Spacecraft design with multiple thermal zones
US10780998B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 22, 2017 |
| Grant date | Sep 22, 2020 |
| Priority date | — |
| Expiry date | Aug 2, 2038 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/506
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A spacecraft includes a body, a plurality of separate units, and a first auxiliary radiator panel. The body includes a plurality of sidewalls, at least a first sidewall of the plurality of sidewalls including an outboard-facing radiator surface having optical solar reflectors disposed thereon. A first subset of the plurality of units is thermally coupled with the outboard-facing radiator surface of the first sidewall. A second subset of the plurality of units is thermally coupled with the first auxiliary radiator panel and is isolated from at least conductive thermal heat transfer with the outboard-facing radiator surface of the first sidewall. The first subset of units is spatially proximate to the second subset of units and is configured to operate in a first temperature range. The second subset of units is configured to operate in a second temperature range, the second temperature range being different from the first temperature range.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.