FIELD: manufacture of engines. SUBSTANCE: hybrid engine includes rocket turbine engine forming dual ramjet engine together with housing and movable casing. Mounted inside central body in shortened nozzle of external expansion is liquid-propellant rocket engine with annular combustion chamber and external expansion nozzle with central body inside which members of common turbopump unit are arranged. EFFECT: enhanced reliability. 1 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| DETONATION COMBUSTION PULSE-JET ENGINE | 1997 |
|
RU2142058C1 |
| REUSABLE FIRST STAGE LAUNCH VEHICLE | 2020 |
|
RU2744736C1 |
| HYBRID JET ENGINE | 2005 |
|
RU2272926C1 |
| VORTEX GAS COMPRESSOR DEVICE FOR COMBINED AIR-JET ENGINE | 2019 |
|
RU2766496C2 |
| AIR-JET ENGINE | 1991 |
|
RU2033549C1 |
| DIRECT FLOW TURBORETACTIVE DETONATION ENGINE (DFTDE) | 2016 |
|
RU2638239C1 |
| LIQUID-PROPELLANT ROCKET ENGINE PLANT | 1998 |
|
RU2136935C1 |
| RETURN STAGE OF ROCKET VEHICLE AND METHOD OF ITS OPERATION | 2015 |
|
RU2609549C1 |
| RETURN STAGE OF ROCKET VEHICLE AND METHOD OF ITS OPERATION | 2015 |
|
RU2609547C1 |
| LIQUID PROPELLANT ROCKET ENGINE | 2013 |
|
RU2524483C1 |
Authors
Dates
1998-03-10—Published
1992-12-30—Filed