Rocket Engine, Liquid Fuel, H-1

The H-1 liquid-fuel rocket engine was the first stage power plant for the Saturn 1 and Saturn 1B launch vehicles, the precursors to the Saturn V, the rocket that propelled astronauts 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 as fuel. The Saturn 1 first flew in 1961 while the last Saturn 1B was flown in 1975 for the Apollo-Soyuz Test Project. The Rocketdyne Division of Rockwell International donated this engineering model to the Smithsonian Institution in 1976.

Gift of the Rocketdyne Division of Rockwell International

Country of Origin
United States of America

Manufacturer
Rocketdyne Division, Rockwell International Corporation

Date
ca. 1958-1975

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. long x 47 in. diameter (254 x 119.38cm)

The H-1 liquid-fuel rocket engine was the first stage power plant for the Saturn 1 and Saturn 1B launch vehicles, the precursors to the Saturn V, the rocket that propelled astronauts 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 as fuel. The Saturn 1 first flew in 1961 while the last Saturn 1B was flown in 1975 for the Apollo-Soyuz Test Project. The Rocketdyne Division of Rockwell International donated this engineering model to the Smithsonian Institution in 1976.

Gift of the Rocketdyne Division of Rockwell International

Country of Origin
United States of America

Manufacturer
Rocketdyne Division, Rockwell International Corporation

Date
ca. 1958-1975

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. long x 47 in. diameter (254 x 119.38cm)

ID: A19760772000