Rocket motor nozzle throat area control system and method
US7464535B2 · kind B2 · utility
1Cited by
22References
22Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 29, 2004 |
| Grant date | Dec 16, 2008 |
| Priority date | — |
| Expiry date | Jun 6, 2026 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K9/82
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A solid rocket motor including a combustion chamber, in which propellant is ignited to produce combustion gas, and a nozzle having a throat with an effective flow area, implements a system and method to inject gas into the nozzle throat to control its effective cross sectional flow area. Controlling the effective cross sectional flow area of the nozzle throat in turn controls combustion chamber pressure, thus the burn rate of the propellant in the combustion chamber, and thus the thrust generated thereby.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.