Rocket engine nozzle that is steerable by means of a moving diverging portion on a cardan mount
US6948307B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 3, 2003 |
| Grant date | Sep 27, 2005 |
| Priority date | — |
| Expiry date | Jul 3, 2023 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K9/97
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The nozzle comprises a moving diverging portion (20) and a static portion (16) secured to the rear end wall of the combustion chamber (12) of the engine. A cardan mount jointed link device connects the moving diverging portion of the nozzle to the static portion, the moving diverging portion and the static portion being in mutual contact via respective spherical surfaces (24a, 16a), and an actuator device (50a, 50b) acts on the moving diverging portion of the nozzle so as to be able to vary the direction of the thrust vector of the engine by modifying the orientation of the nozzle with sliding of the spherical surfaces one on the other. Resilient return means (62, 64) are interposed between the moving diverging portion (20) of the nozzle and the static portion (16) and act on the moving diverging portion in order to urge it towards the static portion so as to keep the spherical surfaces (24a, 16a) in mutual contact for any desired orientation of the nozzle.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.