOUNDARY
TOP,2
RIGHT,1
BOT,1
LEFT,2
 ZBC,3
**
*STEP
*STATIC
*DLOAD
ELALL,P1,100
*OUTPUT, FIELD
*ELEMENT OUTPUT
 1,2,3,4,5,6,7,8,9
 S,
*OUTPUT, FIELD
*ELEMENT OUTPUT, POSITION=NODES
 1,2,3,4,5,6,7,8,9
 S,
*NODE OUTPUT
 U,
*EL FILE,ELSET=OUTPUT,POSITION=AVERAGED AT NODES
 1,2,3,4,5,6,7,8,9
 S, 
*END STEP