Introduction to Aircraft Structural Analysis (Elsevier Aerospace Engineering)

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540 CHAPTER 19 Structural Idealization


TheidealizedsectionisshowninFig.19.4(b),inwhich,fromsymmetry,B 1 =B 6 ,B 2 =B 5 ,B 3 =B 4.
Sincethesectionisrequiredtoresistbendingmomentsinaverticalplane,thedirectstressatanypoint
intheactualwingsectionisdirectlyproportionaltoitsdistancefromthehorizontalaxisofsymmetry.
Further,thedistributionofdirectstressinallthepanelswillbelinearsothateitherofEq.(19.1)orof
Eq.(19.2)maybeused.Wenotethatinadditiontocontributionsfromadjacentpanels,theboomareas
includetheexistingsparflanges.Hence,


B 1 = 300 +

3.0× 400

6

(

2 +

σ 6
σ 1

)

+

2.0× 600

6

(

2 +

σ 2
σ 1

)

or


B 1 = 300 +

3.0× 400

6

( 2 − 1 )+

2.0× 600

6

(

2 +

150

200

)

whichgives


B 1 (=B 6 )=1050mm^2

Also,


B 2 = 2 × 300 +

2.0× 600

6

(

2 +

σ 1
σ 2

)

+

2.5× 300

6

(

2 +

σ 5
σ 2

)

+

1.5× 600

6

(

2 +

σ 3
σ 2

)

thatis,


B 2 = 2 × 300 +

2.0× 600

6

(

2 +

200

150

)

+

2.5× 300

6

( 2 − 1 )+

1.5× 600

6

(

2 +

100

150

)

fromwhich


B 2 (=B 5 )=1791.7mm^2

Finally,


B 3 = 300 +

1.5× 600

6

(

2 +

σ 2
σ 3

)

+

2.0× 200

6

(

2 +

σ 4
σ 3

)

thatis,


B 3 = 300 +

1.5× 600

6

(

2 +

150

100

)

+

2.0× 200

6

( 2 − 1 )

sothat


B 3 (=B 4 )=891.7mm^2
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