Satellite architecture with deployable electrical equipment
US6196501A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Oct 7, 1998 |
| Grant date | Mar 6, 2001 |
| Priority date | — |
| Expiry date | Oct 7, 2018 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/503
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A spacecraft comprises a first module including a first assembly of components and a second module including a second assembly of components and a thermal radiator. The second module is movable between a stowed position proximate the first module whereat the thermal radiator is only partially operative and a deployed position distant from the first module whereat the thermal radiator means is fully operative for dissipating waste heat to deep space for at least one of the first and second assemblies of components. In one embodiment, the first module includes a housing defining an interior cavity, the second module including a casing so shaped and dimensioned as to be telescopically received within the internal cavity of the first module and the second module being translationally movable along a deploying axis between the stowed position and the deployed position but incapable of mutual rotation about the deploying axis. In another embodiment, a spacecraft includes a plurality of discrete faces and comprises an equipment panel including an assembly of heat generating components which require cooling, a thermal radiator, and a connecting hinge mounting the equipment panel for pivota…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.