Topics covered: Composite materials and Elastic structures

This assignment covers the following Learning outcome of the course:

CLO$5.$ Analyze the beam, shaft and thin plate structures.

CLO$6.$ Analyze the different parts of aircraft under loading and Airworthiness.

Question $1$

Assume the spar of the wing is of rectangular cross$-$section as given in the diagram below and is constrained like cantilever beam. $\backslash (\backslash$mathrm$\{$B$\}=\backslash$mathbf$\{50\}\backslash$mathrm$\{$mm$\},\backslash$mathrm$\{$H$\}=\backslash$mathbf$\{50\}\backslash$mathrm$\{$mm$\},\backslash$mathrm$\{$L$\}=\backslash$mathbf$\{5\}\backslash$mathrm$\{$m$\}\backslash ),$ Force $($ F $)=\backslash (\backslash$mathrm$\{$kN$\}\_\{\backslash$mathrm$\{$N$\}\}\backslash )$ y $=25$ mm $.$

a$.$ Find the bending stress and maximum deflection acting on the spar?

b$.$ Where the bending stress will be maximum, where the deflection will be maximum?

c$.$ Is the stress more than yield stress $($if the beam is made of steel$)?$

Formula for calculating $\backslash ($ I$=1/12$ B $\backslash$times H$^\{3\}\backslash ).$

Formula for calculating Bending stress $\backslash (=$M $\backslash$times y $/$ l$=$F x L x y $/$ I $\backslash )$

Formula for calculating maximum deflection $\backslash (=$F $\backslash$times L$^\{3\}/3\backslash$times E $\backslash$times I $\backslash )$

Question $2$

a$.$ Write the names of the $($two$)$ parts of the aircraft that are assumed as thin plate structures?

b$.$ What are the types of forces experienced by Stringers, Longerons, frames and spar?

c$.$ What are the types of forces acting on compressor and turbine blades?

d$.$ What are the types of fail safe and safe life structures in aircraft, list any two parts?

e$.$ What is meant by Airworthiness?