Satellite Attitude Control and Power Tracking with Energy/Momentum Wheels

A control law for an Integrated Power/Attitude Control System (IPACS) for a satellite is presented in this paper. Four or more energy/momentum wheels in an arbitrary non-coplanar configuration and a set of three thrusters are used to implement the torque inputs. The energy/momentum wheels are used as attitude control actuators, as well as an energy storage mechanism, providing power to the spacecraft. In that respect, they can replace the currently used heavy chemical batteries. The thrusters are used to implement the torques for large and fast (slew) maneuvers during the attitude initialization and target acquisition phases and to implement the momentum management strategies. The energy/momentum wheels are used to provide the reference-tracking torques and the torques for spinning up or down the wheels for storing and releasing kinetic energy. The controller published in a previous work by the authors is adopted here for the attitude tracking function of the wheels. Power tracking for charging and discharging the wheels is added to complete the IPACS framework. The torques applied by the energy/momentum wheels are decomposed into two spaces which are orthogonal to each other, with the attitude control torques and power tracking torques in each space. This control law can be easily incorporated in an IPACS system on-board a satellite. The possibility of occurrence of singularities, where no arbitrary energy profile can be tracked, is studied for a generic wheel cluster configuration. A standard momentum management scheme is considered to null the total angular momentum of the wheels so as to minimize the gyroscopic effects and prevent the singularity from occurring. A numerical example for a satellite in a low Earth near-polar orbit is provided to test the proposed IPACS algorithm. The satellite’s boresight axis is required to track a ground station, while the satellite is required to rotate about its boresight axis so that the solar panel axis is perpendicular to the satellite-Sun vector.