It is suggested by the Engineering Manager to modify the construction of the fuselage from a single material to two interfacing materials with the outer skin being aluminium 7075 and the inner being high strength steel. In order to simplify the experiment, we will assume that the fuselage is not closed at the ends (can be treated as open cylinder). Both the steel and the aluminium tubes are just touching prior to exposing them to cruising altitude pressure of 83 kN/m2 and a temperature reduction of 50C. Calculate the resulting stresses in the fuselage, shown in the figure, as a result of the cabin differential pressure and temperature at a simulated high altitude of 1 kilometer. Ignoring the effect of the cabin differential pressure, calculate the thermal stresses in the fuselage, If the compound cylinder is subjected to a high altitude temperature reduction of 50C. Determine the minimum radial gap between the steel and the aluminium cylinders that is needed to avoid the exchange of stress between them as a result of the altitude pressure and reduction in temperature. You may use the material properties provided in the table below and assume that the coefficient of linear