Fuselage Design

2. Fuselage Structure
➢Given fuselage structure and determine
the ultimate bending strength.
➢ Given loads and determine the
maximum stresses applied to the
fuselage structure.
➢ Given loads and determine the shear
flow distribution.
ACE - Dr Mohamed Elfarran

3. Unsymmetrical tapered fuselage- Example
Determine the stringer stresses and forces at station 0 and station 30 due to the
given loads applied at station (150),
Neglect the skin effect.
𝑃𝑧 = 4000 𝐼𝑏, 𝑃𝑦 = 1000 𝐼𝑏, 𝑃𝑥 = 1500 𝐼𝑏.
ACE - Dr Mohamed Elfarran

4. Unsymmetric tapered fuselage- Example
Solution strategy:
Since the fuselage is unsymmetrical and under general applied loading. We
will use the general bending stresses equation
And we need to calculate the centroid position w.r.t. Z and Y axes.
ACE - Dr Mohamed Elfarran

5. Unsymmetrical tapered fuselage- Example
Section 0:
ACE - Dr Mohamed Elfarran

6. Unsymmetrical tapered fuselage- Example
Section 0:
ACE - Dr Mohamed Elfarran

7. Unsymmetrical tapered fuselage- Example
Section 0:
ACE - Dr Mohamed Elfarran

8. Unsymmetrical tapered fuselage- Example
Section 0:
ACE - Dr Mohamed Elfarran

9. Unsymmetrical tapered fuselage- Example
Section 0:
ACE - Dr Mohamed Elfarran

10. Unsymmetrical tapered fuselage- Example
Section 30:
ACE - Dr Mohamed Elfarran

11. Unsymmetrical tapered fuselage- Example
Section 30:
ACE - Dr Mohamed Elfarran

12. Unsymmetrical tapered fuselage- Example
Section 30:
ACE - Dr Mohamed Elfarran

13. Unsymmetrical tapered fuselage- Example
Section 30:
ACE - Dr Mohamed Elfarran