펄스형태 추력기 입력을 이용한 인공위성 자세제어

Abstract

Satellite attitude control by multiple pulse type thruster inputs is addressed in this study. Fixed pulse width thruster input may by used for ground commanding of spacecraft in case of an anomalous situation. The design parameters in that case include pulse width and pulse period which need to be adjusted to satisfy terminal constraints usually expressed in the form of final attitudes. Designed control strategy is applied to three-axis attitude maneuver based upon nonlinear rotational dynamic equations of motion. The proposed control technique provides potential applications for mission operation of spacecraft by manual thruster firings.