Introduction to Aircraft Structural Analysis (Elsevier Aerospace Engineering)

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510 CHAPTER 17 Torsion of Beams


SubstitutinginEq.(i)andsettingw 0 = 0

w′ 12 =


2 abG

(

s 1
δta


s 1
4 a

)

(iv)

sothatw′ 12 varieslinearlyfromzeroat1to


w′ 2 =

T

2 abG

2

(

b
tb

+

a
ta

)[

a
2 (b/tb+a/ta)ta


1

4

]

at2.Thus,


w′ 2 =

T

4 abG

(

a
ta


b
tb

)

or


w′ 2 =−

T

4 abG

(

b
tb


a
ta

)

(v)

Similarly,


w′ 23 =


2 abG

[

1

δ

(

a
ta

+

s 2
tb

)


1

4 b

(b+s 2 )

]

(vi)

Thewarpingdistributionthereforevarieslinearlyfromavalue−T(b/tb−a/ta)/ 4 abGat2tozero
at3.Theremainingdistributionfollowsfromsymmetrysothatthecompletedistributiontakestheform
showninFig.17.7.


Fig.17.7


Warping distribution produced by selecting an arbitrary origin fors.

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