As illustrated in the figure below, the $\backslash (\backslash$mathrm$\{$O$\}-2\backslash )$ wing is modeled as a beam with a pin support at location A and a diagonal strut supporting the beam at location B$.$ Under cruising conditions, the lift acting on the wing is idealized as a uniform distributed load from location A to the strut at location B and then a linearly distributed load from location $\backslash ($ B $\backslash )$ to the wingtip.

The distributed load and dimensions are given as:

$\backslash [$

$\backslash$begin$\{$array$\}\{$l$\}$

$\backslash$mathrm$\{$w$\}=200\backslash$mathrm$\{$lbs$\}/\backslash$mathrm$\{$ft$\}\backslash \backslash$

$\backslash$mathrm$\{$a$\}=3\mathrm{.}4\backslash$mathrm$\{$ft$\}\backslash$quad $\backslash$mathrm$\{$~b$\}=13\mathrm{.}5\backslash$mathrm$\{$ft$\}$

$\backslash$end$\{$array$\}$

$\backslash ]$

Answers:

Based on the given dimensions and distributed load, determine the maximum internal loads on the beam and the location of each maximum load $($as measured from location A$).$

Note: Assume that the wing is horizontal with lift distribution $($i$.$e$.$ perpendicular to the aircraft centreline$),$ thereby disregarding the dihedral $($i$.$e$.$ angle$)$ of the wing.