Radiator using thermal control coating
US5884868A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Mar 18, 1997 |
| Grant date | Mar 23, 1999 |
| Priority date | — |
| Expiry date | Mar 18, 2017 |
Classification
- Technology area (CPC C)Chemistry; Metallurgy
- CPC primaryC08K3/11
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A spacecraft has internal structure which generates heat, and a radiator element in thermal communication with the spacecraft internal structure. The radiator element has a radiating surface and a coating on the radiating surface including a white thermal control paint. The paint has an initial solar absorptance of not greater than about 0.20 and an initial infrared emittance of not less than about 0.80. The standard end-of-life projected solar absorptance is not more than about 0.3 for a paint with an inorganic binder, and the standard end-of-life projected solar absorptance is not more than about 0.6 for a paint with an organic binder.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.