Abstract: A new method to realize the relative navigation and identification of inertia parameters based on stereo vision is proposed to address the measurement and perception of a non cooperative spacecraft in an on orbit serving mission. The features points recognized by stereo vision are used to define a geometric coordinate system, based on which the filters for attitude measurement and relative navigation are designed to estimate the attitude, angular velocity, ratio of inertia, orbit and center of mass of the target. The mass and moment of inertia are then identified based on the difference of the ratio of inertia and position of center of mass of the target estimated through the relative navigation method before and after the combination with an adhesive satellite. The validity of the proposed method is verified through numerical simulation.

Key words: Non cooperative spacecraft, Stereo vision, Attitude measurement, Relative navigation, Parameter identification