Encyclopedia Astronautica
Saturn MLV-V-4(S)



s1cdet.jpg
S-1C details
Credit: © Mark Wade
American orbital launch vehicle. MSFC study, 1965. Saturn V core, strengthened but not stretched, with 4 Titan UA1205 strap-on solid rocket boosters.

LEO Payload: 118,000 kg (260,000 lb) to a 185 km orbit at 28.00 degrees. Payload: 52,900 kg (116,600 lb) to a translunar trajectory in 1985 dollars. Flyaway Unit Cost $: 463.420 million.

Stage Data - Saturn MLV-V-4(S)

  • Stage 0. 4 x Titan UA1205. Gross Mass: 226,233 kg (498,758 lb). Empty Mass: 33,798 kg (74,511 lb). Thrust (vac): 5,849.411 kN (1,315,000 lbf). Isp: 263 sec. Burn time: 115 sec. Isp(sl): 238 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 25.91 m (85.00 ft). Propellants: Solid. No Engines: 1. Engine: UA1205. Status: Out of Production.
  • Stage 1. 1 x Saturn IC. Gross Mass: 2,286,217 kg (5,040,245 lb). Empty Mass: 135,218 kg (298,104 lb). Thrust (vac): 38,703.160 kN (8,700,816 lbf). Isp: 304 sec. Burn time: 161 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 42.06 m (137.99 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1. Status: Out of Production.
  • Stage 2. 1 x Saturn MS-II-4(S)B. Gross Mass: 494,100 kg (1,089,300 lb). Empty Mass: 42,300 kg (93,200 lb). Thrust (vac): 5,169.000 kN (1,162,037 lbf). Isp: 421 sec. Burn time: 355 sec. Isp(sl): 200 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 24.84 m (81.49 ft). Propellants: Lox/LH2. No Engines: 5. Engine: J-2. Status: Study Boeing 1967. Comments: Standard S-II but with structural strength increased from 86% to 502% depending on station, resulting in 8.6% increase in empty weight.
  • Stage 3. 1 x Saturn MS-IVB-1. Gross Mass: 120,500 kg (265,600 lb). Empty Mass: 13,900 kg (30,600 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 475 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 18.08 m (59.31 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Study 1965. Comments: Marshall studies, 1965: S-IVB structurally strengthened to handle larger payloads, otherwise unchanged.

Status: Study 1965.
Gross mass: 3,947,350 kg (8,702,410 lb).
Payload: 118,000 kg (260,000 lb).
Height: 102.00 m (334.00 ft).
Diameter: 10.06 m (33.00 ft).
Thrust: 54,911.50 kN (12,344,596 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • F-1 Rocketdyne Lox/Kerosene rocket engine. 7740.5 kN. Isp=304s. Largest liquid rocket engine ever developed and flown. Severe combustion stability problems were solved during development and it never failed in flight. First flight 1967. More...
  • UA1205 CSD solid rocket engine. 5849.3 kN. Out of production. Isp=263s. Strap-on boosters for Titan 3C, 3D, 3E. Proposed for advanced Saturn IB versions. First flight 1965. More...

See also
  • Saturn The Saturn launch vehicle was the penultimate expression of the Peenemuende Rocket Team's designs for manned exploration of the moon and Mars. Numerous designs and variants were studied, but in the end only three models - the Saturn I, IB, and V - were built in the 1960's, and then only used to support NASA's Apollo moon landing program. More...
  • Saturn V America's booster for the Apollo manned lunar landing. The design was frozen before a landing mode was selected; the Saturn V could be used for either Earth-Orbit-Rendezvous or Lunar-Orbit-Rendezvous methods. The vehicle ended up with the same payload capability as the 'too large' Nova. The basic diameter was dictated by the ceiling height at the Michoud factory selected for first stage manufacture. Despite the study of innumerable variants, production was ended after only 12 were built and America spent the next fifty years in a pointless slow-motion withdrawal from manned space exploration. More...

Associated Manufacturers and Agencies
  • Von Braun American manufacturer of rockets and spacecraft. Von Braun, USA. More...

Associated Stages
  • Saturn IC Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,286,217/135,218 kg. Thrust 38,703.16 kN. Vacuum specific impulse 304 seconds. Configuration as flown. More...
  • Saturn MS-II-4(S)B Lox/LH2 propellant rocket stage. Loaded/empty mass 494,100/42,300 kg. Thrust 5,169.00 kN. Vacuum specific impulse 421 seconds. Standard S-II but with structural strength increased from 86% to 502% depending on station, resulting in 8.6% increase in empty weight. More...
  • Saturn MS-IVB-1 Lox/LH2 propellant rocket stage. Loaded/empty mass 120,500/13,900 kg. Thrust 1,031.60 kN. Vacuum specific impulse 421 seconds. Marshall studies, 1965: S-IVB structurally strengthened to handle larger payloads, otherwise unchanged More...
  • Titan UA1205 Solid propellant rocket stage. Loaded/empty mass 226,233/33,798 kg. Thrust 5,849.41 kN. Vacuum specific impulse 263 seconds. More...

Home - Browse - Contact
© / Conditions for Use