Estimation of MCMG parameters and torques for rapid slewing maneuver of agile spacecraft

The micro control moment gyro (MCMG) parameters were estimated for an agile spacecraft performing a rapid slewing maneuver to provide reference data for the MCMGs parameters in the primary design stage. The estimation algorithms for the MCMG's maximum angular rates and the output torques were based on the spacecraft dynamics during the slewing maneuver. The response of the attitude control system of a small spacecraft during slewing was simulated for MCMGs with a pyramid configuration. Simulation results show that the estimation algorithm gives reasonable results.