Modeling and Analysis of the Attitude Control System for Micro-Spacecraft

For the purpose of spacecraft miniaturization,a novel flywheel scheme using only two flywheels to control spacecraft attitude is presented.Moreover,this scheme can manage energy which is stored in flywheels with high rotary speeds.That no saturated-speed uninstalled devices such as magnetic moment apparatus are needed reduces the structure of the flywheel attitude control system.This paper describes the structure and principle of the system in detail,and deduces nonlinear dynamic model of the attitude control system.After analyzing the primary factor of influencing performance of attitude maneuver,this scheme is validated by model simulation.