Trajectory-Planning Attitude Control System for Satellites with Magnetic Attitude Control and One Reaction Wheel

Abstract

Selecting attitude actuators for spacecraft in low earth orbit (LEO) often involves a trade between reaction wheels and magnetorquers. Reaction wheels generally have higher size, weight and power as well as cost, compared with magnetorquers, but have performance advantages. We consider a hybrid system relying on a single reaction wheel and three magnetorquers, using a trajectory planning control method that focuses on meeting pointing goals and minimizing the need to desaturate the reaction wheel. The use of planning allows for intelligent use of the reaction wheel and accommodates time-changing goals and orbit-varying magnetic fields. Preliminary results show trajectories with fractional-degree-accuracy, as well as management of reaction wheel momentum and avoidance of stiction. We also compare to a magnetorquer-only planning-based control system and show better convergence and faster slews.

arXiv comment19 pages, 26 figures in 14 groups, AAS/AIAA Astrodynamics Specialist Conference