Saturn 1B/120-7 seg
Saturn 1B with 120 inch 7 segment strap on
Credit: © Mark Wade
North American study, 1966. Saturn variant with a modified S-II first stage with seven high-performance HG-3 engines; S-IVB second stage. Poor performance and cost-effectiveness and not studied further.
LEO Payload: 42,000 kg (92,000 lb) to a 185 km orbit at 28.00 degrees.
Stage Data - Saturn INT-17
- Stage 1. 1 x Saturn II-INT-17. Gross Mass: 495,000 kg (1,091,000 lb). Empty Mass: 48,000 kg (105,000 lb). Thrust (vac): 9,713.400 kN (2,183,659 lbf). Isp: 450 sec. Burn time: 200 sec. Isp(sl): 275 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: 7. Engine: HG-3-SL. Status: Study 1966. Comments: Saturn II modifed with reduced expansion ratio HG-3 high pressure engines for use a first stage (sea level launch).
- Stage 2. 1 x Saturn IVB (S-IB). Gross Mass: 118,800 kg (261,900 lb). Empty Mass: 12,900 kg (28,400 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: 17.80 m (58.30 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Out of Production. Comments: Saturn IB version of S-IVB stage. Due to lower payload payload, 300 kg saving in structure compared to Saturn V version. Due to deletion of restart requirement, 700 kg saving in propulsion system (primarily reduction in helium for restart).
Status: Study 1966.
More... - Chronology...
Gross mass: 504,400 kg (1,112,000 lb).
Payload: 42,000 kg (92,000 lb).
Height: 51.00 m (167.00 ft).
Diameter: 10.06 m (33.00 ft).
Thrust: 5,936.01 kN (1,334,468 lbf).
Apogee: 185 km (114 mi).
HG-3-SL Rocketdyne lox/lh2 rocket engine. 1387 kN. Study 1966. Isp=450s. High-performance high-pressure chamber engine developed from the J-2, fitted with lower-expansion nozzle for sea level use on Saturn INT-17. Technology led to Space Shuttle Main Engines. 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...
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...
Associated Manufacturers and Agencies
Von Braun American manufacturer of rockets and spacecraft. Von Braun, USA. More...
Saturn IVB (S-IB) Lox/LH2 propellant rocket stage. Loaded/empty mass 118,800/12,900 kg. Thrust 1,031.60 kN. Vacuum specific impulse 421 seconds. Saturn IB version of S-IVB stage. Due to lower payload payload, 300 kg saving in structure compared to Saturn V version. Due to deletion of restart requirement, 700 kg saving in propulsion system (primarily reduction in helium for restart). More...
Saturn II-INT-17 Lox/LH2 propellant rocket stage. Loaded/empty mass 495,000/48,000 kg. Thrust 9,713.40 kN. Vacuum specific impulse 450 seconds. Saturn II modifed with reduced expansion ratio HG-3 high pressure engines for use a first stage (sea level launch). More...
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