FIELD: engines and pumps.
SUBSTANCE: invention refers to the space engineering. The low-thrust engine block of the booster contains a box-shaped casing, two stabilization engines secured in the bottom base of the casing, a stabilization engine secured on one of the lateral walls of the casing, and a mounting bracket. Each stabilization engine contains a combustion chamber casing and a fuel supply control valve connected to the combustion chamber casing. The low-thrust engine block is equipped with adapters and thermal buses. Each thermal bus contains a package of strips with tips overplayed on each other. Each stabilization engine is secured on the casing via one of the adapters, the bottom of each of which is connected with the combustion chamber casing of the relevant stabilization engine, and the external supporting ring is secured on the casing of the block. The top base of the casing is mostly performed in the form of a thermal control radiator.
EFFECT: result of the invention provides the reducing of thermal impact of the stabilization engines on fuel tanks of the booster during their operation.
13 cl, 19 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| INTERORBITAL TOWING VEHICLE | 1995 |
|
RU2094331C1 |
| RETURN STAGE OF ROCKET VEHICLE AND METHOD OF ITS OPERATION | 2015 |
|
RU2609549C1 |
| RETURN STAGE OF ROCKET VEHICLE AND METHOD OF ITS OPERATION | 2015 |
|
RU2609547C1 |
| RETURN STAGE OF ROCKET VEHICLE, METHOD OF ITS OPERATION AND GAS TURBINE ENGINE | 2015 |
|
RU2609664C1 |
| SMALL BOOSTER | 2023 |
|
RU2808312C1 |
| THERMAL CONTROL SYSTEM FOR INTERNAL COMBUSTION ENGINES BASED ON SELF-REGULATING ELECTRIC HEATERS | 2019 |
|
RU2718556C1 |
| RETURN CARRIER ROCKET STAGE, METHOD OF ITS OPERATION AND GAS TURBINE ENGINE | 2015 |
|
RU2602656C1 |
| RETURN CARRIER ROCKET STAGE | 2015 |
|
RU2603305C1 |
| ICE FUEL AND MOTOR OIL THERMAL CONTROL SYSTEM | 2009 |
|
RU2398126C1 |
| NON-EXPANDABLE AERO-SPACE SYSTEM | 1999 |
|
RU2164882C1 |
