Rocket Engine, Liquid Fuel, J-2

The J-2 liquid propellant rocket engine, using liquid hydrogen and liquid oxygen, was the powerplant for the second and third stages of the Saturn V launch vehicle that took astronauts to the Moon in the Apollo program. The engine shown here was an early developmental model and produced 200,000 pounds of vacuum thrust. It made three tests for a total duration firing time of 291 seconds.

The Saturn V's second stage used a cluster of five J-2s, while the third stage had one J-2 that was gimballed, or steerable, so that this stage could be steered on its way to the Moon. The J-2 was developed and built by the Rocketddyne Division of the Rockwell International Corporation. NASA transferred this J-2 engine 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
1964

Type
PROPULSION-Rocket Engines

Materials
Stainless steel and other metals.
Dimensions
Overall: 132 in. long x 80 3/8 in. diameter, 5740 lb. (335.28 x 204.22cm, 2603.6kg)

The J-2 liquid propellant rocket engine, using liquid hydrogen and liquid oxygen, was the powerplant for the second and third stages of the Saturn V launch vehicle that took astronauts to the Moon in the Apollo program. The engine shown here was an early developmental model and produced 200,000 pounds of vacuum thrust. It made three tests for a total duration firing time of 291 seconds.

The Saturn V's second stage used a cluster of five J-2s, while the third stage had one J-2 that was gimballed, or steerable, so that this stage could be steered on its way to the Moon. The J-2 was developed and built by the Rocketddyne Division of the Rockwell International Corporation. NASA transferred this J-2 engine 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
1964

Type
PROPULSION-Rocket Engines

Materials
Stainless steel and other metals.
Dimensions
Overall: 132 in. long x 80 3/8 in. diameter, 5740 lb. (335.28 x 204.22cm, 2603.6kg)

ID: A19700261000