Encyclopedia Astronautica
Saturn V-D



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Saturn V 260" SRB
Saturn V 260 inch strapons
Credit: © Mark Wade
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Saturn II stage
Credit: © Mark Wade
American orbital launch vehicle. MSFC study, 1968. Rehashed the Boeing 1967 studies, covering a variety of stage stretches and 120, 156, or 260 inch solid rocket boosters, but with S-ID stage-and-a-half first stage.

LEO Payload: 326,500 kg (719,800 lb) to a 185 km orbit at 28.00 degrees. Payload: 112,000 kg (246,000 lb) to a translunar trajectory in 1985 dollars. Flyaway Unit Cost $: 736.600 million.

Stage Data - Saturn V-D

  • Stage 0. 4 x 260 inch solid FL. Gross Mass: 1,648,355 kg (3,634,000 lb). Empty Mass: 156,126 kg (344,198 lb). Thrust (vac): 35,391.395 kN (7,956,302 lbf). Isp: 263 sec. Burn time: 114 sec. Isp(sl): 238 sec. Diameter: 6.60 m (21.60 ft). Span: 6.60 m (21.60 ft). Length: 30.48 m (99.99 ft). Propellants: Solid. No Engines: 1. Engine: AJ-260X. Status: Study 1968. Comments: 260 inch solid booster - full length. These would have been the flight configuration motors, replacing the Saturn V first stage or being used as booster motors in various Uprated Saturn and Nova configurations.
  • Stage 1. 1 x Saturn S-ID Booster. Gross Mass: 67,100 kg (147,900 lb). Empty Mass: 67,100 kg (147,900 lb). Thrust (vac): 30,962.500 kN (6,960,647 lbf). Isp: 304 sec. Burn time: 154 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.01 m (62.36 ft). Length: 42.07 m (138.02 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: F-1. Status: Study 1967. Comments: Boeing studies, 1967:'Stage and a half' S-1C with four outboard F-1's jettisoned and inboard F-1 functioning as sustainer as in Atlas. Booster half stage recoverable. Mass estimated based on double mass of four F-1's (based on Atlas example).
  • Stage 2. 1 x Saturn S-ID Sustainer. Gross Mass: 2,219,100 kg (4,892,200 lb). Empty Mass: 68,100 kg (150,100 lb). Thrust (vac): 7,740.300 kN (1,740,089 lbf). Isp: 304 sec. Burn time: 315 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.01 m (62.36 ft). Length: 42.07 m (138.02 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: F-1. Status: Study 1967. Comments: Boeing studies, 1967:'Stage and a half' S-1C with four outboard F-1's jettisoned and inboard F-1 functioning as sustainer as in Atlas. Booster half stage burns 124 seconds in this configuration.
  • Stage 3. 1 x Saturn II. Gross Mass: 490,778 kg (1,081,980 lb). Empty Mass: 39,048 kg (86,086 lb). Thrust (vac): 5,165.790 kN (1,161,316 lbf). Isp: 421 sec. Burn time: 390 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: Out of Production.
  • Stage 4. 1 x Saturn IVB (S-V). Gross Mass: 119,900 kg (264,300 lb). Empty Mass: 13,300 kg (29,300 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 V version of S-IVB stage.

Status: Study 1968.
Gross mass: 9,882,100 kg (21,786,300 lb).
Payload: 326,500 kg (719,800 lb).
Height: 102.00 m (334.00 ft).
Diameter: 10.06 m (33.00 ft).
Thrust: 161,846.50 kN (36,384,541 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • AJ-260X Aerojet solid rocket engine. 35,390.7 kN. Study 1967. Full length version of 260 inch motor tested in 1960's. Proposed for use in various Saturn and Nova configurations. Isp=263s. More...

See also
  • 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...

Associated Stages
  • 260 inch solid FL Solid propellant rocket stage. Loaded/empty mass 1,648,355/156,126 kg. Thrust 35,391.40 kN. Vacuum specific impulse 263 seconds. 260 inch solid booster - full length. These would have been the flight configuration motors, replacing the Saturn V first stage or being used as booster motors in various Uprated Saturn and Nova configurations. More...
  • Saturn II Lox/LH2 propellant rocket stage. Loaded/empty mass 490,778/39,048 kg. Thrust 5,165.79 kN. Vacuum specific impulse 421 seconds. Configuration as flown. More...
  • Saturn IVB (S-V) Lox/LH2 propellant rocket stage. Loaded/empty mass 119,900/13,300 kg. Thrust 1,031.60 kN. Vacuum specific impulse 421 seconds. Saturn V version of S-IVB stage for use with upper stage. More...
  • Saturn S-ID Booster Lox/Kerosene propellant rocket stage. Loaded/empty mass 67,100/67,100 kg. Thrust 30,962.50 kN. Vacuum specific impulse 304 seconds. Boeing studies, 1967:'Stage and a half' S-1C with four outboard F-1's jettisoned and inboard F-1 functioning as sustainer as in Atlas. Booster half stage recoverable. Mass estimated based on double mass of four F-1's (based on Atlas example). More...
  • Saturn S-ID Sustainer Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,219,100/68,100 kg. Thrust 7,740.30 kN. Vacuum specific impulse 304 seconds. Boeing studies, 1967:'Stage and a half' S-1C with four outboard F-1's jettisoned and inboard F-1 functioning as sustainer as in Atlas. Booster half stage burns 124 seconds in this configuration. More...

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