³ ³ x y - Vibrationdata · 2019-03-27 · 1 PLATE BENDING FREQUENCIES VIA THE FINITE ELEMENT...
Transcript of ³ ³ x y - Vibrationdata · 2019-03-27 · 1 PLATE BENDING FREQUENCIES VIA THE FINITE ELEMENT...
1
PLATE BENDING FREQUENCIES VIA THE FINITE ELEMENT METHOD
WITH RECTANGULAR ELEMENTS
Revision A
By Tom Irvine
Email: [email protected]
May 6, 2011
Rectangular Plate in Bending
Figure 1.
Stiffness Matrix
Let u represent the out-of-plane displacement. The total strain energy of the plate is
dxdyyx
u12
y
u
x
u2
y
u
x
u
2
DU
b
0
a
0
22
2
2
2
22
2
22
2
2
(1)
a
b
Y
X 0
k l
m n
2
Note that the plate stiffness factor D is given by
)1(12
EhD
2
3
(2)
where
E = elastic modulus
h = plate thickness
= Poisson's ratio
The plate has one translational and two rotational degrees-of-freedom at each corner, for a total of 12
degrees-of-freedom. The two rotational components are about the x and y-axes respectively.
Let the four corners be labeled k, l, m, and n, as shown in Figure 1.
The rotation components θ at the corner 1 are
x
u
l
lx (3)
y
u
l
ly (4)
The displacement equation has 12 constants to enforce 12 continuity conditions.
312
311
310
29
28
37
265
24321
xyayxayaxyayxa
xayaxyaxayaxaa)t,y,x(u
(5)
The displacement equation can be written as
Z}A{)t,y,x(u T (6)
where
121110987654321T aaaaaaaaaaaa}A{ (7)
3
33322322T xyyxyxyyxxyxyxyx1}Z{ (8)
The strain energy is thus
Adxdy)y,x(SA2
DU
b
0
a
0
T (9)
where
22
2
2
2
22
2
22
2
2
yx
u12
y
u
x
u2
y
u
x
u)y,x(S
(10)
Again,
312
311
310
29
28
37
265
24321
xyayxayaxyayxa
xayaxyaxayaxaa)t,y,x(u
(11)
312
211
298
27542 yayxa3yaxya2xa3yaxa2a)t,y,x(u
x
(12)
212
311
2109
28653 xya3xaya3xya2xaya2xaa)t,y,x(u
y
(13)
4
The displacement and derivatives at each corner are
1a}t,0,0{u (14)
2a}t,0,0{x
u
(15)
3a}t,0,0{y
u
(16)
)a(a)a(a)a(a)a(}t,0,a{u 73
42
21 (17)
)a(a3)a(a2)a(}t,0,a{x
u7
242
(18)
)a(a)a(a)a(a)a(}t,0,a{y
u11
38
253
(19)
312
311
310
29
28
37
265
24321
ababaabaababaa
aabaabaaabaaaa}t,b,a{u
(20)
)a(b)a(ba3)a(b)a(ab2)a(a3)a(b)a(a2)a(}t,b,a{x
u12
311
29
287
2542
(21)
)a(ab3)a(a)a(b3)a(ab2)a(a)a(b2)a(a)a(}t,b,a{y
u12
211
310
298
2653
(22)
310
2631 b)a(b)a(b)a()a(}t,b,0{u (23)
312
2952 b)a(b)a(b)a()a(}t,b,0{
x
u
(24)
)a(b3)a(b2)a(}t,b,0{y
u10
263
(25)
5
The displacement vector for element i is
ynxnnymxmmylxllykxkki uuuu}u{ T (26)
The displacement vector can be written as
AB}u{ i (27)
where
00b3000b200100
b00b000b0010
00b000b00b01
ab3ab3ab22a0b2a0100
bba30bab2a30ba2010
abbababbaabababa1
0a00a00a0100
00000a300a2010
00000a00a0a1
000000000100
000000000010
000000000001
]B[
2
32
32
232
3222
33322322
32
2
32
(28)
Solve for A .
i}u{BA 1 (29)
Let
1B]c[ (30)
i}u{cA (31)
6
The strain energy is thus
i}u{cdxdy)y,x(Scu2
DU
b
0
a
0
TT (32)
The kinetic energy is
dxdyu2
hK
b
0
a
0
2
(33)
Recall the displacement equation
Z}A{)t,y,x(u T (34)
The velocity is
Z}A{u T (35)
}A{ZZ}A{]u[ TT2 (36)
Recall
i}u{cA (37)
ii }u{cZZc}u{]u[ TTT2 (38)
Let
TZZ)y,x(P (39)
ii }u{c)y,x(Pc}u{]u[ TT2 (40)
7
The kinetic energy is thus
ii }u{cdxdy)y,x(Pc}u{2
hK
b
0
a
0
TT
(41)
The virtual work due to the nodal forces and moment is
iiii }F{}u{}u{}F{W T (42)
where
ynxnnymxmmylxllykxkki MMFMMFMMFMMF}F{ T
(43)
Hamilton’s principle yields the equation of motion.
i}F{}u]{k[}u]{m[ ii (44)
The respective local mass and stiffness matrices are
]c[dxdy)y,x(P]c[h]m[b
0
a
0
T (45)
]c[dxdy)y,x(S]c[D]k[b
0
a
0
T (46)
The local matrices can then be assembled into global matrices. Then boundary conditions can be
applied.
