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METHOD OF COMPUTATIONS OF LOADS AT THE DESIGN OF ROTOR UNITS AND HELICOPTER CONTROL SYSTEM

Volumen 46, Ausgabe 6, 2015, pp. 577-590
DOI: 10.1615/TsAGISciJ.v46.i6.50
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ABSTRAKT

A method allowing determination of the following parameters is developed, namely, aerodynamic rotor characteristics (thrust, longitudinal and transversal forces, torque at axle), the collective pitch angle to obtain the specified rotor thrust; the angles of cyclic pitch required to create the helicopter balance moments on the bush; the angle of attack of the helicopter rotor needed for specified speed flight; blade deformations in the flap plane, in the rotation plane; torsion deformations and corresponding to these deformations bending and hinge moments and their harmonic composition. The results of the computations of the hinge moments are presented. This method is developed for a rotor with blades elastic in the planes of thrust, rotation, and torsion, for hinge and rigid attaching of the blades in the base, and also for complex structures of the bush of modern semi-rigid and rigid rotors with elastic elements, control cases, and elastomeric hydraulic dampers and tips with the sweep and with deflection downward.

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