An apparatus comprising: A satellite; and an orbit controller configured to control stationkeeping maneuvers of the satellite, wherein the satellite comprises: a satellite bus having a nadir side configured to face the Earth and a zenith side opposite the nadir side; a north electric thruster installed toward a north region of the zenith side and oriented downward to produce thrust through a center of mass of the satellite; a south electric thruster installed toward a south region of the zenith side and oriented upward to produce thrust through the center of mass of the satellite; an east chemical thruster installed on an east side of the satellite bus; and a west chemical thruster installed on a west side of the satellite bus; characterized in that the orbit controller is configured to detect a failure of one of the electric thrusters (210, 211), and in response to the failure, to: control a burn of the remaining electric thruster (210, 211) proximate to an orbital node (412, 414); control a burn of one of the chemical thrusters (220, 221) at 90° ± 5° from the burn of the remaining electric thruster (210, 211); and control a burn of the other one of the chemical thrusters (220, 221) at 270° ± 5° from the burn of the remaining electric thruster (210, 211), wherein the east chemical thruster and the west chemical thruster are configured to produce thrust through the center of mass of the satellite. A satellite; and an orbit controller configured to control stationkeeping maneuvers of the satellite, wherein the satellite comprises: a satellite bus having a nadir side configured to face the Earth and a zenith side opposite the nadir side; a north electric thruster installed toward a north region of the zenith side and oriented downward to produce thrust through a center of mass of the satellite; a south electric thruster installed toward a south region of the zenith side and oriented upward to produce thrust through the center of mass of the satellite; an east chemical thruster installed on an east side of the satellite bus; and a west chemical thruster installed on a west side of the satellite bus; a satellite bus having a nadir side configured to face the Earth and a zenith side opposite the nadir side; a north electric thruster installed toward a north region of the zenith side and oriented downward to produce thrust through a center of mass of the satellite; a south electric thruster installed toward a south region of the zenith side and oriented upward to produce thrust through the center of mass of the satellite; an east chemical thruster installed on an east side of the satellite bus; and a west chemical thruster installed on a west side of the satellite bus; characterized in that the orbit controller is configured to detect a failure of one of the electric thrusters (210, 211), and in response to the failure, to: control a burn of the remaining electric thruster (210, 211) proximate to an orbital node (412, 414); control a burn of one of the chemical thrusters (220, 221) at 90° ± 5° from the burn of the remaining electric thruster (210, 211); and control a burn of the other one of the chemical thrusters (220, 221) at 270° ± 5° from the burn of the remaining electric thruster (210, 211), control a burn of the remaining electric thruster (210, 211) proximate to an orbital node (412, 414); control a burn of one of the chemical thrusters (220, 221) at 90° ± 5° from the burn of the remaining electric thruster (210, 211); and control a burn of the other one of the chemical thrusters (220, 221) at 270° ± 5° from the burn of the remaining electric thruster (210, 211), wherein the east chemical thruster and the west chemical thruster are configured to produce thrust through the center of mass of the satellite.