The effects of (simulated) ballistic damage on helicopter rotor blade response and rotor hub loads are investigated. A finite element formulation based on Hamilton's principle is used for structural analysis, and aerodynamic loads are calculated using quasisteady aerodynamic theory. Each blade is as being composed of elastic beams undergoing flap bending, lag bending, elastic twist, and axial deflections. Dynamic responses of multi-blade rotor systems are calculated from nonlinear periodic normal mode equations using a finite element in time scheme. Results are calculated for the SA349/2 Gazelle helicopter for both undamaged and damaged blade configurations. Blade damage effects are determined in terms of blade mode shapes and frequencies, aeroelastic response, and rotor hub loads. Blade dissimilarity due to ballistic damage can induce a luge 1/rev vibratory component on the rotor hub. Helicopters, Rotor blades, Hub loads, Aerodynamics, Helicopter aeroelasticity, Coupled trim solution.
Blade and Hub Loads of Ballistically Damaged Helicopter Rotors
1993
44 pages
Report
Keine Angabe
Englisch
Aircraft , Aerodynamics , Aerodynamic characteristics , Helicopter rotors , Rotor blades(Rotary wings) , Aeroelasticity , Ballistics , Bending , Configurations , Damage , Deflection , Dynamics , Equations , Formulations , Frequency , Helicopters , Hubs , Response , Shape , Structural analysis , Theory , Time
DRIVETRAIN INFLUENCE ON THE BLADE LOADS OF HINGELESS HELICOPTER ROTORS
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