System for controlling speed transition and thrust vectorisation in a multiple-shaped nozzle by secondary injection
US11661910B2 · kind B2 · utility
Assignees
Inventors
Key dates
| Filing date | Apr 18, 2019 |
| Grant date | May 30, 2023 |
| Priority date | — |
| Expiry date | May 6, 2039 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/713
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A mixing tube with multiple shapes is provided, allowing additional injection of gas in order to keep the flow detached from the second shape in an ascent phase and to bring about, in a descent phase, a controlled detachment as a result of the change of slope between the two shapes. A propulsion nozzle for an engine of a spacecraft or aircraft is provided including such a mixing tube and a method for controlling the speed transition of the propulsion gases in such a nozzle in accordance with the altitude. Also, a method is provided for vectorising the thrust in such a nozzle by radial and asymmetrical injection of gas and a control method which prevents re-attachment of the jet to the second shape of such a propulsion nozzle for an engine of a spacecraft when it is in the take-off or landing phase.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.