Abstract
Tilt-rotor aircraft performance in hover and forward flight modes is optimized using the stiffnesses of the rotor blade as design variables. The performance in both flight modes is maximized simultaneously using a combined objective function. Aeroelastic analysis is based on mixed variational formulation for dynamics of moving beams along with finite-state dynamic inflow theory. Stiffnesses of an extension-torsion coupled and a fully coupled box beam are chosen as design parameters. Constraints are imposed on non-rotating natural frequencies of the beam, angle of attack and material failure. Based on the optimized stiffnesses, different composite materials for the rotor are studied to obtain a maximum performance in both flight regimes. Results show that significant improvements in the tilt-rotor performance are possible using optimally stiffened beam. The key stiffnesses affecting the performance of the rotor are identified.
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