The Boeing Company
Systems and methods for satellite orbit and momentum control

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.