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Abstract
In this work, fully-resolved rotor-fuselage interactional aerodynamics is used as the forcing term in a model based on the Euler-Bernoulli equation, aiming to simulate helicopter tail-boom vibration. The model is based on linear beam analysis and captures the effect of the blade-passing as well as the effect of the changing force direction on the boom. The Computational Fluid Dynamics (CFD) results were obtained using a well-validated helicopter simulation tool. Results for the tail-boom vibration are not validated due to lack of experimental data, but were obtained using an established analytical approach and serve to demonstrate the strong effect of aerodynamics on tail-boom aeroelastic behavior.
Highlights
Interactional effects between the main rotor and the fuselage are commonplace in rotorcraft.In particular, at low advance ratios of the main rotor, its wake can interact with the main fuselage and the empennage
In contrast to earlier works [3] where the rotor aerodynamics is represented by blade-element methods, Computational Fluid Dynamics (CFD)
CFD modeling was used to compute the unsteady flow around the main rotor-fuselage, and the aerodynamic loads were used in conjunction with the analytical structural model, based on the Euler-Bernoulli equation with one spatial coordinate
Summary
Interactional effects between the main rotor and the fuselage are commonplace in rotorcraft. Amongst the current research reports there is little information on the effect of these aerodynamic interactions on the vibration and deformation of the tail-boom structure. The Euler-Bernoulli equation for various end conditions allows for analytical or approximate solution of the natural and forced vibrations of uniform and non-uniform beams [4,5,6,7,8,9]. In [11], maintaining the non-dimensional amplitude of the forces against several lifting conditions were analyzed with the FEM approach These works did not proceed to compute the effects of wake aerodynamics on the tail boom. The forced vibrations are computed using an approximation of the tail boom load obtained from CFD calculation of rotor-fuselage configuration. The aerodynamic predictions of the helicopter fuselage aerodynamics are validated against wind tunnel tests
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