chapter 10 板殼結構分析 analysis of plates and shells. 2/34 contents 10.1shell63:...
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Chapter 10
板殼結構分析Analysis of Plates and Shells
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Contents
10.1 SHELL63: 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 Be
am
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
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第 10.1節
SHELL63: 板殼結構元素SHELL63: Structural Shell Element
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10.1.1 SHELL63元素描述
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10.1.2 SHELL63輸入資料Element Name SHELL63
Nodes I, J, K, L
Degrees of Freedom UX, UY, UZ, ROTX, ROTY, ROTZ
Real Constants TK(I), TK(J), TK(K), TK(L), EFS, THETA, RMI, CTOP, CBOT, …, ADMSUA, etc.
Material Properties EX, NUXY, GXY, ALPX, DENS, DAMP, etc.
Surface Loads Pressureface 1, face 2, face 3, face 4, face 5, face 6
Body Loads Temperature -- T(1), T(2), T(3), T(4), T(5), T(6), T(7), T(8)
Special Features Stress stiffening, Large deflection, etc.
KEYOPT(1) 0 -- Bending and membrane stiffness1 -- Membrane stiffness only2 -- Bending stiffness only
KEYOPT(3) Key for inclusion of extra displacement shapes
KEYOPT(5) Key for element solution
etc.
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10.1.3 SHELL63輸出資料
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第 10.2節
實例 : C型斷面懸臂樑Example: Channel Section Cantilever Beam
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10.2.1 問題描述
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10.2.2 ANSYS Procedure (1/4)01
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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 = 0.3125 ! 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
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10.2.2 ANSYS Procedure (2/4)16
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/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, 8
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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
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10.2.2 ANSYS Procedure (3/4)59
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/POST1
PLDISP, 2
PLNSOL, S, X
/VIEW,, 1, 0, 0
PLDISP, 2
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10.2.2 ANSYS Procedure (4/4)59
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/POST1
PLDISP, 2
PLNSOL, S, X
/VIEW,, 1, 0, 0
PLDISP, 2
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第 10.3節
實例 : 氣曩之充氣模擬Example: Inflation of an Airbag
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10.3.1 問題描述
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10.3.2 ANSYS Procedure (1/6)
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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 = 0.0025 ! 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
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10.3.2 ANSYS Procedure (2/6)16
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/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, 0.005
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
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10.3.2 ANSYS Procedure (3/6)
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/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
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ANTYPE, TRANS
NLGEOM, ON
SSTIF, ON
KBC, 0
TIME, TM
DELTIM, DT
OUTRES, NSOL, ALL
SOLVE
TIME, 1
DELTIM, 0.01
SOLVE
FINISH
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10.3.2 ANSYS Procedure (4/6)
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/POST1
SET, LAST
/VIEW,, 1, -90, 0
/VUP,, Z
PLDISP, 2
/VIEW,, 0, 0, 1
/VUP,, Y
PLDISP, 2
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10.3.2 ANSYS Procedure (5/6)
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SHELL, MID
RSYS, 1
PLNSOL, S, X
PLNSOL, S, Y
FINISH
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10.3.2 ANSYS Procedure (6/6)83
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/POST26
NSOL, 2, CNODE, U, Z
PLVAR, 2
NSOL, 3, ENODE, U, X
PLVAR, 3
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10.3.3 Simulation Results Using LS-DYNA (1/2)
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10.3.3 Simulation Results Using LS-DYNA (2/2)
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第 10.4節
板殼結構元素瀏覽Overview of Shell Elements
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10.4.1 Elastic Shells
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10.4.2 Plastic Shells
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10.4.3 Large Strain Shell
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10.4.4 Membrane and Shear Panel
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10.4.5 Axisymmetric Shell
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10.4.6 Layer Shells
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10.4.7 P-Element
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10.4.8 Explicit Dynamics
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10.4.9 Thermal Shell
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10.4.10 Coupled-Field Shell
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第 10.5節
練習題 : 懸臂樑分析Exercise: Analysis of Cantilever Beam