Encyclopedia Astronautica
M-13


Nissan solid rocket engine. 1262.4 kN. Isp=263s. Used on Mu-3S launch vehicle. First flight 1969.

Thrust (sl): 1,142.400 kN (256,822 lbf). Thrust (sl): 116,494 kgf.

Gross mass: 34,800 kg (76,700 lb).
Unfuelled mass: 7,640 kg (16,840 lb).
Height: 14.75 m (48.39 ft).
Diameter: 1.41 m (4.62 ft).
Thrust: 1,262.40 kN (283,799 lbf).
Specific impulse: 263 s.
Specific impulse sea level: 238 s.
Burn time: 70 s.
Number: 24 .

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Associated Countries
See also
Associated Launch Vehicles
  • Mu-3S Japanese all-solid orbital launch vehicle. Four stage vehicle consisting of 8 x SB-310 + 1 x M-13TVC + 1 x M-22TVC + 1 x M-3A More...

Associated Manufacturers and Agencies
  • Nissan Japanese manufacturer of rocket engines and rockets. Nissan, Japan. 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
  • M-13TVC Solid rocket stage. 1020.00 kN (229,305 lbf) thrust. Mass 34,200 kg (75,398 lb). More...
  • Mu-3S-1 Solid propellant rocket stage. Loaded/empty mass 34,800/7,640 kg. Thrust 1,262.42 kN. Vacuum specific impulse 263 seconds. More...

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