ATTITUDE CONTROL SYSTEM FOR SMALL SATELLITES
First Claim
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1. An attitude control system (ACS) for use with a pico- or a nano-satellite comprising:
- a plurality of single-gimbaled control moment gyroscopes (SGCMGs) arranged in a pyramidal configuration and operable to provide three-axis attitude control of the satellite, wherein the ACS occupies a volume of less than about 100 mm×
100 mm×
50 mm of the satellite and has a mass less than about 500 grams.
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Abstract
Various embodiments of the present invention include an attitude control system for use with small satellites. According to various embodiments, the system allows rapid retargeting (e.g., high slew rates) and full three-axis attitude control of small satellites using a compact actuation system. In certain embodiments, the compact actuation system includes a plurality of single-gimbaled control moment gyroscopes (SGCMG) arranged in a pyramidal configuration that are disposed within a small satellite.
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Citations
21 Claims
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1. An attitude control system (ACS) for use with a pico- or a nano-satellite comprising:
a plurality of single-gimbaled control moment gyroscopes (SGCMGs) arranged in a pyramidal configuration and operable to provide three-axis attitude control of the satellite, wherein the ACS occupies a volume of less than about 100 mm×
100 mm×
50 mm of the satellite and has a mass less than about 500 grams.- View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18)
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19. A single-gimbaled control moment gyroscope (SGCMG) comprising:
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a flywheel assembly comprising; a flywheel housing; at least one flywheel rotationally disposed within the flywheel housing; and a flywheel motor configured to drive the flywheel via a drive shaft of the flywheel, wherein the drive shaft of the flywheel has a rotational axis oriented substantially perpendicular to a longitudinal axis extending through the SGCMG; and a gimbal assembly comprising; an L-shaped bracket comprising a first end surface and a second end surface; and a gimbal motor having a rotational axis oriented substantially co-axial to the longitudinal axis of the SGCMG, the gimbal motor coupled to the second end surface and configured for rotating the flywheel assembly about the longitudinal axis of the SGCMG and between the first end surface and the gimbal motor.
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20. A single-gimbaled control moment gyroscope (SGCMG) comprising:
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a flywheel assembly comprising; a flywheel housing; at least one flywheel rotationally disposed within the flywheel housing; a flywheel motor configured to drive the flywheel via a drive shaft of the flywheel; and at least one flywheel motor driver board coupled to the flywheel housing, wherein the drive shaft of the flywheel has a rotational axis oriented substantially perpendicular to a longitudinal axis extending through the SGCMG; and a gimbal assembly comprising; a bracket comprising a first end surface and a second end surface; and a gimbal motor having a rotational axis oriented substantially co-axial to the longitudinal axis of the SGCMG, the gimbal motor coupled to the second end surface and configured for rotating the flywheel assembly about the longitudinal axis of the SGCMG and between the first end surface and the gimbal motor.
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21. A method for providing three-axis attitude control of a pico- or a nano-satellite comprising:
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providing an attitude control system (ACS) comprising a plurality of single-gimbaled control moment gyroscopes (SGCMG) arranged in a pyramidal configuration, wherein the ACS occupies a volume of less than about 100 mm×
100 mm×
50 mm of the satellite and has a mass less than about 500 grams; andcontrolling the SGCMGs to produce a net torque on the satellite to adjust the attitude thereof.
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Specification