Rocket Engine, Liquid Fuel, H-1

Rocket Engine, Liquid Fuel, H-1

     

The H-1 liquid-fuel rocket engine was the first stage powerplant for the Saturn 1 and Saturn 1B launch vehicles, the precursors to the Saturn V which 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 uses RP-1 (kerosene) and liquid oxygen. The model shown here may be the second variation that produced 188,000 pounds of thrust. The Saturn 1, with its eight H-1's, first flew in 1961 while the last Saturn 1B was flown in 1975 for the low-Earth orbit Apollo-Soyuz Test Project. This H-1 was transferred to from NASA to the Smithsonian in 1970.

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: 100 in. tall x 47 in. diameter (254 x 119.38cm)

The H-1 liquid-fuel rocket engine was the first stage powerplant for the Saturn 1 and Saturn 1B launch vehicles, the precursors to the Saturn V which 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 uses RP-1 (kerosene) and liquid oxygen. The model shown here may be the second variation that produced 188,000 pounds of thrust. The Saturn 1, with its eight H-1's, first flew in 1961 while the last Saturn 1B was flown in 1975 for the low-Earth orbit Apollo-Soyuz Test Project. This H-1 was transferred to from NASA to the Smithsonian in 1970.

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: 100 in. tall x 47 in. diameter (254 x 119.38cm)

ID: A19700258000