Propulsion system for hypersonic flight
US4919364A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Apr 7, 1989 |
| Grant date | Apr 24, 1990 |
| Priority date | — |
| Expiry date | Apr 7, 2009 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A propulsion system for an aircraft capable of hypersonic flight combines a turbo-jet with a ramjet which are so arranged that the ramjet or jets are located directly adjacent to the aircraft body while the turbo-jet or jets are located away from the aircraft body so that the ramjet or jets is placed between the turbo-jets and the body. This arrangement makes the turbo-jets much more accessible for maintenance and exchange work. Both types of engines have a common air intake which is provided with flaps capable of guiding the body boundary layer through the ramjet when the latter is not in operation. When the ramjet is in operation, the air intake flaps form the air intake in such a way that boundary layer turbulent air is mixed with undisturbed incoming air for the ramjet while the air inflow to the turbo-jet is closed off altogether. The guide channel for the body boundary layer begins upstream of the common air intake and can be closed for the ramjet operation so that the boundary layer air is guided into the air intake. At least one nozzle flap is arranged near the thrust nozzles so that both thrust jets can be influenced. One effective surface of the nozzle flap influences the…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.