It makes full use of the information of single satellite s position and velocity in ECI(earth center inertial frame),and is not necessary to install new sensors to measure the relative attitude.

This thesis mainly studies on the dynamics and control issues of relative attitude in formation flying, aiming to provide some useful theoretical reference for the practical applications of satellite formation flying.

Active disturbance rejection controller design for spacecraft attitude maneuver;

Control of flexible satellite attitude maneuver using pulse modulated input shaper;

Active vibration suppression of flexible spacecraft integrating piezoceramics with pseudo rate modulated thrusters during attitude maneuvers;

Measurement device design of off-plane pose of plane suspender;