Hybrid missile propulsion system with reconfigurable multinozzle grid
US8117847B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 7, 2008 |
| Grant date | Feb 21, 2012 |
| Priority date | — |
| Expiry date | Dec 22, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K9/30
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A propulsion system, such as for use in a missile, includes a multinozzle grid having a pair of plates that are separably mechanically coupled together. When coupled together in a first configuration, the plates provide multiple nozzles in a first nozzle configuration (geometry). Separation of the plates, such as by separating an aft plate from a forward plate that remains with the missile, reconfigures the multinozzle grid to a second configuration that has nozzles in a second nozzle configuration (geometry). The nozzle configurations may be suitable for different types of propulsion mechanisms. The hybrid propulsion system utilizing the multinozzle grid may include a pair of pressurized gas sources, for example a solid rocket fuel and a combustion chamber for a ramjet.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.