Control moment gyroscope array and method of power distribution therefor
US8210062B2 · kind B2 · utility
0Cited by
6References
13Claims
0Family size
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Key dates
| Filing date | Apr 18, 2007 |
| Grant date | Jul 3, 2012 |
| Priority date | — |
| Expiry date | May 14, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T74/1254
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An attitude control system for a spacecraft is disclosed that includes a scissored pair of control moment gyroscopes for delivering an output torque to the spacecraft along a an output axis, wherein each gyroscope has a spin motor for spinning a rotor about a rotor axis and a gimbal torque motor for rotating the rotor about a gimbal axis, and wherein the system includes a generator for extracting kinetic energy from the rotors during rotor deceleration to power the gimbal torque motors of the gyroscopes.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.