Control moment gyroscope based momentum control systems in small satellites
US8312782B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 16, 2009 |
| Grant date | Nov 20, 2012 |
| Priority date | — |
| Expiry date | Jul 11, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T74/1282
- WIPO fieldTransport
- WIPO sectorMechanical engineering
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.