Analysis of the dynamic performance of the pointing and attitude control subsystem of the resilient spacecraft with power gyroscopic unit on the basis of GD 02-150 gyrodyne

The actual issues of the analysis of the dynamic performance of pointing and attitude control subsystem including elasticity of spacecraft construction units are considered. Investigations of the resonant elastic vibrations of elastic spacecraft construction units, such as solar array panels and communication payload antennas excited by perturbing moments of power gyroscopic unit on the basis of ГД 02-150 gyrodyne when required control moment is being formed, are conducted. The analysis of zero-input response of elastic spacecraft with continuous gyro gimbal speed setting, zero-input response dynamic performance of elastic spacecraft when the gyrodyne moments are applied and elastic vibrations errors caused by power gyroscopic unit operation in the subsystem control loop are, are carried out. The assessment of the attitude dynamic error between the connected and the given coordinate systems, and antenna angular deviations from its nominal position caused by the elastic vibrations, is given. Recommendations how to eliminate resonance elastic vibrations of elastic spacecraft construction units are developed basing on the results of the performed investigations.