Relative Status Determination for Spacecraft Relative Motion Based on Dual Quaternion

Abstract

For the two-satellite formation, the relative motion and attitude determination algorithm is a key component that affects the flight quality and mission efficiency. The relative status determination algorithm is proposed based on the Extended Kalman Filter (EKF) and the system state optimal estimate linearization. Aiming at the relative motion of the spacecraft formation navigation problem, the spacecraft relative kinematics and dynamics model are derived from the dual quaternion in the algorithm. Then taking advantage of EKF technique, combining with the dual quaternion integrated dynamic models, considering the navigation algorithm using the fusion measurement by the gyroscope and star sensors, the relative status determination algorithm is designed. At last the simulation is done to verify the feasibility of the algorithm. The simulation results show that the EKF algorithm has faster convergence speed and higher accuracy.

Vision-Based Relative Navigation Using Dual Quaternion for Spacecraft Proximity Operations

“…In relative navigation, estimation techniques using extended Kalman filter (EKF) have been intensively studied. Many of those approaches employ dual inertia operator to estimate angular and linear velocity under the assumption of known mass moment of inertia information of spacecraft [12,13]. Dual quaternionbased relative navigation-applied extended Kalman filter (EKF) is introduced in asteroid circumnavigation considering gravity field and integrated navigation sensor system [14].…”