Abstract: An example spacecraft includes a first arm having a first end pivotably coupled to the spacecraft and a second end. The example spacecraft includes a first thruster rotatably coupled to the second end of the first arm. The first arm extends from the first pivot point along a first edge of an anti-nadir face of the spacecraft when the first arm is in a stowed position. The first arm is configured to pivot between the stowed position, a first extended position in which the first arm extends outward from the spacecraft relative to the first edge, and a second extended position in which the first arm extends along a third edge of the anti-nadir face and the first thruster is disposed outward of a second edge of the anti-nadir face opposite the first edge.

Abstract: Apparatus and methods for stationkeeping in a satellite. The satellite includes a north electric thruster and a south electric installed on a zenith side, an east chemical thruster installed on an east side, and a west chemical thruster installed on a west side. An orbit controller detects a failure of one of the electric thrusters. In response to the failure, the orbit controller controls a burn of the remaining electric thruster proximate to an orbital node. The orbit controller controls a burn of one of the chemical thrusters at 90°±5° from the burn of the remaining electric thruster, and controls a burn of the other one of the chemical thrusters at 270°±5° from the burn of the remaining electric thruster.

Abstract: Systems and methods for satellite orbit and momentum control are disclosed herein. An example spacecraft includes a first arm having a first end pivotably coupled to the spacecraft and a second end. The example spacecraft includes a first thruster rotatably coupled to the second end of the first arm. The first arm is to selectively pivot about the spacecraft to position the first thruster to generate a change in velocity of the spacecraft to maintain the spacecraft within an orbit station.

Abstract: Apparatus and methods for stationkeeping in a satellite. The satellite includes a north electric thruster and a south electric installed on a zenith side. An orbit controller selects a duration of a burn of the north electric thruster proximate to an ascending node that differs from a duration of a burn of the south electric thruster proximate to a descending node. The orbit controller is configured to select an offset of the burn of the north electric thruster in relation to the ascending node that differs from an offset of the burn of the south electric thruster in relation to the descending node.

Abstract: Apparatus and methods for stationkeeping in a satellite. The satellite includes a north electric thruster and a south electric installed on a zenith side. An orbit controller selects a duration of a burn of the north electric thruster proximate to an ascending node that differs from a duration of a burn of the south electric thruster proximate to a descending node. The orbit controller is configured to select an offset of the burn of the north electric thruster in relation to the ascending node that differs from an offset of the burn of the south electric thruster in relation to the descending node.

Abstract: Apparatus and methods for stationkeeping in a satellite. The satellite includes a north electric thruster and a south electric installed on a zenith side, an east chemical thruster installed on an east side, and a west chemical thruster installed on a west side. An orbit controller detects a failure of one of the electric thrusters. In response to the failure, the orbit controller controls a burn of the remaining electric thruster proximate to an orbital node. The orbit controller controls a burn of one of the chemical thrusters at 90°±5° from the burn of the remaining electric thruster, and controls a burn of the other one of the chemical thrusters at 270°±5° from the burn of the remaining electric thruster.