8
The generalized eigenvalue problem is
0U}]M[]K[{ 2 (47)
where
K is the global stiffness matrix
M is the global mass matrix
is the natural frequency
U is the corresponding mode shape
Note that there is a natural frequency and mode shape for each degree-of-freedom.
References
1. W. Soedel, Vibrations of Shells and Plates, Third Edition (Dekker Mechanical Engineering), Third Edition, Marcel Dekker, New York, 2004.
2. R. Blevins, Formulas for Natural Frequency and Mode Shape, Krieger, Malabar, Florida,
1979. See Table 11-6.
9
APPENDIX A
Mass Matrix Core
33322322
3
3
3
2
2
3
2
2
T xyyxyxyyxxyxyxyx1
xy
yx
y
xy
yx
x
y
xy
x
y
x
1
}Z}{Z{
(A-1)
10
62446524334542334323
44264334256332452343
6436542335432433
52345423324432233222
43254233245322342232
3463324562345343
5335432234322322
4224432234322322
33532234522342232
423432233222
324322342232
33322322
T
yxyxxyyxyxyxxyyxyxxyyxxy
yxyxyxyxyxyxyxyxyxyxyxyx
xyyxyxyyxyxyxyyxyxyy
yxyxxyyxyxyxxyyxyxxyyxxy
yxyxyxyxyxyxyxyxyxyxyxyx
yxyxyxyxyxxyxyxxyxxx
xyyxyxyyxyxyxyyxyxyy
yxyxxyyxyxyxxyyxyxxyyxxy
yxyxyxyxyxxyxyxxyxxx
xyyxyxyyxyxyxyyxyxyy
yxyxxyyxyxxxyyxxxyxx
xyyxyxyyxxyxyxyx1
}Z}{Z{
(A-2)
11
APPENDIX B
Stiffness Matrix Core
Again,
33322322T xyyxyxyyxxyxyxyx1}Z{ (B-1)
The derivatives are
3222T
yyx30yxy2x30yx2010x
Z
(B-2)
0xy600y2x6002000x
ZT
2
2
(B-3)
2322T
xy3xy3xy2x0y2x0100y
Z
(B-4)
xy60y6x200200000y
ZT
2
2
(B-5)
22
T2
y3x30y2x20010000yx
Z
(B-6)
12
0xy600y2x6002000
0
xy6
0
0
y2
x6
0
0
2
0
0
0
x
Z
x
ZT
2
2
2
2
(B-7)
000000000000
0yx3600xy12yx3600xy12000
000000000000
000000000000
0xy1200y4xy1200y4000
0yx3600xy12x3600x12000
000000000000
000000000000
0xy1200y4x12004000
000000000000
000000000000
000000000000
x
Z
x
Z
2222
22
22
T
2
2
2
2
(B-8)
13
xy60y6x200200000
xy6
0
y6
x2
0
0
2
0
0
0
0
0
y
Z
y
ZT
2
2
2
2
(B-9)
2222
22
22
T
2
2
2
2
yx360xy36yx1200xy1200000
000000000000
xy360y36xy1200y1200000
yx120xy12x400x400000
000000000000
000000000000
xy120y12x400400000
000000000000
000000000000
000000000000
000000000000
000000000000
y
Z
y
Z
(B-10)
14
2222
2222
22
22
22
22
T
2
2
2
2T
2
2
2
2
yx360xy36yx1200xy1200000
0yx3600xy12yx3600xy12000
xy360y36xy1200y1200000
yx120xy12x400x400000
0xy1200y4xy1200y4000
0yx3600xy12x3600x12000
xy120y12x400400000
000000000000
0xy1200y4x12004000
000000000000
000000000000
000000000000
y
Z
y
Z
x
Z
x
Z
(B-11)
15
xy60y6x200200000
0
xy6
0
0
y2
x6
0
0
2
0
0
0
y
Z
x
ZT
2
2
2
2
(B-12)
000000000000
yx360xy36yx1200xy1200000
000000000000
000000000000
xy120y12xy400y400000
yx360xy36x1200x1200000
000000000000
000000000000
xy120y12x400400000
000000000000
000000000000
000000000000
y
Z
x
Z
2222
22
22
T
2
2
2
2
(B-13)
16
0xy600y2x6002000
xy6
0
y6
x2
0
0
2
0
0
0
0
0
x
Z
y
ZT
2
2
2
2
(B-14)
0yx3600xy12yx3600xy12000
000000000000
0xy3600y12xy3600y12000
0yx1200xy4x1200x4000
000000000000
000000000000
0xy1200y4x12004000
000000000000
000000000000
000000000000
000000000000
000000000000
x
Z
y
Z
2222
22
22
T
2
2
2
2
(B-15)
17
0yx3600xy12yx3600xy12000
yx360xy36yx1200xy1200000
0xy3600y12xy3600y12000
0yx1200xy4x1200x4000
xy120y12xy400y400000
yx360xy36x1200x1200000
0xy1200y4x12004000
000000000000
