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Problem name: c:\users\emaloc~1\appdata\local\temp\Ass
Date        : 04/05/2023     Time:   13:23:01


 SYSTEM OF UNITS:
 International System of Units, SI, is used for all input/output data.
 Common Quantities:
 Length:meter, Mass:kilogram, Time:second, Temperature:kelvin
 Force:newton, Pressure also stress:pascal, Energy:joule, Power:watt

 NUMBER OF PHYSICAL CORES USED TO RUN SIMULATION:  6

  C O N T R O L  I N F O R M A T I O N                  

   CURRENT RESTRAINT SET . . . . . . . . . . . (BC_SET)  =           1

   NUMBER OF LOAD CASES  . . . . . . . . . . . (NLCASE)  =           1
   SOLUTION MODE . . . . . . . . . . . . . . . (MODEX)   =           0
      EQ. 0, STATIC ANALYSIS                              
      EQ. 1, BUCKLING ANALYSIS                            
      EQ. 2, DYNAMIC ANALYSIS                             
      EQ. 3, DROP TEST                                    

   SOLVER TYPE . . . . . . . . . . . . . . . . .(ISOL)   =           2
      EQ. 0, DIRECT SPARSE SOLVER                         
      EQ. 1, DIRECT SKYLINE SOLVER                        
      EQ. 2, ITERATIVE SOLVER                             
      EQ. 3, EXPLICIT INTEGRATION                         
      EQ. 4, LARGE PROBLEM DIRECT SPARSE SOLVER           
      EQ. 5, INTEL DIRECT SPARSE SOLVER                   
      EQ. 6, INTEL NETWORK SPARSE SOLVER                  

   ITERATIVE SOLUTION MODE . . . . . . . . . . (IMODE)   =           1
      EQ. 1, GENERAL                                      
      EQ. 2, MEMORY SAVER (FOR TETRA10)                   
      EQ. 3, ULTRA-MEMORY SAVER (FOR TETRA10)             

   SOLVER CONVERGENCE TOLERANCE  . . . . . . . (CONVR)   =   0.100E-03

   THERMAL LOADING FLAG . . . . . . . . . . . .(ITHERM)  =           0
      EQ. 0, NO THERMAL EFFECTS CONSIDERED                
      EQ. 1, ADD TEMPERATURE EFFECT                       
   GRAVITY LOADING FLAG . . . . . . . . . . . .(IGRAV)   =           0
      EQ. 0, NO GRAVITY LOADING CONSIDERED                
      EQ. 1, ADD GRAVITY LOADING EFFECT                   
   CENTRIFUGAL LOADING FLAG . . . . . . . . . .(ICNTRF)  =           0
      EQ. 0, NO CENTRIFUGAL LOADING CONSIDERED            
      EQ. 1, ADD CENTRIFUGAL LOADING EFFECT               
   IN-PLANE STIFFENING FLAG . . . . . . . . . .(INPLN)   =           0
      EQ. 0, NO IN-PLANE EFFECTS CONSIDERED               
      EQ. 1, IN-PLANE EFFECTS CONSIDERED                  
   SOFT SPRING ADDITION FLAG . . . . . . . . . (ISOFT)   =           0
      EQ. 0, NO SOFT SPRING OPTION                        
      EQ. 1, SOFT SPRING ADDED                            

   SAVE DECOMPOSED STIFFNESS MATRIX FLAG . . . (ISAVK)   =           0
      EQ. 0, DO NOT SAVE DECOMPOSED K                     
      EQ. 1, SAVE DECOMPOSED K                            
   FORM STIFFNESS MATRIX FLAG . . . . . . . . .(IFORMK)  =           0
      EQ. 0, FORM STIFFNESS MATRIX                        
      EQ. 1, USE EXISTING DECOMPOSED STIFFNESS MATRIX     

