Satellite having a stackable configuration
US5522569A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Feb 4, 1994 |
| Grant date | Jun 4, 1996 |
| Priority date | — |
| Expiry date | Feb 4, 2014 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S136/292
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A satellite has two solar array panels which are moveable between a closed configuration and an open configuration. The solar array panels are pivotably mounted on hinges attached along the top and bottom of the satellite and extend outwardly from the top and bottom of the satellite in the open configuration. The height of the perimeter sidewall is selected such that the satellite has a generally oblate configuration. Each solar array panel has a surface area substantially equal to that of the satellite cross-sectional area. The hinges are mounted on pintles extending from a solar array drive motor which rotates the solar panel about the axis defined by the pintles to provide one axis sun tracking. The solar array panels are pivoted about the axes of the hinges until substantially parallel to the top and bottom of the satellite to form a compact, stackable configuration of the satellite for stowage. Three couplers positioned along the perimeter wall couple the satellite to similarly configured satellites within the fairing of a launch vehicle. The coupled satellites form a stack having three load-bearing columns consisting of the satellite couplers. In the stacked configuration, th…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.