Spacecraft Attitude Stabilization using Magnetorquers with Separation between Measurement and Actuation

摘要

In actual implementations of magnetic control laws for spacecraft attitude stabilization, the time in which Earth magnetic field is measured must be separated from the time in which magnetic dipole moment is generated. In this work we present a magnetic attitude stabilization law that takes into account of the latter separation. A proportional-derivative feedback is presented, and a design method for determining its parameters is obtained. The proposed method is validated through a case study.