How is the aircraft loads analysis process structured?

Loads analysis determines design loads for structural sizing. Process: Flight conditions - Define load cases (maneuvers, gusts, ground loads) per FAR 25.301-459; Aerodynamic modeling - Panel methods, CFD for pressure distribution, unsteady effects for dynamic loads; Structural dynamics - Finite element model for stiffness, inertia, coupled aero-structure (aeroelasticity); Loads calculation - Static maneuvers (n-z envelope), dynamic gusts (discrete and continuous turbulence), ground loads (landing, taxi, turning). Load cases: Thousands of combinations (speed, altitude, weight, CG, configuration, maneuver type); Critical load envelopes identify design cases. Outputs: Shears, moments, torques at wing stations, Interface loads (engine, gear), and Internal loads for structural sizing. Certification: Analysis methods approved, flight test validates representative cases. Loads model iteration: Design changes require loads recalculation; affects weight and subsequent loads. Final loads freeze after extensive iteration.