| CPC B64G 1/6462 (2023.08) [B64G 1/244 (2019.05); B64G 1/40 (2013.01)] | 20 Claims |
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1. A servicer satellite configured to perform rendezvous with a client satellite, the servicer satellite comprising:
a body comprising an X axis with a +X direction and a −X direction, a Y axis with a +Y direction and a −Y direction, and a Z axis with a +Z direction and a −Z direction;
a set of thrusters comprising: i) a first thruster coupled to the body, ii) a second thruster coupled to the body, iii) a third thruster coupled to the body, and iv) a fourth thruster coupled to the body;
a controller configured with commands to fire: i) the first thruster and the second thruster to produce a first thrust vector that reduces a separation distance between the servicer satellite and the client satellite and that removes an angular momentum or a rotational velocity of the body, and ii) the third thruster and the fourth thruster to produce a second thrust vector that reduces a rate of closure between the servicer satellite and the client satellite and that removes the angular momentum or the rotational velocity of the body, the controller further configured with commands to fire the first thruster and the second thruster to follow a rendezvous trajectory that matches orbital parameters of the servicer satellite and the client satellite;
wherein:
the first thruster is coupled to at least one of a first hinge and a first gimble and the second thruster is coupled to at least one of a second hinge and a second gimble to enable the first thruster and the second thruster to position to produce the first thrust vector; and
the third thruster is coupled to at least one of a third hinge and a third gimble and the fourth thruster is coupled to at least one of a fourth hinge and a fourth gimble to enable the third thruster and the fourth thruster to position to produce the second thrust vector.
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