Encyclopedia Astronautica
260 inch solid TL


Solid propellant rocket stage. Loaded/empty mass 561,000/60,600 kg. Thrust 10,105.31 kN. Vacuum specific impulse 275 seconds. Study NASA 1969

Status: Study NASA 1969.
Gross mass: 561,000 kg (1,236,000 lb).
Unfuelled mass: 60,600 kg (133,600 lb).
Height: 21.65 m (71.03 ft).
Diameter: 6.60 m (21.60 ft).
Span: 6.60 m (21.60 ft).
Thrust: 10,105.31 kN (2,271,764 lbf).
Specific impulse: 275 s.
Burn time: 130 s.

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Associated Countries
Associated Engines
  • AJ-260-1/3 Aerojet solid rocket engine. 10,105 kN. Design concept 1960's. Isp=275s. Used on Saturn INT-05B launch vehicle. More...

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...

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