Chapter 10 板殼結構分析 Analysis of Plates and Shells

2/34 Contents 10.1SHELL63: 板殼結構元素 SHELL63: Structural Shell Element 10.2 實例 : C 型斷面懸臂樑 Example: Channel Section Cantilever Beam 10.3 實例 : 氣曩之充氣模擬 Example: Inflation of an Airbag 10.4 板殼元素瀏覽 Overview of Shell Elements 10.5 練習題 : 懸臂樑分析 Analysis of Cantilevel Beam

3/34 第 10.1 節 SHELL63: 板殼結構元素 SHELL63: Structural Shell Element

4/ SHELL63 元素描述

5/ SHELL63 輸入資料 Element NameSHELL63 NodesI, J, K, L Degrees of FreedomUX, UY, UZ, ROTX, ROTY, ROTZ Real ConstantsTK(I), TK(J), TK(K), TK(L), EFS, THETA, RMI, CTOP, CBOT, …, ADMSUA, etc. Material PropertiesEX, NUXY, GXY, ALPX, DENS, DAMP, etc. Surface LoadsPressure face 1, face 2, face 3, face 4, face 5, face 6 Body LoadsTemperature -- T(1), T(2), T(3), T(4), T(5), T(6), T(7), T(8) Special FeaturesStress stiffening, Large deflection, etc. KEYOPT(1)0 -- Bending and membrane stiffness 1 -- Membrane stiffness only 2 -- Bending stiffness only KEYOPT(3)Key for inclusion of extra displacement shapes KEYOPT(5)Key for element solution etc.

6/ SHELL63 輸出資料

7/34 第 10.2 節 實例 : C 型斷面懸臂樑 Example: Channel Section Cantilever Beam

8/ 問題描述

9/ ANSYS Procedure (1/4) FINISH /CLEAR /TITLE, C6X8.2 Section Cantilever Beam /UNITS, BIN D = 6! Depth BF = 1.92! Flange width TW = 0.2! Thickness of web TF = ! Thickness of flange L = 36! Length E = 30E6! Young's modulus NU = 0.3! Poisson's Ratio P = 2400! Load SZ = 1.2! Element size

10/ ANSYS Procedure (2/4) /PREP7 ET, 1, SHELL63 MP, EX, 1, E MP, NUXY, 1, NU R, 1, TW R, 2, TF /VIEW,, 1, 2, 3 K, 1, 0, 0, BF K, 2, 0, 0, 0 K, 3, 0, D, 0 K, 4, 0, D, BF K, 5, L, 0, BF K, 6, L, 0, 0 K, 7, L, D, 0 K, 8, L, D, BF A, 1, 2, 6, 5 A, 2, 3, 7, 6 A, 4, 3, 7, ESIZE, SZ MSHAPE, 0, 2D MSHKEY, 1 REAL, 1 AMESH, 2 REAL, 2 AMESH, 1, 3, 2 FINISH /SOLU NSEL, S, LOC, X, 0 D, ALL, ALL, 0 ALLSEL ND = NODE(L,D,BF) F, ND, FY, -P /PBC, ALL,, ON EPLOT SOLVE FINISH

11/ ANSYS Procedure (3/4) /POST1 PLDISP, 2 PLNSOL, S, X /VIEW,, 1, 0, 0 PLDISP, 2

12/ ANSYS Procedure (4/4) /POST1 PLDISP, 2 PLNSOL, S, X /VIEW,, 1, 0, 0 PLDISP, 2

13/34 第 10.3 節 實例 : 氣曩之充氣模擬 Example: Inflation of an Airbag

14/ 問題描述

15/ ANSYS Procedure (1/6) FINISH /CLEAR /TITLE, Inflation of Air Bag /UNITS, SI RO = 1000! Mass density E = 2E9! Young's Modulus NU = 0.4! Poisson's Ratio T = ! Thickness R = 0.25! Radius of air bag P = 0.5E5! Pressure DV = 20! Number of divisions TM = 0.1! Inflation time DT = 0.001! Integration time step

16/ ANSYS Procedure (2/6) /PREP7 ET, 1, SHELL63 MP, EX, 1, E MP, NUXY, 1, NU MP, DENS, 1, RO R, 1, T CSYS, 1 PCIRC, R,, 0, 30 LESIZE, 1, LESIZE, 2,,, 20, 5 LESIZE, 3,,, 20, 1/5 MSHAPE, 0, 2D MSHKEY, 0 AMESH, ALL NROTAT, ALL CNODE = NODE(0,0,0) ENODE = NODE(R,0,0) FINISH

17/ ANSYS Procedure (3/6) /SOLU NSEL, S, LOC, Y, 0 NSEL, A, LOC, Y, 30 DSYM, SYMM, Y, 1 NSEL, S, LOC, X, R D, ALL, UZ, 0 D, ALL, ROTX, 0 ALLSEL SFE, ALL, 1, PRES,, P ANTYPE, TRANS NLGEOM, ON SSTIF, ON KBC, 0 TIME, TM DELTIM, DT OUTRES, NSOL, ALL SOLVE TIME, 1 DELTIM, 0.01 SOLVE FINISH

18/ ANSYS Procedure (4/6) /POST1 SET, LAST /VIEW,, 1, -90, 0 /VUP,, Z PLDISP, 2 /VIEW,, 0, 0, 1 /VUP,, Y PLDISP, 2

19/ ANSYS Procedure (5/6) SHELL, MID RSYS, 1 PLNSOL, S, X PLNSOL, S, Y FINISH

20/ ANSYS Procedure (6/6) /POST26 NSOL, 2, CNODE, U, Z PLVAR, 2 NSOL, 3, ENODE, U, X PLVAR, 3

21/ Simulation Results Using LS-DYNA (1/2)

22/ Simulation Results Using LS-DYNA (2/2)

23/34 第 10.4 節 板殼結構元素瀏覽 Overview of Shell Elements

24/ Elastic Shells

25/ Plastic Shells

26/ Large Strain Shell

27/ Membrane and Shear Panel

28/ Axisymmetric Shell

29/ Layer Shells

30/ P-Element

31/ Explicit Dynamics

32/ Thermal Shell

33/ Coupled-Field Shell

34/34 第 10.5 節 練習題 : 懸臂樑分析 Exercise: Analysis of Cantilever Beam