Gimbaled ion thruster arrangement for high efficiency stationkeeping
AssigneeLockheed Martin Corporation
InventorsMichael Joseph Glogowski, Neil Evan Goodzeit
Life of this patent
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Abstract
An attitude control system for a spacecraft that includes a north side, a south side, an east side, a west side, an earth facing side, and an anti-earth facing side. The attitude control system includes a plurality of gimbaled thrusters interconnected with the spacecraft and arranged to produce thrust in a direction parallel to a roll-pitch plane of the spacecraft.
Claims30
An attitude and orbit control system for a spacecraft that includes a north side, a south side, an east side, a west side, an earth facing side, and an anti-earth facing side, the attitude control system comprising:
- a plurality of gimbaled thrusters interconnected with the spacecraft, each thruster being positioned on the spacecraft such that by gimbaling each thruster can produce thrust in a direction substantially in a roll-pitch plane of the spacecraft while producing substantially no torque, wherein at least one of the plurality of gimbaled thrusters has a range of motion such that in a first position it directs thrust substantially alone a first axis, and in a second position it directs thrust substantially along a second axis, and wherein the second axis is perpendicular to the first axis.
A method for maneuvering a spacecraft that includes a north side, a south side, an east side, a west side, an earth facing side, and an anti-earth facing side, the method comprising:
- gimbaling at least one of a plurality of thrusters interconnected with the spacecraft;
- operating the at least one thruster to produce thrust in a direction parallel to a roll-pitch plane of the spacecraft, wherein at least one thruster has a range of motion such that in a first position it directs thrust substantially along a first axis, and in a second position it directs thrust substantially along a second axis, and wherein the second axis is perpendicular to the first axis.
A spacecraft, comprising:
- a north side, a south side, an east side, a west side, an earth facing side, and an anti-earth facing side;
- and
- an attitude and orbit control system, comprising:
- a plurality of gimbaled thrusters interconnected with the spacecraft, each thruster being positioned on the spacecraft such that by gimbaling each thruster can produce thrust in a direction substantially in a roll-pitch plane of the spacecraft while producing substantially no torque, wherein at least one of the plurality of gimbaled thrusters has a range of motion such that in a first position it directs thrust substantially along a first axis, and in a second position it directs thrust substantially along a second axis, and wherein the second axis is perpendicular to the first axis.
Dependencies are inferred from the claim text.