AbstractA relative navigation and formation control algorithm for satellite formation flying was developed, and a hardware-in-the-loop (HIL) simulation testbed was established and configured to evaluate this algorithm. The algorithm presented is a relative navigation estimation algorithm using double-difference carrier-phase and single-difference code measurements based on the extended Kalman filter (EKF). In addition, a state-dependent Riccati equation (SDRE) technique is utilized as a nonlinear controller for the formation control problem. The state-dependent coefficient (SDC) form is formulated to include nonlinearities in the relative dynamics. To evaluate the relative navigation and control algorithms developed, a closed-loop HIL testbed is configured. To demonstrate the performance of the testbed, a test formation flying scenario comprising formation acquisition and keeping in a low earth orbit (LEO) has been established. The relative navigation results from the closed-loop simulations show that a 3D RMS of 0.07m can be achieved for position accuracy. The targeted leader–follower formation flying in the along-track separation of 100m was maintained with a mean position error of approximately 0.2m and a standard deviation of 0.9m. The simulation results show that the HIL testbed is capable of successful demonstration of the GPS-based satellite autonomous formation flying mission.
Hardware-in-the-loop simulations of GPS-based navigation and control for satellite formation flying
Advances in Space Research ; 46 , 11 ; 1451-1465
2010-08-06
15 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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