Rocket Engine, Liquid Fuel, Attitude Control and Ullage, Titan IIIE Transtage

This is the Attitude Control and Ullage System module for the Titan III-E transtage. The Titan III-E was a modified Titan missile used to launch deep space probes and satellites into geosynchronous orbits. The Control and Ullage System provided roll and yaw control for the vehicle. The Titan III-E made its first successful launch in 1974. Among the vehicle's most significant missions occurred in August and September 1975 when it launched the Viking 1 and 2 spacecraft to Mars, respectively. This Attitude Control System was transferred from the U.S. Air Force to the Smithsonian Institution in 1970.

Transferred from the U.S. Air Force

Country of Origin
United States of America

Manufacturer
Rocketdyne, Division of North American Aviation Co.

Date
1967

Type
PROPULSION-Rocket Engines

Materials
Overall, stainless steel; combustion chambers, phenolic; rubber nozzle protective covers for each of three nozzles; steel clamps around protective covers; most of the propellant lines, brass colored, and probably of brass; two thinest lines, aluminum colored and probably of aluminum; one red plastic protective cap, loose, attached to main assembly with adhesive tape; dessicant in small brown paper bags underneath each nozzle protective cap.
Dimensions
Overall: 5 1/2 in. tall x 23 3/4 in. long x 18 1/2 in. wide, 26 lb. (13.97 x 60.33 x 46.99cm, 11.8kg)
Other (each nozzle): 3 1/4 in. outside diamter x 5/8 in. thick (8.26 x 1.59cm)

This is the Attitude Control and Ullage System module for the Titan III-E transtage. The Titan III-E was a modified Titan missile used to launch deep space probes and satellites into geosynchronous orbits. The Control and Ullage System provided roll and yaw control for the vehicle. The Titan III-E made its first successful launch in 1974. Among the vehicle's most significant missions occurred in August and September 1975 when it launched the Viking 1 and 2 spacecraft to Mars, respectively. This Attitude Control System was transferred from the U.S. Air Force to the Smithsonian Institution in 1970.

Transferred from the U.S. Air Force

Country of Origin
United States of America

Manufacturer
Rocketdyne, Division of North American Aviation Co.

Date
1967

Type
PROPULSION-Rocket Engines

Materials
Overall, stainless steel; combustion chambers, phenolic; rubber nozzle protective covers for each of three nozzles; steel clamps around protective covers; most of the propellant lines, brass colored, and probably of brass; two thinest lines, aluminum colored and probably of aluminum; one red plastic protective cap, loose, attached to main assembly with adhesive tape; dessicant in small brown paper bags underneath each nozzle protective cap.
Dimensions
Overall: 5 1/2 in. tall x 23 3/4 in. long x 18 1/2 in. wide, 26 lb. (13.97 x 60.33 x 46.99cm, 11.8kg)
Other (each nozzle): 3 1/4 in. outside diamter x 5/8 in. thick (8.26 x 1.59cm)

ID: A19700336000