Spacecraft Attitude Stabilization Using Magnetorquers with Separation Between Measurement and Actuation

摘要

In this work, a magnetic control law for spacecraft attitude stabilization has been presented; the control law possesses the important feature of separating measurement time from actuation time. A design method for the parameters of the controller has been obtained, and it has been applied to a case study. The proposed method leads to a systematic approach for choosing the length of the actuation interval.