Hardware-in-the-loop simulations of GPS-based navigation and control for satellite formation flying

Details Hardware-in-the-loop simulations of GPS-based navigation and control for satellite formation flying Hardware-in-the-loop simulations of GPS-based navigation and control for satellite formation flying

Dec 2010

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2010adspr..46.1451p&link_type=abstract

Advances in Space Research, Volume 46, Issue 11, p. 1451-1465.

Computer Science

Performance

Scientific paper

A 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 0.07 m can be achieved for position accuracy. The targeted leader-follower formation flying in the along-track separation of 100 m was maintained with a mean position error of approximately 0.2 m and a standard deviation of 0.9 m. The simulation results show that the HIL testbed is capable of successful demonstration of the GPS-based satellite autonomous formation flying mission.

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