Results of simulation of main rotor blade loads and deformations, which can be generated during boundary states
of helicopter flight, are presented. Concerned cases of flight envelope include hover at maximum height, level flight at
high velocity, pull-up manoeuvres applying cyclic pitch and mixed collective and cyclic control. The simulation
calculations were executed for data of light helicopter with three-bladed articulated rotor. For analysis, the real
blades are treated as elastic axes with distributed masses of blade segments. The model of deformable blade allows
for out-of-plane bending, in plane bending, and torsion. For assumed flight state of helicopter, the equations of rotor
blades motion are solved applying Runge-Kutta method. According to Galerkin method, for each concerned azimuthal
position of blade the parameters of its motions are assumed as a combination of considered bending and torsion eigen
modes of the blade. The loads of rotor blades generated during flight depend due to velocity of flight, helicopter mass,
position of rotor axis in air and deflections of swashplate that correspond to collective and cyclic pitch angle applied
to rotor blades. The results of simulations presenting rotor loads and blade deformations are shown in form of timeruns and as plots of rotor-disk distributions. The simulations of helicopter flight states may be useful for prediction the
conditions of flight-tests without exceeding safety boundaries or may help to define limitations for manoeuvre and
control of helicopter.
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