Prediction of Rotor Loads from Fuselage Sensors for Improved Structural Modeling and Fatigue Life Calculation

Phase I addressed the technological gap in the predictive capabilities of CFD/FSI in the context of hybrid loads/sensor models used in an aircraft’s fatigue life tracking program for critical fuselage and dynamic components across the full flight regime. It demonstrated these technology advancements: (1) a combined rotor, fuselage aeroelastic model; (2) empirical rotor hub loads prediction from fuselage sensors; (3) innovative whole aircraft CFD/FSI/IMGA methods; (4) rotor hub loads to blade loads predictions; and (5) a strategy for required fuselage-based instrumentation. Phase II will improve the full aircraft structural dynamics model, including tail rotor, all dominant excitation modes, as well as component mode synthesis for enhanced modal super-elements for the fuselage and fatigue-critical main rotor hub component models, expand the aerodynamics model for full aircraft CFD/FSI/IMGA with performance optimized for use in a structural fatigue life tracking program, perform loads prediction validation for all flight regimes, and quantify this load prediction methodology via structural fatigue analysis for select rotor components. The fuselage sensors will be validated. These efforts will provide a solid platform for implementation in a US Navy structural fatigue life tracking program, and ultimately leading to enhanced safety and cost optimization due to improved, measurement-based rotorcraft loads prediction.