CONTROL MOMENT GYROSCOPE BASED MOMENTUM CONTROL SYSTEMS IN SMALL SATELLITES
First Claim
1. An apparatus to control the attitude of a space craft comprising:
- an enclosure;
at least three control moment assemblies (CMAs) mounted within the enclosure, each CMA having a longitudinal axis and disposed in the enclosure at an orientation whereby the longitudinal axis of each CMA is one of orthogonal and inversely parallel in relation to each other, each CMA comprising;
a momentum rotor integrated within each CMA and configured to rotate about a second axis;
a spin motor comprising a motor rotor and a non-ferric motor stator, the non-ferric motor stator configured to induce rotation of the motor rotor about the second axis, the motor rotor and having a first end and a second end, the first end being coaxially affixed to the momentum rotor; and
a bearing concentric with the first axis in which the second end is mounted.
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Accused Products
Abstract
A self-contained momentum control system (MCS) for a spacecraft is provided for small satellites. The MCS features a miniaturized gyroscopic rotor with a rotational speed in excess of 20,000 RPM. The MCS includes at least three control moment gyroscopic mechanical assemblies (CMAs) rigidly mounted within a single enclosure, where each CMA mounted in an orientation whereby the longitudinal axis of each CMA is either orthogonal to every other CMA or is parallel to another CMA but in the opposite orientation. In order to further reduce the size of the MCS, an electronics package that is configured to interface command and control signals with and to provide power to the CMAs is included within the MCS enclosure. A plurality of shock isolation devices are used to secure each of the CMAs to the enclosure in order to reduce the launch load upon the CMAs thereby allowing the use of smaller rotor spin bearings. The MCS enclosure surrounding the CMAs and support structure is hermetically sealed.
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Citations
20 Claims
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1. An apparatus to control the attitude of a space craft comprising:
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an enclosure; at least three control moment assemblies (CMAs) mounted within the enclosure, each CMA having a longitudinal axis and disposed in the enclosure at an orientation whereby the longitudinal axis of each CMA is one of orthogonal and inversely parallel in relation to each other, each CMA comprising; a momentum rotor integrated within each CMA and configured to rotate about a second axis; a spin motor comprising a motor rotor and a non-ferric motor stator, the non-ferric motor stator configured to induce rotation of the motor rotor about the second axis, the motor rotor and having a first end and a second end, the first end being coaxially affixed to the momentum rotor; and a bearing concentric with the first axis in which the second end is mounted. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A self-contained momentum control system for a spacecraft comprising:
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a hermetically sealed enclosure; a compartment adjoined to the hermitic enclosure; at least three control moment assemblies (CMAs) rigidly mounted within the enclosure, each CMA mounted in an orientation whereby the longitudinal axis of each CMA is one of orthogonal and inversely parallel in relation to each other; an electronics package mounted within the compartment adjoined to the hermitic enclosure, the electronics package configured to interface command and control signals with, and to provide power to, the at least three CMAs; and a plurality of shock isolation devices coupling each of the at least three CMAs to the enclosure. - View Dependent Claims (12, 13, 14, 15, 16, 17, 18, 19, 20)
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Specification