**************************************************************** **************************************************************** ** ** ** ** ** CCC OO SSS M M OO SSS ** ** C O O S MM MM O O S ** ** C O O SS M MM M O O SS ** ** C O O S M M O O S ** ** CCC OO SSS M M OO SSS ** ** ** ** ** ** Simulations V2016 ** ** Distributed By: SolidWorks Corporation ** ** 6320 Canoga Avenue, Suite 300 ** ** Woodland Hills, California 91367 ** ** Telephone Number (818)673-2200 ** ** Copyright 1988-2011 SolidWorks Corporation ** ** ** **************************************************************** **************************************************************** Problem name: C:\Users\anabavi\Desktop\anabavi\project Date : 01/27/2018 Time: 10:39:09 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 C O N T R O L I N F O R M A T I O N 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 ITERATIVE SOLUTION MODE . . . . . . . . . . (IMODE) = 2 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) = 69396 NUMBER OF ELEMENTS. . . . . . . . . . . . . . .(NUME) = 12752 NUMBER OF NODAL POINTS. . . . . . . . . . . . .(NUMNP)= 23762 ************************************************************************ * R E S P O N S E P R I N T O U T (LOAD CASE 1) * ************************************************************************ ************************************************************************ * R E S P O N S E 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 1130 23762 23418 0 0 0 MIN. -4.60836E-09 -2.43553E-08 -2.41279E-10 0.0000 0.0000 0.0000 NODE 1831 945 23762 0 0 0 MAX. 2.54596E-09 8.16739E-10 2.46695E-10 0.0000 0.0000 0.0000 MAXIMUM RESULTANT DISPLACEMENT NODE 23762 MAX. 2.44297E-08 FOR REQUESTED (Global Cartesian Coord. System) NODES FX FY FZ MX MY MZ Total React. 0.6152E-02 0.1736E+00 -.4010E-05 0.0000E+00 0.0000E+00 0.0000E+00 TOTAL STRAIN ENERGY. . . . . . . . . . . = 0.101964E-08 MAXIMUM NODAL VON MISES STRESS NODE 1323 MAX. 5151.7 E R R O R E S T I M A T I O N (for requested elements) Total Strain Energy (TSE) = 0.101964E-08 Total Error Energy (TEE) = 0.264212E-09 Ave. Percentage Error (APE) = 0.338675E+02 ( 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 . . . . . . . . . . . . . . = 1 TIME FOR CALCULATION OF STRUCTURE STIFFNESS MATRIX= 0 TIME FOR FFEPLUS (PCG ITERATIVE) SOLVER . . . . . = 4 TIME FOR AL CONTACT (AND/OR LARGE DISP) OPERATIONS= 0 TIME FOR REACTION FORCE & DISP UPDATE TO POST . . = 1 TIME FOR STRESS CALCULATION . . . . . . . . . . . = 1 TIME FOR LOAD CASE SOLUTIONS . . . . . . . . . . = 0 T O T A L S O L U T I O N T I M E . . . . . = 6 T O T A L S O L U T I O N T I M E (sec) . . . . = 6