FIELD: cosmonautics.
SUBSTANCE: invention relates to payload (PL) launchers. Stage comprises instrument compartment (1), tanks of first (2) and second (3) fuel components. In engine compartment (4) below toroidal tank (3) there is a propulsion unit, chambers (5) of which are located evenly along the bottom circumference. In the presence of a steering rocket engine, its chambers (6) are located similarly. Compartment (7) of PL (8) is mainly formed by surfaces of tanks, and there is a device for moving (pushing) PL along axis (9) of the stage. PL compartment is closed by hatch (10). For landing, retractable or folding landing supports (11) are used. There may also be braking parachutes arranged in compartments (12).
EFFECT: improved design perfection and improved mass-dimensional characteristics of the carrier rocket reusable stage.
8 cl, 4 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| REUSABLE LAUNCH VEHICLE STAGE | 2020 |
|
RU2746471C1 |
| REUSABLE CARRIER ROCKET STAGE | 2021 |
|
RU2766468C1 |
| LAUNCH VEHICLE WITH UNIVERSAL UPPER STAGE AND PROPULSION SYSTEM FOR IT | 2020 |
|
RU2750825C1 |
| RETURNING UPPER STAGE OF TWO-STAGE LAUNCH VEHICLE AND METHOD FOR ITS LANDING | 2022 |
|
RU2809408C1 |
| MULTISTAGE CARRIER ROCKET CONFIGURATION | 2013 |
|
RU2532445C1 |
| GLIDING SPACESHIP (VERSIONS) WITH FOLDING NOSE CONE AND METHOD OF CONTROLLING ITS DESCENT TO AIRFIELD | 2011 |
|
RU2479469C1 |
| REUSABLE AIRCRAFT SYSTEM | 0 |
|
SU580696A1 |
| REUSABLE FIRST STAGE OF THE LAUNCH VEHICLE | 2022 |
|
RU2790569C1 |
| REUSABLE SPACE TRANSPORTATION SYSTEM FOR MASS DELIVERY FROM NEAR-EARTH ORBIT TO CIRCUMLUNAR ORBIT OF TOURISTS OR PAYLOADS AND SUBSEQUENT RETURN TO EARTH | 2019 |
|
RU2736657C1 |
| MULTI-CHAMBER LIQUID ROCKET ENGINE WITH CONTROLLED THRUST VECTOR | 2021 |
|
RU2771474C1 |
