Central Fuselage Structural Analysis

I have a full set of dimensions, load cases, and material properties for an isolated central fuselage section and I must verify its strength and stability right away. The task covers two linked studies:

• Bending analysis – quantify stresses, strains, deflection curves, and margin of safety under the prescribed flight-level bending moments.
• Instability (buckling) analysis – determine critical load factors, identify likely buckle modes, and flag any skin-frame or stringer instability risks.

Finite-element modelling is expected; ANSYS, NASTRAN, Abaqus, or an equivalent solver is fine as long as the mesh, boundary conditions, and convergence checks are clearly explained. Hand-calcs for sanity checks are welcome.

Deliverables I need:
• Native model files plus a neutral export (e.g., .inp or .bdf)
• Post-processed stress and buckling contour plots in high resolution
• A concise PDF report covering methodology, assumptions, results, and recommendations, ready for internal review

Everything is needed ASAP, so please indicate how quickly you can turn the work around once I supply the load cases and material data.