Introduction to Aircraft Structural Analysis (Elsevier Aerospace Engineering)

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444 CHAPTER 15 Bending of Open and Closed, Thin-Walled Beams


whereC 1 isaconstantofintegrationwhichisobtainedfromtheboundaryconditionthatv′=0atthe
built-inendwherez=0.Hence,C 1 =0and


EIv′=−W

(

Lz−

z^2
2

)

(iii)

IntegratingEq.(iii),weobtain


EIv=−W

(

Lz^2
2


z^3
6

)

+C 2

inwhichC 2 isagainaconstantofintegration.Atthebuilt-inendv=0whenz=0sothatC 2 =0.Hence,
theequationofthedeflectioncurveofthecantileveris


v=−

W

6 EI

( 3 Lz^2 −z^3 ) (iv)

Thedeflection,vtip,atthefreeendisobtainedbysettingz=LinEq.(iv).Then


vtip=−

WL^3

3 EI

(v)

andisclearlynegativeanddownward.


Example 15.6
DeterminethedeflectioncurveandthedeflectionofthefreeendofthecantilevershowninFig.15.17(a).
Thecantileverhasadoublysymmetricalcrosssection.


Fig.15.17


Deflection of a cantilever beam carrying a uniformly distributed load.

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