Introduction to Aircraft Structural Analysis (Elsevier Aerospace Engineering)

134 CHAPTER 5 Energy Methods

Fig.5.16

Determination of bending moment distribution in a shear- and direct-loaded ring.

whichgives

M=MA+NAR( 1 −cosθ)+

PR

π

(

1 −cosθ−

1

2

θsinθ

)

(iv)

Hence,

∂M

∂MA

= 1

∂M

∂NA

=R( 1 −cosθ) (v)