Single gimbal control moment gyroscope skewed array mounting arrangement
US4825716A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Nov 13, 1987 |
| Grant date | May 2, 1989 |
| Priority date | — |
| Expiry date | Nov 13, 2007 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T74/1221
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A gyroscope mounting structure for use in a spacecraft attitude control system has ten control moment gyroscopes. The structure has a truss for supporting the gyroscopes. The truss has an axis of symmetry. Five front gyroscopes are axially spaced from five rear gyroscopes along the axis of symmetry. The front gyroscopes and the rear gyroscopes are peripherally spaced about the axis of symmetry at equal angular spacings. Each gyroscope has a gimbal axis which is disposed at substantially the same acute angle to the axis of symmetry. Each gimbal axis is disposed parallel to an adjacent reference line which passes through a common intersection point on the axis of symmetry. The truss has a front frame, a rear frame and chords connecting the frames. The truss has five front struts interspaced between the five front gyroscopes for support thereof. The truss also has five rear struts interspaced between the five rear gyroscopes for support thereof. The structure is intended to provide ease of access to the gyroscopes and to minimize structure size and weight.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.