Encyclopedia Astronautica
AJ-260-1/3

Aerojet solid rocket engine. 10,105 kN. Design concept 1960's. Isp=275s. Used on Saturn INT-05B launch vehicle.

Status: Design concept 1960's.
Thrust: 10,105.00 kN (2,271,694 lbf).
Specific impulse: 275 s.
Burn time: 130 s.

Associated Countries

See also

Associated Launch Vehicles

Saturn INT-05A American orbital launch vehicle. UA Study, 1965: Full length 260 inch solid motor with S-IVB upper stage. More...

Associated Manufacturers and Agencies

Aerojet American manufacturer of rockets, spacecraft, and rocket engines. Aerojet, Sacramento, CA, USA. 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...

Associated Stages

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 More...