  This paper proposes a solution for multiple-impulse orbital maneuvers near
circular orbits for special cases where orbital observations are not globally
available and the spacecraft is being observed through a limited window from a
ground or a space-based station. The current study is particularly useful for
small private launching companies with limited access to global observations
around the Earth and/or for orbital maneuvers around other planets for which
the orbital observations are limited to the in situ equipment. An appropriate
cost function is introduced for the sake of minimizing the total
control/impulse effort as well as the orbital uncertainty. It is subsequently
proved that for a circle-to-circle maneuver, the optimization problem is
quasi-convex with respect to the design variables. For near circular
trajectories the same cost function is minimized via a gradient based
optimization algorithm in order to provide a sub-optimal solution that is
efficient both with respect to energy effort and orbital uncertainty. As a
relevant case study, a four-impulse orbital maneuver between circular orbits
under Mars gravitation is simulated and analyzed to demonstrate the
effectiveness of the proposed algorithm.
