A Docking Maneuver Scenario of a Servicing Satellite—Quaternion-Based Dynamics and Control Design

Abstract

The paper presents a quaternion-based dynamics formulation for a servicing satellite approaching a client satellite. For understanding the dynamics behavior of the satellite, the orbit dynamics is presented in the paper with focus on the integration error for on-orbit dynamics. The mission scenario presented in the paper is applicable for geostationary satellite servicing missions or conceptual missions for a satellite of a modular structure, which allows changing components, for example a broken sensor. Quaternion-based dynamics is used to omit problems with Euler angle functions singularity during approaching maneuvers to a target satellite. Investigation in space flight dynamics and control is an active research area due to their practical and financial significance. Docking to well-known objects with defined and cooperative interfaces is known and proved, for example docking to International Space Stations. New areas of investigation are the non-cooperative objects approaching and interception, like space debris, broken satellites, or prolongation of satellite operational functions. The quaternion-based dynamics model presented in the paper describes functionality of all effectors, which allow orientation of the satellite on its orbit. The orbit dynamics accompanying attitude dynamics form a complete model for a satellite control design.