Encyclopedia Astronautica
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.

Status: Development 1968.
Gross mass: 1,920,200 kg (4,233,300 lb).
Unfuelled mass: 192,000 kg (423,000 lb).
Height: 54.75 m (179.62 ft).
Diameter: 6.61 m (21.68 ft).
Span: 6.61 m (21.68 ft).
Thrust: 44,238.70 kN (9,945,255 lbf).
Specific impulse: 263 s.
Specific impulse sea level: 238 s.
Burn time: 99 s.

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Associated Countries
Associated Engines
  • 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. 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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