Gaseous secondary injection thrust vector control device
US4686824A · kind A · utility
12Cited by
11References
3Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 25, 1982 |
| Grant date | Aug 18, 1987 |
| Priority date | — |
| Expiry date | Mar 25, 2002 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T137/2109
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Apparatus for modulating the thrust vector of a rocket motor by injecting t gas into the divergent section of the rocket nozzle and modulating injection of the hot gas by varying the flow from a solid propellant gas generator by controlling its flow rate with a vortex throttling valve arrangement.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.