F213_O2S-1_D276SS_L240.jpg ThumbnailsF213 O2S-1 D276SS L017ThumbnailsF213 O2S-1 D276SS L017
"11.1.4. Nominal engine thrust in vacuum, tf:
second stage - 250
orbital maneuvering - 3.5
reaction control - 0.4

11.1.5. Engine propellant components:
second stage - O2+H2
orbital maneuvering and reaction control - N2O4+UDMH

11.1.6. Throttle range of second stage engines, %
-50...+9

11.1.7. Crew compartment volume, m³:
general - 120
working - 80

11.1.8. Number of astronauts:
crew - 3
passengers (due to reduction in payload mass) - up to 6

11.1.9. Duration of stay on the satellite:
standard - up to 7 days
with additionally consumed reserves of mass for the
operation of on-board systems and life support - up to 30 days

11.1.10. Crossrange due to the use of aerodynamic quality, km ±2000

11.1.11. Landing speed, km/h:
during normal landing - 280-320
during emergency landing - 360-370

11.1.12. Operational lifetime, flights:
airframe - no less than 100
engines - 50, with refurbishment up to 100"

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