Saturn-Shuttle
| NASA model of Saturn-Shuttle configuration | |
| Function | Crewed LEO launch vehicle |
|---|---|
| Manufacturer | Boeing (S-IC) Martin Marietta (External Tank) Rockwell International (Space Shuttle orbiter) |
| Country of origin | United States |
| Size | |
| Height | 86 m (281 ft)[1] |
| Diameter | 10 m (33 ft)[1] |
| Mass | 2,300,000 kg (5,070,000 lb)[1] |
| Stages | 2 |
| Capacity | |
| Payload to LEO | |
| Mass | 60,500 kg (133,400 lb)[1] |
| Launch history | |
| Status | Canceled |
| Launch sites | Kennedy LC-39 |
| First stage – S-IC | |
| Height | 137.99 ft (42.06 m)[1] |
| Diameter | 33 ft (10 m)[1] |
| Empty mass | 298,104 lb (135,218 kg)[1] |
| Gross mass | 5,040,245 lb (2,286,217 kg)[1] |
| Powered by | 5 Rocketdyne F-1 [1] |
| Maximum thrust | 8,700,816 lbf (38,703.16 kN)[1] |
| Specific impulse | 304 seconds (2.98 km/s)[1] |
| Burn time | 161 s[1] |
| Propellant | RP-1/LOX [1] |
| Second stage – External Tank | |
| Height | 153.8 ft (46.9 m)[1] |
| Diameter | 27.5 ft (8.4 m)[1] |
| Empty mass | 65,980 lb (29,930 kg)[1] |
| Gross mass | 1,655,616 lb (750,975 kg)[1] |
| Specific impulse | 455 seconds (4.46 km/s)[1] |
| Burn time | 480 s[1] |
| Propellant | LH2 / LOX [1] |
| Second stage – Orbiter plus External Tank | |
| Powered by | 3 SSMEs located on Orbiter[1] |
| Maximum thrust | 5,250 kN (1,180,000 lbf)[1] |
| Specific impulse | 455 seconds (4.46 km/s)[1] |
| Burn time | 480 s[1] |
| Propellant | LH2 / LOX [1] |
The Saturn-Shuttle was a preliminary concept of launching the Space Shuttle orbiter using a modified version of the first stage of the Saturn V rocket.[1] It was studied and considered in 1971–1972.[2]
Description
[edit ]An interstage would be fitted on top of the S-IC stage to support the external tank in the space occupied by the S-II stage in the Saturn V. It was an alternative to the SRBs.[1]
Some studies proposed the addition of wings (and some form of landing gear) to the S-IC stage, which would allow the booster to fly back to the Kennedy Space Center, where technicians would then refurbish the booster (by replacing only the five F-1 engines and reusing the tanks and other hardware for later flights).[1]
The Shuttle would handle space station logistics, while the Saturn V would launch components. This would have allowed the International Space Station, using a Skylab or Mir configuration with both U.S. and Russian docking ports, to have been lifted with just a handful of launches. However, it was ultimately rejected on basis of cost.[citation needed ]
See also
[edit ]References
[edit ]- ^ a b c d e f g h i j k l m n o p q r s t u v w x y z aa ab "Saturn Shuttle". www.astronautix.com. Archived from the original on October 27, 2016. Retrieved 2019年06月24日.
- ^ Lindroos, Marcus (June 15, 2001). "Phase B' Shuttle contractor studies 1971". Introduction to Future Launch Vehicle Plans [1963-2001] – via PMView.
Further reading
[edit ]- "Phase B' Shuttle contractor studies 1971". Archived from the original on January 27, 2023. Retrieved May 26, 2023.
- "Phase B' Shuttle cost tradeoffs 1971". Archived from the original on January 17, 2023. Retrieved May 26, 2023.
External links
[edit ]- "Shuttle". www.astronautix.com. Archived from the original on July 12, 2016.
- Saturn Shuttle with Flyback Booster, video rendering by Hazegrayart
