Saturn-Shuttle

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]
[edit on Wikidata]

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]