In this paper, an adaptive, output feedback control design methodology is presented for a multiple spacecraft formation flying (MSFF) system. A Lagrangian derivation of the MSFF model is considered to produce position dynamics for follower spacecraft #n relative to follower spacecraft #(n - 1), assuming that the leader spacecraft in the formation follows a no-thrust, natural, elliptical orbit. Next, a control law is designed to provide a filtered velocity measurement and a desired adaptive compensation with semi-global, asymptotic, relative position tracking. The proposed control law is simulated for the case of two and three spacecraft and is shown to yield semi-global, asymptotic tracking of the relative position errors.
ASJC Scopus subject areas
- Electrical and Electronic Engineering