Encyclopedia Astronautica
Goose II


RO solid rocket engine. 22 kN.

Gross mass: 300 kg (660 lb).
Unfuelled mass: 95 kg (209 lb).
Height: 3.40 m (11.10 ft).
Diameter: 0.26 m (0.85 ft).
Thrust: 22.00 kN (4,945 lbf).
Burn time: 17 s.

More... - Chronology...


Associated Countries
See also
Associated Manufacturers and Agencies
Associated Propellants
  • Solid Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...

Associated Stages
  • INTA-255-1 Solid rocket stage. 22.00 kN (4,946 lbf) thrust. Mass 300 kg (661 lb). More...

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