Rocket Engine, Liquid Fuel, H-1, Cutaway

Rocket Engine, Liquid Fuel, H-1, Cutaway

     

The H-1 liquid-fuel rocket engine was the first stage powerplant of the Saturn 1 and Saturn 1B launch vehicles, precursors to the Saturn V that took men to the Moon in the Apollo program. The Saturn 1 and Saturn 1B were each fitted with eight H-1 engines in their first stages. The engine used RP-1 (kerosene) and liquid oxygen. The model shown here may be the second variation which produced 188,000 pounds of thrust. The Saturn 1 first flew in 1961 while the last Saturn 1B was flown in 1975 for the low-Earth orbit Apollo-Soyuz Test Project. This cutaway version of the engine was transferred to the Smithsonian in 1970 from the NASA Marshall Space Flight Center.

Transferred from the National Aeronautics and Space Administration

Country of Origin
United States of America

Manufacturer
Rocketdyne Division, Rockwell International Corporation

Date
ca. 1958-1969

Type
PROPULSION-Rocket Engines

Materials
Chamber and nozzle coolant passages 347 stainless steel. Propellant tanks, lines, and valves, stainless steel. Pumps, aluminum alloys; turbine, Hastealloy. Injector, OHFC copper and 347 stainless steel.
Combustion chamber made of 292 stainless steel tubes. The assembly, except for inlet manifold, was furnaced brazed with gold brazing alloy. Injectors, furnaced brazed.
Dimensions
Overall: 8 ft. 4 in. long x 3 ft. 11 in. diameter (254 x 119.38cm)

The H-1 liquid-fuel rocket engine was the first stage powerplant of the Saturn 1 and Saturn 1B launch vehicles, precursors to the Saturn V that took men to the Moon in the Apollo program. The Saturn 1 and Saturn 1B were each fitted with eight H-1 engines in their first stages. The engine used RP-1 (kerosene) and liquid oxygen. The model shown here may be the second variation which produced 188,000 pounds of thrust. The Saturn 1 first flew in 1961 while the last Saturn 1B was flown in 1975 for the low-Earth orbit Apollo-Soyuz Test Project. This cutaway version of the engine was transferred to the Smithsonian in 1970 from the NASA Marshall Space Flight Center.

Transferred from the National Aeronautics and Space Administration

Country of Origin
United States of America

Manufacturer
Rocketdyne Division, Rockwell International Corporation

Date
ca. 1958-1969

Type
PROPULSION-Rocket Engines

Materials
Chamber and nozzle coolant passages 347 stainless steel. Propellant tanks, lines, and valves, stainless steel. Pumps, aluminum alloys; turbine, Hastealloy. Injector, OHFC copper and 347 stainless steel.
Combustion chamber made of 292 stainless steel tubes. The assembly, except for inlet manifold, was furnaced brazed with gold brazing alloy. Injectors, furnaced brazed.
Dimensions
Overall: 8 ft. 4 in. long x 3 ft. 11 in. diameter (254 x 119.38cm)

ID: A19700285000