Space storable, thrust-vectorable rocket motor nozzle and related methods
US10001085B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 24, 2014 |
| Grant date | Jun 19, 2018 |
| Priority date | — |
| Expiry date | Mar 6, 2037 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/603
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A thrust-vectoring rocket motor nozzle includes a forward assembly having a forward shell with a flange configured for connection to a motor and a throat portion opposite the flange. A ball joint sleeve may be disposed proximate the throat portion, and an exit cone assembly may include a ball joint socket configured to mate with the ball joint sleeve to allow movement of the exit cone assembly about one or more axes relative to the forward assembly. A thermal barrier may be disposed in a gap between the forward assembly and the exit cone assembly. The forward assembly may include a throat insulator mechanically locked within the forward shell. Related methods include forming thrust-vectorable rocket motor nozzles. Rocket motors may include such nozzles.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.