High temperature thermal protection system for rockets, and associated methods
US11174818B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 10, 2019 |
| Grant date | Nov 16, 2021 |
| Priority date | — |
| Expiry date | Sep 6, 2039 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/601
- WIPO fieldSurface technology, coating
- WIPO sectorChemistry
Abstract
A high temperature thermal protection systems for rockets, and associated methods, is disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end. The launch vehicle is elongated along a vehicle axis extending between the first and second ends and carries a propulsion system having at least one nozzle positioned at the second end of the launch vehicle. A thermal protection apparatus positioned around the nozzle is used to provide cooling and/or insulation to the nozzle during the flight of the launch vehicle. The thermal protection apparatus can include multiple fabric layers and an insulation layer stacked and stitched together. The fabric layers can include metal alloy fibers. In representative systems, the thermal protection apparatus can further include provisions for water that saturates the insulation layer to provide further insulating and/or cooling effects.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.