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AJ-260X
Part of AJ-260
Aerojet solid rocket engine. Study 1967. Full length version of 260 inch motor tested in 1960's. Proposed for use in various Saturn and Nova configurations. Solid propellant rocket stage. 260 inch solid booster - full length. These would have been the flight configuration motors, replacing the Saturn V first stage or being used as booster motors in various Uprated Saturn and Nova configurations. Solid propellant rocket stage. Boeing study, 1969. Solid propellant rocket stage. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb payload to LEO): Low Cost Booster, Solid Propellant.

AKA: 260 inch solid FL;MLLV-0;Saturn LCB-SR. Status: Study 1967. Thrust: 35,390.70 kN (7,956,146 lbf). Gross mass: 1,648,355 kg (3,634,000 lb). Unfuelled mass: 156,126 kg (344,198 lb). Specific impulse: 263 s. Specific impulse sea level: 238 s. Burn time: 114 s. Height: 30.48 m (99.99 ft). Diameter: 6.60 m (21.60 ft).

Thrust (sl): 32,026.700 kN (7,199,889 lbf). Thrust (sl): 3,265,865 kgf. Propellant Formulation: PBAN.

Country: USA. Launch Vehicles: Saturn INT-05A, Saturn V/4-260, Saturn LCB-SR, Saturn V-D, MLLV. Propellants: Solid. Stages: AJ-260X. Agency: Aerojet.
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