Abstract: Attitude control/momentum management (ACMM) aims to balance the disturbance through active attitude adjustment, which can significantly reduce the fuel consumption for control moment gyro (CMG) momentum desaturation. The adaptive momentum management controller based on parameter identification developed in this paper consists of an online identification loop and a feedback linearization loop. In the feedback linearization loop, the ACMM system is transformed into an equivalent linear system through output transformation and state transformation. Nonlinear control laws for the original system are obtained through the design of the linear controller . The online identification loop identifies the system moment of inertia based on the closed loop control information, which provides feedback linearization with enough robustness to parameter variations of the system. Simulation results based on the space station module transfer operation demonstrate excellent performance even when the deviation between the torque equilibrium attitude (TEA) and the local vertical local horizontal orientation is significant.

Key words: attitude control/momentum management, parameter identification, feedback linearization, torque equilibrium attitude