Saturn INT-21

The Saturn INT-21 was a study for an American orbital launch vehicle of the 1970s. It was derived from the Saturn V rocket used for the Apollo program, using its first and second stages, but lacking the third stage. The guidance unit would be moved from the top of the third stage to the top of the second stage. The INT-21 was never flown.

Saturn INT-21
FunctionLaunch vehicle
Manufacturer
Country of originUnited States
Size
Height80.00 m (262.47 ft) (without payload)
Diameter10.06 m (33.0 ft)
Mass2,916,080 kg (6,428,860 lb)
Stages2
Capacity
Payload to LEO
Mass87,880 kg (193,740 lb)[1]
Launch history
StatusStudy
Launch sitesLC-39A, Kennedy Space Center
Total launches0
First stage – S-IC
Engines5 Rocketdyne F-1
Thrust34.02 MN (7,650,000 lbf)
Burn time150 seconds
FuelRP-1 / LOX
Second stage – S-II
Engines5 Rocketdyne J-2
Thrust5 MN (1,100,000 lbf)
Burn time360 seconds
FuelLH2 / LOX

A related variant was launched once, from the Kennedy Space Center, Florida carrying the Skylab space station into orbit, at 17:30 UTC, on May 14, 1973.[2] As Skylab was built from an S-IVB stage, there was no need to move the guidance unit. This version was intended to be used for other flights in the Apollo Applications Program, and would have also been used to launch other American space stations, including Skylab B.

See also

The Saturn INT-21 would have been similar to the Saturn V which launched the Skylab space station, on May 14, 1973

References

  1. "EP-107 Skylab: A Guidebook. Chapter IV: Skylab Design and Operation". NASA. NASA History. Retrieved June 10, 2020.
  2. Young, Anthony (2008). The Saturn V F-1 Engine. Springer-Praxis. p. 245. ISBN 0-387-09629-9.


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