Satellite Formation Flight via Thrusters and Proportional-Integral-Derivative Control Approaches

This chapter is focused to control of relative satellite vector estimations with various Kalman filter (KF) and Proportional-Integral-Derivative (PID) approaches. The identical 3U target and follower satellites orbits and initial conditions are simulated according with desired formation geometry limitations. In this study, target and follower satellites states are determined as derived simulation data. The various satellites thruster’s scenario is analyzed with various relative state estimation which use Kalman filters. The novel methods, which satellites and relative orbit estimation are determined via two stages, are inputted to the control section of follower satellites within formation flight of satellites architecture.