Modeling of Attitude Control Actuator for a Flexible Spacecraft Using an Extended Simulation Environment

Abstract

The effects of the reaction wheel as control actuator in multi-axis attitude maneuver of a flexible spacecraft is considered. Four reaction wheels in an inclined configuration are used for reorienting a flexible spacecraft. In modeling of the actuator, friction, inertia and electrical subsystems are considered. An efficient approach in modeling the mechanical and electrical subsystems of the spacecraft is presented. Modeling of the spacecraft with two flexible sub-structures attached to a rigid central hub, and attitude control actuators is performed using an extended simulation environment of softwares. This approach provides facilities in modeling and evaluation the control problem of complicate electro-mechanical systems such as flexible spacecrafts in attitude maneuver. Numerical simulations show the effects of subsystems and verify the effectiveness of the proposed method.