**************************************************************** **************************************************************** ** ** ** ** ** 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 ** ** ** ** ** ** COSMOSWorks V2008 SP01 ** ** Distributed By: SolidWorks Corporation ** ** 3000 Ocean Park Blvd., Suite 2001 ** ** Santa Monica, California 90405 ** ** Telephone Number (310)309-2800 ** ** Copyright 1988-2004 SolidWorks Corporation ** ** ** **************************************************************** **************************************************************** Problem name: C:\Documents and Settings\jon\Desktop\De Date : 01/30/2008 Time: 09:35:52 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 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-05 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) = 1722261 NUMBER OF ELEMENTS. . . . . . . . . . . . . . .(NUME) = 414480 NUMBER OF NODAL POINTS. . . . . . . . . . . . .(NUMNP)= 574087 ************************************************************************ * 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) FORCES ON THE ACTIVE CONTACT ELEMENT(S) ELEMENT NODE TARGET FX FY FZ NORMAL FORCE TOTAL 0.0000E+00 0.0000E+00 0.0000E+00 TOTAL NUMBER OF ACTIVE CONTACT ELEMENT(S) = 0 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 10457 10517 0 0 0 0 MIN. -9.58337E-06 -9.57952E-06 0.0000 0.0000 0.0000 0.0000 NODE 108366 115555 552390 0 0 0 MAX. 2.03936E-06 2.03891E-06 1.13102E-05 0.0000 0.0000 0.0000 MAXIMUM RESULTANT DISPLACEMENT NODE 10460 MAX. 1.36521E-05 FOR REQUESTED (Global Cartesian Coord. System) NODES FX FY FZ MX MY MZ Total React. 0.1131E+04 0.1131E+04 -.2441E+03 0.0000E+00 0.0000E+00 0.0000E+00 TOTAL STRAIN ENERGY. . . . . . . . . . . = 0.403150E-02 MAXIMUM NODAL VON MISES STRESS NODE 573897 MAX. 0.34855E+09 E R R O R E S T I M A T I O N (for requested elements) Total Strain Energy (TSE) = 0.403150E-02 Total Error Energy (TEE) = 0.115648E-03 Ave. Percentage Error (APE) = 0.118913E+02 ( APE = sqrt (TEE/(TSE*2. + TEE)) * 100. ) T O T A L S O L U T I O N T I M E (sec) . . . . = 387