ME4212 Aircraft Structures
Fig. 1 shows the structural layout of the wing of a small aircraft. The structure consists of a front and rear spar with spanwise stringers. You may assume the leading edge cell ahead of the front spar and the structures behind the rear spar are ineffective in carrying stresses; hence the structure is a one-cell beam with multiple stringers. A vertical load 𝑉௭ = 18.0 × 10ଷ
lb. is applied to Stringer 4 at Station 190, as indicated by the red arrow in Fig. 1.
Fig. 2 shows the cross-section at Station 20, with information on the dimensions of the 14 flanges or stringers. The reference axes are labeled X’ and Z’, while the centroidal axes are labeled X and Z. Table 1 shows the positions of the stringers.
Determine the maximum bending stress and shear stress at Station 20. State all assumptions and your answers in metric units
