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Blade and Hub Loads of Ballistically Damaged Helicopter Rotors

Ki C. Kim

Abstract

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 large 1/rev vibratory component on the rotor hub.

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Key concepts: Blade element theory, Blade element momentum theory, Structural engineering, Helicopter rotor, Aeroelasticity, Aerodynamics, Finite element method, Rotor (electric)