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eng.fuselage-hoop-stress-pressure Calculator
Calculates fuselage hoop stress from cabin pressure differential and fuselage diameter using thin-wall pressure vessel theory. Aircraft fuselages are cyclic pressure vessels — each pressurisation cycle contributes to fatigue damage, motivating the fail-safe and damage tolerance design approaches.
Inputs
P Psi
Force per unit area (Pa). Atmospheric pressure at sea level: 101,325 Pa. Check whether gauge or absolute pressure is required.
R M
Distance from centre to edge of a circle. Radius = diameter / 2.
T Mm
Perpendicular measurement through the material. For insulation: thicker is better. For beams: directly affects bending resistance.
Sigma Ult Mpa
Reference formula or conversion factor shown for context.
Results
hoop stress σ_θ (MPa)
Internal force per unit area (Pa or MPa). Must stay below yield strength in service. Beyond yield: permanent deformation. Beyond tensile strength: fracture.
axial stress σ_x (MPa)
Internal force per unit area (Pa or MPa). Must stay below yield strength in service. Beyond yield: permanent deformation. Beyond tensile strength: fracture.
factor of safety (hoop)
Strength / applied load. A safety factor of 2.0 means the structure can handle twice the design load before failure. Buildings: 1.5–3. Lifting equipment: 4–6.
σ_hoop = p·R/t
Reference formula or conversion factor shown for context.
σ_axial = p·R/(2t)
Reference formula or conversion factor shown for context.