Preliminary Study on Satellite Formation Flying Control
Around L2Using Solar Sail Propulsion
› Triwanto Simanjuntakõ Yuichi Tsudaö
Mutsuko Y. Morimotoö Junichiro Kawaguchiõö
Sawada Hirotakaö
õDepartment of Aeronautics and Astronautics, University of Tokyo,
7-3-1 Hongo, Bunkyo-ku, Tokyo 113-8656, JAPAN
öInstitute of Space and Astronautical Science/JAXA
3-1-1 Yoshinodai, Sagamihara, Kanagawa 229-8510, JAPAN
Here at L2, introduced a satellite formation flying consists of two satellites powered by solar sail, the
Mirror Spacecraft (MSC) and the Detector Spacecraft (DSC). The two satellites are separated such that
the operational detector is at the focus of the mirror. Due to the instability of the collinear Lagrangian
points, the desired distance between the two satellites need to be maintained. This paper addresses the
control design scheme for formation keeping control. The equation of motion is derived in Hill's frame
and inertial frame and then control law formulated mathematically. Halo and Lissajous orbit are
considered as options for reference orbit.
Key Words: Formation Flying Control, Lagrangian Libration Point, Solar Sail Propulsion, Restricted
Three Body Problem