Rocket Engine, Liquid Fuel, F-1

Rocket Engine, Liquid Fuel, F-1

     

This is an Rocketdyne F-1 rocket engine meant as a flight spare for either the Apollo 18 or 19 manned missions to the Moon. The engine underwent eight start tests in 1966 for a total firing time of about 500 seconds. However, the Apollo 18 and 19 missions were later cancelled and Apollo 17 was the last manned flight to the Moon.

The first stage of the Apollo Project's Saturn V used five F-1s. Each F-1 produced 1.5 million pounds of thrust for a total lift-off thrust of 7.5 million pounds. The fully-fueled Saturn V weighed 6.1 million pounds. The F-1 used RP-1, a type of kerosene, and liquid oxygen as the propellants.

The engine shown here was donated to the Smithsonian by NASA/Marshall Space Flight Center in 2004.

Transferred from NASA/Marshall Space Flight Center

Country of Origin
United States of America

Manufacturer
Rocketdyne, Division of North American Aviation Co.

Date
ca. 1966-1967

Type
PROPULSION-Rocket Engines

Materials
Overall: Non-ferrous
Aluminum pipe along chamber: Non-ferrous valves
Actuators: Steel
Structual Access Door at front, track-shaped: Steel
Dimensions
Overall: 10ft 1in. (307.34cm)

This is an Rocketdyne F-1 rocket engine meant as a flight spare for either the Apollo 18 or 19 manned missions to the Moon. The engine underwent eight start tests in 1966 for a total firing time of about 500 seconds. However, the Apollo 18 and 19 missions were later cancelled and Apollo 17 was the last manned flight to the Moon.

The first stage of the Apollo Project's Saturn V used five F-1s. Each F-1 produced 1.5 million pounds of thrust for a total lift-off thrust of 7.5 million pounds. The fully-fueled Saturn V weighed 6.1 million pounds. The F-1 used RP-1, a type of kerosene, and liquid oxygen as the propellants.

The engine shown here was donated to the Smithsonian by NASA/Marshall Space Flight Center in 2004.

Transferred from NASA/Marshall Space Flight Center

Country of Origin
United States of America

Manufacturer
Rocketdyne, Division of North American Aviation Co.

Date
ca. 1966-1967

Type
PROPULSION-Rocket Engines

Materials
Overall: Non-ferrous
Aluminum pipe along chamber: Non-ferrous valves
Actuators: Steel
Structual Access Door at front, track-shaped: Steel
Dimensions
Overall: 10ft 1in. (307.34cm)

ID: D20050101000