Influence of Gyroscopic Damping Systems on Aeroelastic Oscillations of a Large Aircraft

The impact of gyroscopic damping systems on the aeroelastic and strength characteristics of a large aircraft was assessed via a mathematical model of the aircraft aeroelasticity that takes into account the fuel mobility in the wing fuel tanks. It is shown that the gyroscopic damping system designed after the diagram of a high-speed gyroscope provides attenuation of oscillations of the engines installed on elastic pylons beneath the wing and allows us to eliminate the local aeroelastic instability caused by the interaction of torsional oscillations of the wing and motor elastic tones. The gyroscopic damping system designed after the diagram of a spring pendulum provides a reduction in the level of loads on the wing in the area of the first bending tone which makes the main contribution to the total fatigue damage to the upper wing panel when moving on the ground. The calculation results for the IL-76, Tu-204 aircraft are presented.