FIELD: determination of moment of inertia of helicopters. SUBSTANCE: proposed method includes successive measurements of amplitudes of angular oscillations of helicopter at initial static unbalance, at additional static unbalance of helicopter main rotor and at additional static unbalance which is diametrically opposite relative to axis of rotation of main rotor. For determination of moment of inertia of helicopter use is made of magnitudes of angular oscillation amplitudes in hovering mode. EFFECT: enhanced reliability of determination of moment of inertia. 1 dwg
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