Theoretical and experimental developments in the aeroelastic and aeromechanical stability of helicopters and tilt-rotor aircraft are addressed. Included are the underlying nonlinear structural mechanics of slender rotating beams, necessary for accurate modeling of elastic cantilever rotor blades, and the development of dynamic inflow, an unsteady aerodynamic theory for low-frequency aeroelastic stability applications. Analytical treatment of isolated rotor stability in hover and forward flight, coupled rotor-fuselage stability in hover and forward flight, and analysis of tilt-rotor dynamic stability are considered. Results of parametric investigations of system behavior are presented, and correlation between theoretical results and experimental data from small and large scale wind tunnel and flight testing are discussed.
Rotorcraft Aeroelastic Stability
1988
177 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aircraft , Aeroelasticity , Helicopter design , Rotor aerodynamics , Computational fluid dynamics , Dynamic structural analysis , Mathematical models , Tilt rotor aircraft , Dynamic stability , Finite element method , Flow distribution , Prediction analysis techniques , Rotor blades (Turbomachinery) , Rotor body interactions , Solid mechanics
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