F213_O5-1_D254_L008.jpg F213 O5-1 D254 L007Thumbnailspolyus launch cyclogramF213 O5-1 D254 L007Thumbnailspolyus launch cyclogram
"[Cont. from previous page: As the second stage of MTKS, the program provides for the creation in 1985-90 of a] reusable flyback first stage, which will replace the expendable first stage."

4. Heavy two-stage launch vehicle RLA-150, with a payload capacity of 230 tons, to a low northeastern reference orbit. It is obtained by hanging six blocks of the first stage of the RLA-120 without steering engines to the oxygen-hydrogen block MTKS with its engines.

Launch weight 5800 t, maximum width ~ 21 m, height 62 m, number of engines 10.

The newly created oxygen-hydrogen third stage with the 11D57М engine makes it possible to launch a satellite weighing ~ 40 tons into geostationary orbit with a powerful nuclear propulsion system to solve special missions of the Ministry of Defense. The same stage launches into orbit the lunar satellite a rocket radome unit weighing 60 tons, the minimum required for landing on the Moon an expedition ship weighing 22 tons with three cosmonauts, a supply of consumable components for 5 days on the Moon, and a return stage.

These circumstances determined 230 tons as the required load capacity of the RLA-150.

Height of the RLA-150 with the third stage and payload - 100 m. Flight tests of the RLA-150 are carried out in 1980-1981.

5. A permanent lunar base-station consists of autonomous modules that are finally assembled and tested in factory conditions on Earth, without carrying out any work on the Moon, except for de-mothballing and deployment of auxiliary equipment. The modules use service and life support systems common with those tested on spacecraft and orbital stations."

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