Encyclopedia Astronautica
H-1b


Rocketdyne Lox/Kerosene rocket engine. 1030.2 kN. Isp=296s. First flight 1966.

Thrust (sl): 911.900 kN (205,003 lbf). Thrust (sl): 92,986 kgf. Engine: 988 kg (2,178 lb). Chamber Pressure: 48.00 bar. Area Ratio: 8. Thrust to Weight Ratio: 106.329200404858. Coefficient of Thrust vacuum: 1.57681378520837. Coefficient of Thrust sea level: 1.4101471185417.

Unfuelled mass: 988 kg (2,178 lb).
Height: 2.20 m (7.20 ft).
Diameter: 0.82 m (2.67 ft).
Thrust: 1,030.20 kN (231,598 lbf).
Specific impulse: 296 s.
Specific impulse sea level: 262 s.
Burn time: 155 s.
Number: 72 .

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Associated Countries
See also
Associated Launch Vehicles
  • Saturn B-1 American orbital launch vehicle. Most powerful version of Saturn I considered. New low energy second stage with four H-1 engines, S-IV third stage, Centaur fourth stage. Masses, payload estimated. More...
  • Saturn A-2 American orbital launch vehicle. More powerful version of Saturn I with low energy second stage consisting of cluster of four IRBM motors and tankage, Centaur third stage. Masses, payload estimated. More...
  • Saturn IB-C American orbital launch vehicle. Douglas Studies, 1965: 4 Minuteman strap-ons; standard S-IB, S-IVB stages. More...
  • Saturn IB-CE American orbital launch vehicle. Douglas Studies, 1965: Standard Saturn IB with Centaur upper stage. More...
  • Saturn IB-D American orbital launch vehicle. Douglas Studies, 1965: Standard Saturn IB with Titan UA1205 5-segment strap-on motors. More...
  • Saturn IB American orbital launch vehicle. Improved Saturn I, with uprated first stage and Saturn IVB second stage (common with Saturn V) replacing Saturn IV. Used for earth orbit flight tests of Apollo CSM and LM. More...
  • Saturn INT-11 American orbital launch vehicle. Chrysler Studies, 1966: S-IB with 4 Titan UA1205 with standard S-IB stage, S-IVB stage, or 4 Titan UA1207 strap-ons with 20-foot stretche S-IB stage, S-IVB stage. S-IB ignition at altitude. More...
  • Saturn INT-12 American orbital launch vehicle. Chrysler Studies, 1966: S-IB with only 4 H-1 motors, with 4 Titan UA1205 with standard length S-IB stage, S-IVB stage, or 4 Titan UA1207 strap-ons with 20-foot stretche S-IB stage, S-IVB stage. S-IB ignition at sea level at same time as strap-ons. More...
  • Saturn INT-13 American orbital launch vehicle. Chrysler Studies, 1966: S-IB with 2 Titan UA1205 with standard length S-IB stage, S-IVB stage, or 2 Titan UA1207 strap-ons with 20-foot stretche S-IB stage, S-IVB stage. S-IB ignition at sea level at same time as strap-ons. More...
  • Saturn INT-14 American orbital launch vehicle. Chrysler Studies, 1966: S-IB with 4 Minuteman motors as strap-ons, with no, 10, or 20-foot stretch S-IB stages, S-IVB stage. S-IB ignition at sea level at same time as strap-ons. More...
  • Saturn INT-15 American orbital launch vehicle. Chrysler Studies, 1966: S-IB with 8 Minuteman motors as strap-ons, with no, 10, or 20-foot stretch S-IB stages, S-IVB stage. S-IB ignition at sea level at same time as strap-ons. More...

Associated Manufacturers and Agencies
Associated Propellants
  • Lox/Kerosene Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. In January 1953 Rocketdyne commenced the REAP program to develop a number of improvements to the engines being developed for the Navaho and Atlas missiles. Among these was development of a special grade of kerosene suitable for rocket engines. Prior to that any number of rocket propellants derived from petroleum had been used. Goddard had begun with gasoline, and there were experimental engines powered by kerosene, diesel oil, paint thinner, or jet fuel kerosene JP-4 or JP-5. The wide variance in physical properties among fuels of the same class led to the identification of narrow-range petroleum fractions, embodied in 1954 in the standard US kerosene rocket fuel RP-1, covered by Military Specification MIL-R-25576. In Russia, similar specifications were developed for kerosene under the specifications T-1 and RG-1. The Russians also developed a compound of unknown formulation in the 1980's known as 'Sintin', or synthetic kerosene. More...

Associated Stages
  • Saturn IB Lox/Kerosene propellant rocket stage. Loaded/empty mass 448,648/41,594 kg. Thrust 8,241.76 kN. Vacuum specific impulse 296 seconds. Configuration as flown, Saturn IB. More...
  • Saturn IB-11 Lox/Kerosene propellant rocket stage. Loaded/empty mass 505,953/48,545 kg. Thrust 8,241.76 kN. Vacuum specific impulse 296 seconds. 20 foot stretch of Saturn IB for use with UA1207 7 segment solid rocket strap-on units. More...
  • Saturn IB-15 Lox/Kerosene propellant rocket stage. Loaded/empty mass 478,103/45,873 kg. Thrust 8,241.76 kN. Vacuum specific impulse 296 seconds. 10 foot stretch of Saturn IB. Not found useful in any configuration except with Minuteman first-stage strap-ons to augment thrust. More...
  • Saturn S-1B-4 Lox/Kerosene propellant rocket stage. Loaded/empty mass 444,700/37,600 kg. Thrust 4,120.70 kN. Vacuum specific impulse 296 seconds. Chrysler Studies, 1966: S-1B with 4 H-1's for use with Titan UA1205 strap-ons More...

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