Stable hybrid rocket technology
US10920714B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 14, 2014 |
| Grant date | Feb 16, 2021 |
| Priority date | — |
| Expiry date | Mar 18, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K9/97
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A hybrid rocket engine is described that achieves stable, highly efficient hybrid combustion by having a core flow of fuel-rich gas generator gases, with the flow being surrounded with an annular injection of oxidizer. The fuel-rich gas serves to vaporize and decompose the oxidizer, such as nitrous oxide, and prepare it for effective, stable combustion. In one embodiment, this is done at the head-end of a combustion chamber. The combustion products can then be expanded through a nozzle to create thrust. The engine can be an upper stage engine that can include modular thrust chambers and an integrated aerospike nozzle. The thrust chambers can be arranged in an array that rings the top of the aerospike nozzle.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.