FIELD: engine devices and pumps.
SUBSTANCE: chamber comprises a cooled part of nozzle and an uncooled header of carbon-carbon composite material, steering assemblies and a frame, according to the invention, in the uncooled header, there are niches in which several sections of a detachable earth nozzle are disposed, having rotation shafts tangential in the area of the joint of uncooled header cooled part of the nozzle, mounted in brackets fixed to the cooled part of nozzle and connected by steering units to the engine frame.
EFFECT: increasing the efficiency and reliability of work along the entire rocket flight path.
3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| LIQUID-PROPELLANT ROCKET ENGINE WITH DEFLECTOR INSIDE NOZZLE | 2018 |
|
RU2686367C1 |
| LIQUID ROCKET ENGINE WITH BAFFLE AT NOZZLE SECTION | 2015 |
|
RU2579294C1 |
| LIQUID ROCKET ENGINE WITH A NOZZLE OF CARBON-CARBON COMPOSITE MATERIAL (CCCM) | 2017 |
|
RU2657400C1 |
| LRE WITH PERIPHERAL RUDDERS AT NOZZLE CUT | 2022 |
|
RU2783307C1 |
| CAMERA LPR | 2017 |
|
RU2681733C1 |
| COMPOUND PROPULSION SYSTEM OF REUSABLE FIRST STAGE LAUNCHER | 2019 |
|
RU2742515C1 |
| LAYOUT OF CRUISE MULTI-CHAMBER PROPULSION PLANT OF TWO-STAGE LAUNCHER WITH COMPOSITE NOZZLE CLUSTER | 2015 |
|
RU2610873C2 |
| LIQUID ROCKET ENGINE WITH DEFLECTOR SECTORS AT THE NOZZLE EXIT | 2016 |
|
RU2631370C1 |
| RETURN CARRIER ROCKET STAGE, METHOD OF ITS OPERATION AND GAS TURBINE ENGINE | 2015 |
|
RU2602656C1 |
| RETURN STAGE OF ROCKET VEHICLE AND METHOD OF ITS OPERATION | 2015 |
|
RU2609549C1 |