   SPIN SOFTENING FLAG . . . . . . . . . . . . (ISPIN)   =           0
      EQ. 0, NO SPIN SOFTENING EFFECTS CONSIDERED         
      EQ. 1, SPIN SOFTENING EFFECTS CONSIDERED            
   INERTIA RELIEF FLAG  . . . . . . . . . . . .(IFORMK)  =           0
      EQ. 0, NO INERITA RELIEF EFFECTS CONSIDERED         
      EQ. 1, INERITA RELIEF EFFECTS CONSIDERED            
   RIGID CONNECTIONS FLAG  . . . . . . . . . . (IRIGID)  =           0
      EQ. 0, HINGE CONNECTIONS BETWEEN SOLIDS & SHELLS    
      EQ. 1, RIGID CONNECTIONS BETWEEN SOLIDS & SHELLS    


  T O T A L  S Y S T E M  D A T A                        
   NUMBER OF EQUATIONS . . . . . . . . . . . . . .(NEQ)  =        5130
   NUMBER OF ELEMENTS. . . . . . . . . . . . . . .(NUME) =        4312
   NUMBER OF NODAL POINTS. . . . . . . . . . . . .(NUMNP)=        2508




************************************************************************
    D I S P L A C E M E N T     P R I N T O U T    (LOAD CASE     1)
************************************************************************




************************************************************************
    D I S P L A C E M E N T     P R I N T O U T    (LOAD CASE     1)
************************************************************************


  STATUS OF THERMAL EFFECTS FOR THIS LOAD CASE:
  ---------------------------------------------

    - Thermal flag is off (no thermal effect)



             D I S P L A C E M E N T S

     NODE X-DISPL.     Y-DISPL.     Z-DISPL.     XX-ROT.      YY-ROT.      ZZ-ROT.


 MINIMUM/MAXIMUM DISPLACEMENTS

  NODE      1697         1689         1669         2334         1716         1689
  MIN.  -3.22273E-04 -1.50638E-03 -2.60086E-09 -3.43079E-06 -6.26373E-06 -5.12035E-02

  NODE      1689         2467         1696         1717         2469         2472
  MAX.   3.74770E-04  3.45221E-07  1.84354E-07  3.10718E-07  4.35245E-07  2.42799E-04

 MAXIMUM RESULTANT DISPLACEMENT

  NODE      1689
  MAX.   1.55230E-03




********************************************************************************
         R E A C T I O N   F O R C E   F O R   LOAD CASE NO.  1
********************************************************************************

    NODE CSYS    Fx         Fy         Fz         Mx         My         Mz

 FOR REQUESTED                 (Global Cartesian Coord. System)
    NODES         FX         FY         FZ         MX         MY         MZ
 Total React. 0.6002E+01 0.1210E+05 -.3516E+00 0.2309E-02 0.2364E-02 0.8686E-02
  



********************************************************************************
 MAXIMUM NODAL VON MISES STRESS & ERROR ESTIMATE FOR LOAD CASE   1
********************************************************************************

  NODE      1689
  MAX.     0.13759E+10



   E R R O R    E S T I M A T I O N
   (for requested elements)

   Total Strain Energy (TSE)        =  0.911357E+01
   Total Error Energy (TEE)         =  0.135150E+00
   Ave. Percentage Error (APE)      =  0.857916E+01
     ( APE =  sqrt (TEE/(TSE*2. + TEE)) * 100. )

  S O L U T I O N   T I M E   L O G   I N   S E C
            FOR PROBLEM
     TIME FOR INPUT PHASE  . . . . . . . . . . . . . . =       0
     TIME FOR CALCULATION OF STRUCTURE STIFFNESS MATRIX=       0
     TIME FOR FFEPLUS (PCG ITERATIVE) SOLVER . . . . . =       0
     TIME FOR AL CONTACT (AND/OR LARGE DISP) OPERATIONS=       0
     TIME FOR REACTION FORCE & DISP UPDATE TO POST . . =       0
     TIME FOR STRESS CALCULATION . . . . . . . . . . . =       0
     TIME FOR LOAD CASE SOLUTIONS  . . . . . . . . . . =       0
      T O T A L   S O L U T I O N   T I M E  . . . . . =       1



T O T A L   S O L U T I O N   T I M E (sec) . . . . =       1
