Encyclopedia Astronautica
AJ-260X


Aerojet solid rocket engine. 35,390.7 kN. Study 1967. Full length version of 260 inch motor tested in 1960's. Proposed for use in various Saturn and Nova configurations. Isp=263s.

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

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

More... - Chronology...


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...
  • Saturn V/4-260 American orbital launch vehicle. Boeing study, 1967-1968. Use of full length 260 inch solid rocket boosters with stretched Saturn IC stages presented problems, since the top of the motors came about half way up the liquid oxygen tank of the stage, making transmission of loads from the motors to the core vehicle complex and adding a great deal of weight to the S-IC. Boeing's solution was to retain the standard length Saturn IC, with the 260 inch motors ending half way up the S-IC/S-II interstage, but to provide additional propellant for the S-IC by putting propellant tanks above the 260 inch boosters. These would be drained first and jettisoned with the boosters. This added to the plumbing complexity but solved the loads problem. More...
  • Saturn LCB-SR American orbital launch vehicle. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, 260 inch solid motor, full length. More...
  • Saturn V-D American orbital launch vehicle. MSFC study, 1968. Rehashed the Boeing 1967 studies, covering a variety of stage stretches and 120, 156, or 260 inch solid rocket boosters, but with S-ID stage-and-a-half first stage. More...
  • MLLV American SSTO VTOVL orbital launch vehicle. Boeing study, 1969, for Saturn follow-on. Plug nozzle, single-stage-to-orbit launch vehicle could itself put 1 million pounds payload into orbit. By addition of up to 12 260 inch solid motors up to 3.5 million pounds payload into orbit with a single launch. 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 FL Solid propellant rocket stage. Loaded/empty mass 1,648,355/156,126 kg. Thrust 35,391.40 kN. Vacuum specific impulse 263 seconds. 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. More...
  • MLLV-0 Solid propellant rocket stage. Loaded/empty mass 1,920,200/192,000 kg. Thrust 44,238.70 kN. Vacuum specific impulse 263 seconds. Boeing study, 1969. More...
  • Saturn LCB-SR Solid propellant rocket stage. Loaded/empty mass 1,678,300/136,100 kg. Thrust 27,034.90 kN. Vacuum specific impulse 263 seconds. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Solid Propellant More...

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