Feedback Control Law Design for the Dual-Spin Turn of Spacecraft

Abstract

A new feedback control law design for the dual-spin turn maneuver of spinning spacecraft is discussed. The control law design study is motivated by stability analysis of dual-spin spacecraft. The feedback control law is based on the relationship between nutational stability and system energy associated with the rotational motion of spacecraft and a momentum wheel. The applied torque to the momentum wheel is adjusted in a feedback control form, for which the control law is expressed as a function of spacecraft angular velocity components, as well as the momentum wheel speed. Furthermore, a two-stage control strategy, which consists of conventional open-loop maneuver and a new feedback technique, is developed. The new strategy is verie ed by simulation study using Koreasat mass property data.