Radiator using thermal control coating
US6176453A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Dec 11, 1998 |
| Grant date | Jan 23, 2001 |
| Priority date | — |
| Expiry date | Dec 11, 2018 |
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 0.16 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 0.33 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.