Encyclopedia Astronautica
Saturn V-24(L)


American orbital launch vehicle. Boeing study, 1967. 4 260 inch liquid propellant boosters (each with 2 F-1A).; Saturn IC stretched 336 inches with 6.0 million pounds propellant and 5 F-1A engines; S-II stretched 156 inches with 1.2 million pounds propellant and 5 HG-3 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 HG-3 engine. Not studied in detail since vehicle height of 600 feet with payload exceeded study limit of 410 feet.

LEO Payload: 435,300 kg (959,600 lb) to a 185 km orbit at 28.00 degrees. Payload: 185,900 kg (409,800 lb) to a translunar trajectory.

Stage Data - Saturn V-24(L)

  • Stage 0. 4 x Saturn MS-LRB-23(L). Gross Mass: 874,100 kg (1,927,000 lb). Empty Mass: 18,100 kg (39,900 lb). Thrust (vac): 15,486.600 kN (3,481,526 lbf). Isp: 304 sec. Burn time: 162 sec. Isp(sl): 265 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 47.85 m (156.98 ft). Propellants: Lox/Kerosene. No Engines: 2. Engine: F-1. Status: Study Boeing 1967. Comments: Liquid rocket booster strap-ons using 2 F-1's.
  • Stage 1. 1 x Saturn MS-IC-1. Gross Mass: 2,694,703 kg (5,940,803 lb). Empty Mass: 169,719 kg (374,166 lb). Thrust (vac): 45,948.754 kN (10,329,691 lbf). Isp: 310 sec. Burn time: 158 sec. Isp(sl): 270 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 48.15 m (157.97 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1A. Status: Study NASA 1966. Comments: Basic Saturn IC stretched 240 inches with F-1A engines uprated 20% in thrust and 6 second improvement in specific impulse.
  • 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-1A. Gross Mass: 179,200 kg (395,000 lb). Empty Mass: 20,400 kg (44,900 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 625 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 22.82 m (74.86 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Study Boeing 1967. Comments: S-IVB with 16.5 foot stretch, 350,000 pounds propellant, standard J-2 engine.

Status: Study 1967.
Gross mass: 7,386,760 kg (16,285,010 lb).
Payload: 435,300 kg (959,600 lb).
Height: 180.00 m (590.00 ft).
Diameter: 10.06 m (33.00 ft).
Thrust: 94,019.40 kN (21,136,402 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • F-1A Rocketdyne Lox/Kerosene rocket engine. 9189.6 kN. Study 1968. Designed for booster applications. Gas generator, pump-fed. Isp=310s. 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 MS-LRB-23(L) Lox/Kerosene propellant rocket stage. Loaded/empty mass 874,100/18,100 kg. Thrust 15,486.60 kN. Vacuum specific impulse 304 seconds. Liquid rocket booster strap-ons using 2 F-1's. More...
  • Saturn MS-IVB-1A Lox/LH2 propellant rocket stage. Loaded/empty mass 179,200/20,400 kg. Thrust 1,031.60 kN. Vacuum specific impulse 421 seconds. S-IVB with 16.5 foot stretch, 350,000 pounds propellant, standard J-2 engine. More...
  • Saturn MS-IC-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,694,703/169,719 kg. Thrust 45,948.75 kN. Vacuum specific impulse 310 seconds. Basic Saturn IC stretched 240 inches with F-1A engines uprated 20% in thrust and 6 second improvement in specific impulse. 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...

Home - Browse - Contact
© / Conditions for Use