Attitude Decoupling Control Method for Large Inertial Product Triaxial Stabilized Satellites
摘要
To solve the problem of strong coupling nonlinearity in attitude control of large inertial product satellites, a decoupling control method based on state feedback is proposed. Based on the mass characteristics of the satellite, the system dynamics model is simplified, and the triaxial coupling term caused by orbital angular velocity and inertial product is compensated to realized the three-axis attitude decoupling control of large inertial product satellites. The simulation results show that the method can realize the fast attitude convergence of the large inertia product satellite and has a good control effect.