Introduction to Aircraft Structural Analysis (Elsevier Aerospace Engineering)

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6.4Matrix Analysis of Pin-jointed Frameworks 181

wheretheyoverlap;forexample,the[k 11 ]submatrixinEq.(ii)receivescontributionsfrom[K 12 ]and
[K 13 ]. The complete stiffness matrix is then of the form shown in Eq. (iv). It is sometimes helpful,
whenconsideringthestiffnessmatrixseparately,towritethenodaldisplacementabovetheappropriate
column(seeEq.(iv)).Wenotethat[K]issymmetrical,thatallthediagonaltermsarepositive,andthat
thesumofeachrowandcolumniszero


[K 12 ]=

AE

L

⎡ ⎢ ⎢ ⎢ ⎢ ⎢ ⎢ ⎢ ⎢ ⎣

10

k 11
00

− 10

k 12
00

− 10
k 21
00

10

k 22
00

⎤ ⎥ ⎥ ⎥ ⎥ ⎥ ⎥ ⎥ ⎥ ⎦

[K 13 ]=

AE

L

⎡ ⎢ ⎢ ⎢ ⎢ ⎢ ⎢ ⎢ ⎢ ⎣

00

k 11
01

00

k 13
0 − 1

00
k 31
0 − 1

00

k 33
01

⎤ ⎥ ⎥ ⎥ ⎥ ⎥ ⎥ ⎥ ⎥ ⎦

(iii)

[K 23 ]=

AE


2 L

⎡ ⎢ ⎢ ⎢ ⎢ ⎢ ⎢ ⎢ ⎢ ⎢ ⎢ ⎢ ⎢ ⎢ ⎢ ⎣

1

2


1

2

k 22

1

2

1

2


1

2

1

2

k 23
1
2


1

2


1

2

1

2

k 32
1
2


1

2

1

2


1

2

k 33

1

2

1

2

⎤ ⎥ ⎥ ⎥ ⎥ ⎥ ⎥ ⎥ ⎥ ⎥ ⎥ ⎥ ⎥ ⎥ ⎥ ⎦ ⎧

⎪⎪

⎪⎪⎪

⎪⎨

⎪⎪

⎪⎪

⎪⎪


Fx,1
Fy,1
Fx,2
Fy,2
Fx,3
Fy,3


⎪⎪

⎪⎪

⎪⎪⎬

⎪⎪

⎪⎪

⎪⎪


=

AE

L

⎡u^1 v^1 u^2 v^2 u^3 v^3
⎢ ⎢ ⎢ ⎢ ⎢ ⎢

⎢⎢

⎢ ⎢ ⎢ ⎢ ⎢ ⎢ ⎢ ⎣

10 −100 0

01 0 0 0 − 1

− 101 +

1

2


2


1

2


2


1

2


2

1

2


2

00 −

1

2


2

1

2


2

1

2


2


1

2


2

00 −

1

2


2

1

2


2

1

2


2


1

2


2

0 − 1

1

2


2


1

2


2


1

2


2

1 +

1

2


2

⎤ ⎥ ⎥ ⎥ ⎥ ⎥ ⎥

⎥⎥

⎥ ⎥ ⎥ ⎥ ⎥ ⎥ ⎥ ⎦


⎪⎪

⎪⎪⎪

⎪⎨

⎪⎪

⎪⎪

⎪⎪


u 1 = 0
v 1 = 0
u 2
v 2
u 3 = 0
v 3 = 0


⎪⎪

⎪⎪

⎪⎪⎬

⎪⎪

⎪⎪

⎪⎪


(iv)
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