Encyclopedia Astronautica
M-23-Mu


Nissan solid rocket engine. 524 kN. Isp=285s. Used on Mu-3S launch vehicle. First flight 1969.

Thrust (sl): 404.500 kN (90,935 lbf). Thrust (sl): 41,247 kgf.

Gross mass: 13,100 kg (28,800 lb).
Unfuelled mass: 2,800 kg (6,100 lb).
Height: 6.19 m (20.30 ft).
Diameter: 1.41 m (4.62 ft).
Thrust: 524.00 kN (117,799 lbf).
Specific impulse: 285 s.
Specific impulse sea level: 220 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
  • Mu-3S-2 Solid propellant rocket stage. Loaded/empty mass 13,100/2,800 kg. Thrust 524.00 kN. Vacuum specific impulse 285 seconds. More...

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