H-1b

Designer: Rocketdyne. Propellants: Lox/Kerosene. Thrust(vac): 1,030.200 kN (231,598 lbf). Thrust(sl): 911.900 kN (205,003 lbf). Isp: 296 sec. Isp (sea level): 262 sec. Burn time: 155 sec. Mass Engine: 988 kg (2,178 lb). Diameter: 0.82 m (2.67 ft). Length: 2.20 m (7.20 ft). Chambers: 1. Chamber Pressure: 48.00 bar. Area Ratio: 8.00. Thrust to Weight Ratio: 106.33. Country: USA. First Flight: 1966. Last Flight: 1975. Flown: 72.

H-1b used on Rocket Stages

Used on stage: Saturn IB. on launch vehicle: Saturn A-2.

Used on stage: Saturn IB. on launch vehicle: Saturn B-1.

Used on stage: Saturn IB. on launch vehicle: Saturn IB.

Used on stage: Saturn IB. on launch vehicle: Saturn IB-C.

Used on stage: Saturn IB. on launch vehicle: Saturn IB-CE.

Used on stage: Saturn IB. on launch vehicle: Saturn IB-D.

Used on stage: Saturn IB-11. on launch vehicle: Saturn INT-11.

Used on stage: Saturn IB-11. on launch vehicle: Saturn INT-13.

Used on stage: Saturn IB-11. on launch vehicle: Saturn INT-14.

Used on stage: Saturn IB-15. on launch vehicle: Saturn INT-15.

Used on stage: Saturn S-1B-4 H-1. on launch vehicle: Saturn INT-12.

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