Semi-axisymmetric scramjet flowpath with conformal nozzle
US7328571B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 29, 2004 |
| Grant date | Feb 12, 2008 |
| Priority date | — |
| Expiry date | Sep 16, 2025 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF42B15/10
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In accordance with a first aspect of the present invention, an aircraft having a scramjet engine is provided. The scramjet engine includes a flowpath which varies in three dimensions. In accordance with a second aspect of the present invention, a method for launching an aircraft having a scramjet engine with a nozzle section and a solid rocket booster positioned within the nozzle section is provided. The method includes the steps of igniting the solid rocket booster to accelerate the aircraft to a speed at which the scramjet engine can operate, clearing the nozzle section by ejecting the solid rocket booster from the nozzle section upon exhaustion of the solid rocket booster; and injecting fuel into a flow of air passing through the scramjet engine and igniting the fuel and the air to provide thrust to the aircraft.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.