Thermal protection device for a nozzle
US11821388B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Nov 2, 2020 |
| Grant date | Nov 21, 2023 |
| Priority date | — |
| Expiry date | Nov 2, 2040 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/38
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Nozzle of a spacecraft engine, comprising a nozzle body extending along a main direction, from a proximal end secured to the engine of the spacecraft, and a free distal end, said nozzle body having a plurality of stiffeners extending from an outer surface of the nozzle body, radially with respect to the main direction, said nozzle comprising a thermal insulation system, comprising at least one strip of insulating material disposed so as to surround the outer surface of the nozzle body over at least part of the height of said nozzle body, said thermal insulation system comprising a plurality of holding elements, each holding element being positioned so as to surround said strips of insulating material, and being disposed between two stiffeners of the nozzle body.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.