Abstract In this paper, formation flying between a chief spacecraft moving in an elliptic orbit and a deputy spacecraft is studied. First, by using a state transition matrix (STM) of the Tschauner-Hempel equations, which describe the relative motion between the chief and deputy spacecraft, two formation trajectories that suppress relative distance variations are obtained. These trajectories are extensions of an along-track formation and a general circular orbit wherein the chief spacecraft moves in a circular orbit. The effects of the J 2 perturbation on the trajectories are considered in the initial conditions. Further, the solution of the formation reconfiguration that minimizes the L 2-norm of the deputy control forces is derived. A control law that realizes the reconfiguration trajectory by using a finite number of impulses is also derived. Finally, numerical examples of the construction of the formation trajectories are shown.
Spacecraft Formation Design and Control in Keplerian Elliptic Orbits
The Journal of the Astronautical Sciences ; 58 , 2 ; 195-220
2011-04-01
26 pages
Article (Journal)
Electronic Resource
English
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