Saturn IB-D

Saturn IB-D
FunctionUncrewed LEO and Lunar launch vehicle
ManufacturerVon Braun
Country of originUnited States
Size
Height51.00 m (167.32 ft)
Diameter6.61 m (21.7 ft)
Mass1,511,980 kg (3,333,350 lb)
Stages2
Capacity
Payload to LEO
Mass33,000 kg (73,000 lb)
Launch history
StatusConcept/study
Launch sitesN/A
Total launchesN/A
Boosters – Titan UA1205
No. boosters4
Powered by1 United Technologies UA1205
Maximum thrust5,849.411 kN (1,315,000 lbf)
Specific impulse263 s (2.58 km/s)
Burn time115 seconds
PropellantPBAN[1]
First stage – S-1B
Powered by8 Rocketdyne H-1
Maximum thrust8,241.763 kN (1,852,822 lbf)
Specific impulse296 s (2.90 km/s)
Burn time155 seconds
PropellantRP-1/LOX
Second stage – S-IVB
Powered by1 Rocketdyne J-2
Maximum thrust1,031.600 kN (231,913 lbf)
Specific impulse421 s (4.13 km/s)
Burn time475 seconds
PropellantLH2/LOX

Studied by Douglas Aircraft Company in 1965, this rocket consisted of a whole Saturn IB with 4 strap-on SRBs that have flown on the Titan 3E interplanetary missile carriers. All components of the vehicle have flown, but not together for this concept.[2]

References

  1. ^ Wade, Mark. "UA1205". www.astronautix.com. Encyclopedia Astronautica. Archived from the original on December 28, 2016. Retrieved 10 June 2020.
  2. ^ Wade, Mark. "Saturn IB-D". www.astronautix.com. Encyclopedia Astronautica. Archived from the original on December 28, 2016. Retrieved 10 June 2020.

Lowther, Scott, Saturn: Development, Details, Derivatives and Descendants, Work in progress. Available chapters may be ordered directly from Scott Lowther at web site indicated. Accessed at: https://web.archive.org/web/20070521083808/http://www.webcreations.com/ptm.


This article is issued from Wikipedia. The text is available under Creative Commons Attribution-Share Alike 4.0 unless otherwise noted. Additional terms may apply for the media files.