Social Impact, Memorabilia & Toys, General [Oversize]
Collection Creator:
National Air and Space Museum. Archives Division. Search this
Type:
Archival materials
Scope and Contents:
Soviet paper hat, circa July 1975, memorabilia from the Apollo-Soyuz Test Project. Front features mission insignia in English and Russian writing with an image of the earth and the mission spacecraft. Reverse has red and white Apollo insignia.
Collection Restrictions:
The majority of the Archives Department's public reference requests can be answered using material in these files, which may be accessed through the Reading Room at the Steven F. Udvar-Hazy Center in Chantilly, Virginia. More specific information can be requested by contacting the Archives Research Request.
Rocketdyne Division, Rockwell International Search this
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: 5 ft. 3/8 in. wide x 6 ft. 1 1/4 in. long x 3 ft. 11 in. diameter, 2000 lb. (153.42 x 186.06 x 119.38cm, 907.2kg)
Type:
PROPULSION-Rocket Engines
Country of Origin:
United States of America
Date:
ca. 1958-1975
Credit Line:
Transferred from the National Aeronautics and Space Administration
Rocketdyne Division, Rockwell International Search this
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: 8ft 4in. x 3ft 11in., 1532lb. (2,300 lbs in crate) (254 x 119.38cm, 694.9kg)
Type:
PROPULSION-Rocket Engines
Country of Origin:
United States of America
Date:
ca. 1958-1969
Credit Line:
Transferred from the National Aeronautics and Space Administration
Rocketdyne Division, Rockwell International Search this
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, furanced brazed.
Dimensions:
Overall: 8 ft. 4 in. long x 3 ft. 11 in. diameter (254 x 119.38cm)
Type:
PROPULSION-Rocket Engines
Country of Origin:
United States of America
Date:
ca. 1958-1975
Credit Line:
Transferred from the National Aeronautics and Space Administration
Rocketdyne Division, Rockwell International Search this
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)
Type:
PROPULSION-Rocket Engines
Country of Origin:
United States of America
Date:
ca. 1958-1969
Credit Line:
Transferred from the National Aeronautics and Space Administration
Rocketdyne Division, Rockwell International Search this
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.
Dessicant holders on each side of rocket plumbing, with red plastic protective covers; bundle of wires in white plastic isulation adjacent to red desicant holders; another bundle of wires with white plastic insulation, in back of plumbing,
Dimensions:
Overall: 5ft 3 1/2in. x 4ft 5 3/4in. x 8ft 4in. (161.3 x 136.5 x 254cm)
Type:
PROPULSION-Rocket Engines
Country of Origin:
United States of America
Date:
ca. 1959-1961
Credit Line:
Transferred from the National Aeronautics and Space Administration
Rocketdyne Division, Rockwell International Search this
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: 75 in. tall x 98 in. long x 47 in. diameter, 1870 lb. (190.5 x 248.92 x 119.38cm, 848.2kg)
Type:
PROPULSION-Rocket Engines
Country of Origin:
United States of America
Date:
ca. 1958-1975
Credit Line:
Transferred from the National Aeronautics and Space Administration