xy120y12x400400000
000000000000
000000000000
000000000000
x
Z
y
Z
y
Z
x
Z
2222
2222
22
22
22
22
T
2
2
2
2T
2
2
2
2
(B-16)
18
22
2
2
T22
y3x30y2x20010000
y3
x3
0
y2
x2
0
0
1
0
0
0
0
yx
Z
yx
Z
(B-17)
422322
224232
322
232
22
T22
y9yx90y6xy600y30000
yx9x90yx6x600x30000
000000000000
y6yx60y4xy400y20000
xy6x60xy4x400x20000
000000000000
000000000000
y3x30y2x20010000
000000000000
000000000000
000000000000
000000000000
yx
Z
yx
Z
(B-18)
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Let 12
42222222322222
22224222223222
2222
3222222
2232222
2222
22
T22
T
2
2
2
2T
2
2
2
2T
2
2
2
2T
2
2
2
2
y9yx36yx9yx36xy36y6yx12xy6xy12yx36xy12y3xy12000
yx9yx36x9yx36xy36yx6yx12x6xy12yx36xy12x3xy12000
xy36xy36y36xy12y12xy36y120y12000
y6yx12yx6yx12xy12y4x4xy4xy4x12x4y2x4000
xy6xy12x6xy12y12xy4xy4x4y4xy12y4x2y4000
yx36yx36xy36x12xy12x36x120x12000
xy12xy12y12x4y4x12404000
y3x30y2x20010000
xy12xy12y12x4y4x12404000
000000000000
000000000000
000000000000
yx
Z
yx
Z
x
Z
y
Z
y
Z
x
Z
y
Z
y
Z
x
Z
x
Z
(B-19)
20
APPENDIX C
Example 1
Consider an aluminum plate, with dimensions 4 x 6 x 0.125 inches. The plate is simply-supported on
all sides.
The natural frequencies are
,3,2,1n,,3,2,1m,b
n
a
m
h
D22
(C-1)
inlbf1789
)2^3.01(12
3)^in125.0)(2^in/lbf07e0.1(
)1(12
EhD
2
3
(C-2)
sec^2/in^3 lbf05-3.238e
)in125.0(sec^2/in^4 lbf)386/1.0(h
(C-3)
21
,3,2,1n,,3,2,1m,in4
n
in6
m
sec^2/in^3 lbf05-3.238e
inlbf178922
mn
(C-4)
Table C-1. Natural Frequencies,
Hand Calculation
fn(Hz) m n
1054 1 1
2027 2 1
3243 1 2
3649 3 1
4216 2 2
Now perform a finite element analysis with 13 nodes along the X-axis and 9 nodes along the Y-axis.
The analysis is performed using the mass and stiffness matrices derived in the main text, as
implemented in Matlab script: plate_fea.m
The fundamental mode shape is shown in Figure C-1. The natural frequency comparison is shown in
Table C-2.
22
Figure C-1.
Table C-2. Natural Frequencies
Mode
Hand
Calculation
fn(Hz)
FEA
fn(Hz)
1 1054 1049
2 2027 2006
3 3243 3223
4 3649 3603
5 4216 4136
01
23
45
6
0
1
2
3
4
0
50
100
Mode 1 fn= 1049 Hz
23
APPENDIX D
Example 2
Repeat example 1 but change the boundary conditions such that the corners are pinned. The edges
are otherwise free.
The fundamental frequency is 291 Hz using the hand calculation formula from Reference 2.
Again, the analysis is performed using the mass and stiffness matrices derived in the main text, as
implemented in Matlab script: plate_fea.m
The natural frequency comparison is shown in Table D-1. The mode shapes are shown in the
following figures.
Table D-1. Natural Frequencies
Mode
Hand
Calculation
fn(Hz)
FEA
fn(Hz)
1 291 294
2 - 708
3 - 852
4 - 1110
5 - 1739
24
Figure D-1.
Figure D-2.
01
23
45
6
0
1
2
3
4
0
20
40
60
80
100
Mode 1 fn= 294.2 Hz
01
23
45
6
0
1
2
3
4
-150
-100
-50
0
50
100
150
Mode 2 fn= 708 Hz
25
Figure D-3.
Figure D-4.
0 1 2 3 4 5 6
0
1
2
3
4
-80
-60
-40
-20
0
20
40
60
80
Mode 3 fn= 852.3 Hz
01
23
45
6
0
0.5
1
1.5
2
2.5
3
3.5
4
-60
-40
-20
0
20
40
60
80
100
Mode 4 fn= 1110 Hz
26
Figure D-5.
0
1
2
3
4
5
6
0
0.5
1
1.5
2
2.5
3
3.5
4
-100
-50
0
50
100
Mode 5 fn= 1739 Hz