Encyclopedia Astronautica
M-3B-Mu


Nissan solid rocket engine. 132.1 kN. Isp=294s. Used on Mu-3S launch vehicle. First flight 1969.

Chamber Pressure: 42.00 bar. Area Ratio: 52.

Gross mass: 3,590 kg (7,910 lb).
Unfuelled mass: 490 kg (1,080 lb).
Height: 2.68 m (8.79 ft).
Diameter: 1.50 m (4.90 ft).
Thrust: 132.10 kN (29,697 lbf).
Specific impulse: 294 s.
Burn time: 85 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-3B Solid propellant rocket stage. Loaded/empty mass 3,590/310 kg. Thrust 132.12 kN. Vacuum specific impulse 294 seconds. More...

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