Jetavator for rocket engine
US5735463A · kind A · utility
2Cited by
7References
8Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 21, 1996 |
| Grant date | Apr 7, 1998 |
| Priority date | — |
| Expiry date | Mar 21, 2016 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K9/97
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A jetavator rotatably installed to a nozzle exit of a rocket engine in order to control the thrust direction of the engine. The jetavator is generally in a hollow frustoconical shape and comprises a heat-resistant layer, a heat insulating layer and a reinforcing layer which are laminated one upon another. The heat-resistant layer is formed with a plurality of slits through which it is divided into a plurality of parts. Each slit is formed passing from the inner peripheral surface to the outer peripheral surface of the heat-resistant layer. Each slit is closed with a backplate which extends along the slit.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.