49 巻 (2001) 575 号 p. 438-440
The potential-function guidance is applied to the autonomous formation-keeping of the eccentricity separation in the co-located many-satellite system. The acceleration resulting from the continuous and throttled thrust is formulated as a function of positions and velocities of all satellites. If these state variables are measured by on-board sensors, the maneuvering schedule can be computed in the respective satellites. A numerical simulation affirms the validity of the control.