Finite-time Velocity-free Attitude-orbit Integrated Tracking Control for Rigid Spacecraft

In this paper, an attitude-orbit integrated controller is designed for rigid spacecraft without velocity and angular velocity measurement. First, based on dual quaternion description, the integrated attitude-orbit kinematics and dynamics model for rigid spacecraft is presented. On this basis, an attitude-orbit integrated output feedback control strategy is developed in the absence of velocity information, and the finite-time convergence of the control system is analyzed. Finally, the numerical simulation is given to verify the effectiveness and feasibility of the proposed velocity-free control strategy.