FIELD: engines and pumps.
SUBSTANCE: liquid propellant rocket (LPR) consists of a frame, a central body with profiled surface positioned coaxially to the longitudinal axis of the engine, and several individual combustion chambers with profiled hypersonic nozzles positioned around the central body and fixed to the engine frame. According to the invention, fairings made of carbon-carbon composite material and fixed to the engine frame are mounted betweem individual combustion chambers in the area of hypersonic nozzles, fairings' side faces serve as an extention to profiled surfaces of individual combustion chamber supersonic nozzles, wherein the fairings have a cylindrical surface on the outside with a radius equal to the radius of the engine outer surface, and are terminated by profiled surface of the central body on the inside.
EFFECT: increased engine thrust and improvement of its effectiveness due to higher specific thrust pulse.
3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| STAGE OF BOOSTER OPERATING IN DENSE AND RAREFIED LAYERS OF ATMOSPHERE | 2020 |
|
RU2739852C1 |
| LAYOUT OF CRUISE MULTI-CHAMBER PROPULSION PLANT OF TWO-STAGE LAUNCHER WITH COMPOSITE NOZZLE CLUSTER | 2015 |
|
RU2610873C2 |
| CAMERA LPR | 2017 |
|
RU2681733C1 |
| LIQUID-PROPELLANT ROCKET ENGINE WITH DEFLECTOR INSIDE NOZZLE | 2018 |
|
RU2686367C1 |
| NON-EXPENDABLE SINGLE-STAGE LAUNCH VEHICLE | 2000 |
|
RU2196078C2 |
| LIQUID-PROPELLANT ROCKET ENGINE CHAMBER WITH CONTROLLED NOZZLE | 2016 |
|
RU2640903C1 |
| PROCESS TO UP THE ROCKET ENGINE SUPERSONIC NOZZLE THRUST | 2013 |
|
RU2551244C2 |
| TEST DEVICE FOR LIQUID PROPELLANT ENGINES (VERSIONS) | 2009 |
|
RU2391548C1 |
| LIQUID PROPELLANT ROCKET ENGINE | 2008 |
|
RU2383770C1 |
| TRANSPORTATION SPACE SYSTEM | 1998 |
|
RU2165870C2 |
