Saturn-Shuttle

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Saturn-Shuttle

NASA model of Saturn-Shuttle configuration
Function	Manned LEO launch vehicle
Manufacturer	Boeing (S-IC) Martin Marietta (External Tank) Rockwell International (Space Shuttle orbiter)
Country of origin	United States
Size
Height	85 m (281 ft)
Diameter	10 m (33 ft)
Mass	2,304,000 kg[citation needed] (5,070,000 lb)
Stages	2
Capacity
Payload to LEO	max 60,500 kg[citation needed] (133,400 lb)
Launch history
Status	Canceled concept
Launch sites	LC-39, Kennedy Space Center
First flight	None, but concept studying began in 1972[1]
First stage - S-IC
Engines	5 Rocketdyne F-1 or F-1A
Thrust	max 34.02 MN (max 7,648,000 lbf)
Burn time	212 seconds
Fuel	RP-1/LOX
Second stage Space Shuttle orbiter and External Tank
Engines	3 Rocketdyne SSMEs
Thrust	6,834.3 kN (1,536,400 lbf) or 1,536,312 lbf (6,833.86 kN)[clarification needed][citation needed]
Burn time	≈ 475 seconds[citation needed]
Fuel	LH2/LOX

The Saturn-Shuttle was a preliminary concept of launching the Space Shuttle orbiter using the Saturn V rocket.^[2] It was studied and considered in 1971-1972.^[3]

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.

The addition of wings (and some form of landing gear) on the S-IC stage 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).^{[citation needed]}

The Shuttle would handle space station logistics, while 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. The Saturn-Shuttle concept also would have eliminated the Space Shuttle Solid Rocket Boosters that ultimately precipitated the Space Shuttle Challenger accident in 1986.

Performance[edit]

Because the shuttle orbiter would be riding piggyback on the external tank, and the need to prevent damage to the delicate thermal protection tiles, the five-engine variant of the Saturn-Shuttle would require the center engine to be shut down 45 to 50 seconds after launch, while two of the outboard engines would have to be shut down prior to staging. Once the S-IC was jettisoned, the three onboard high-energy Space Shuttle main engines would then propel the orbiter into LEO, shutting down 6.5 minutes after ignition. The external tank would then be jettisoned, as on the actually flown shuttle configuration, and the orbiter would then perform its mission.^{[citation needed]}

But because of the need to keep costs down and to allow President Richard Nixon to approve the shuttle program in 1972, NASA decided to utilize segmented solid rocket boosters similar to those used on the Titan III rocket instead of the S-IC, thus ending the Saturn program after the initial Saturn V order was completed.^{[citation needed]}

See also[edit]

• Boeing X-20 Dyna-Soar
• X-37
• Saturn V
• List of space launch system designs

External links[edit]

• Shuttle (Astronautix)

References[edit]

Further reading[edit]

• Phase B' Shuttle contractor studies 1971 - describes and shows some of the S-1C based proposals.
• Phase B' Shuttle cost tradeoffs 1971 - shows HO BRB and S-1C derived HO flyback options.