Rocket Motor, Solid Fuel, X-259

Rocket Motor, Solid Fuel, X-259

     

This is the X-259, or Antares II, the third-stage, solid-fuel rocket motor for the all-solid fuel U.S. Scout launch vehicle. Antares II produced about 23,500 pounds of thrust. Like the other stages of the Scout, Antares was named after a star constellation. (The Scout's first, second, and fourth stages were the Algol, Castor, and Altair, respectively.)

The Scout was conceived in 1958 as a low-cost launch vehicle for light payloads. The first Scout was launched in 1960 and continued as a very successful vehicle. This object was donated to the Smithsonian in 1968 by the Alleghany Ballistic Laboratory.

Gift of Alleghany Ballistics Laboratory

Country of Origin
United States of America

Manufacturer
Alleghany Ballistics Laboratory, Hercules Incorporated

Date
ca. 1968

Type
PROPULSION-Rocket Engines

Materials
Filament-wound, resin-bonded glass fiber body with asbestos-filled SBR rubber. Windings by circumferential wraps of glass fiber coated with catalyzed epoxy resin. Aluminum nozzle fixture rings. Aluminum skirt rings bolted underneath forward dome.
Dimensions
Overall: 2 ft. 4 in. wide x 9 ft. 6 1/2 in. long x 2 ft. 5 in. diameter, 200 lb. (71.12 x 290.83 x 73.66cm, 90.7kg)

This is the X-259, or Antares II, the third-stage, solid-fuel rocket motor for the all-solid fuel U.S. Scout launch vehicle. Antares II produced about 23,500 pounds of thrust. Like the other stages of the Scout, Antares was named after a star constellation. (The Scout's first, second, and fourth stages were the Algol, Castor, and Altair, respectively.)

The Scout was conceived in 1958 as a low-cost launch vehicle for light payloads. The first Scout was launched in 1960 and continued as a very successful vehicle. This object was donated to the Smithsonian in 1968 by the Alleghany Ballistic Laboratory.

Gift of Alleghany Ballistics Laboratory

Country of Origin
United States of America

Manufacturer
Alleghany Ballistics Laboratory, Hercules Incorporated

Date
ca. 1968

Type
PROPULSION-Rocket Engines

Materials
Filament-wound, resin-bonded glass fiber body with asbestos-filled SBR rubber. Windings by circumferential wraps of glass fiber coated with catalyzed epoxy resin. Aluminum nozzle fixture rings. Aluminum skirt rings bolted underneath forward dome.
Dimensions
Overall: 2 ft. 4 in. wide x 9 ft. 6 1/2 in. long x 2 ft. 5 in. diameter, 200 lb. (71.12 x 290.83 x 73.66cm, 90.7kg)

ID: A19680240000