TECHNICAL DATA ANALYSIS, INC. — Department of Defense STTR Phase I: N17A-T009

Description

For rotorcraft, accurate loads prediction is required across the full flight regime, including turbulent flow, blade-vortex interaction, as well as interactions with the fuselage and tail rotor. Predictive capabilities of modern computational fluid dynamics coupled with computational structural dynamics software must be addressed in the context of technology integration into a real aircrafts fatigue life tracking program, requiring both incorporation of fatigue damage initiation and propagation models for critical fuselage and dynamic components as well as demonstration of performance robust enough to ultimately support near real-time lifing assessments. New technology advances are required. Innovative coupled main rotor-fuselage/tail rotor models must be developed, taking into account direct load measurement for closed-loop feedback used for loads prediction improvements. The methods employed in computational loads analysis must mature. Recent advances in geometry modeling and mesh generation, computational fluid/structural mechanics, coupled multi-physics models, and high-performance computing create a unique opportunity for the development of the next generation of predictive simulation methods and tools for modern rotorcraft, with significantly improved representation of complex geometry and multi-physics phenomena. This effort will produce a comprehensive, physics-based model of a combined main rotor, tail rotor, and fuselage used for rotor loads prediction based on measured fuselage responses.