Encyclopedia Astronautica
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.

Cost $ : 0.430 million.

AKA: M-13.
Status: Retired 1995.
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).
Span: 5.00 m (16.40 ft).
Thrust: 1,262.42 kN (283,803 lbf).
Specific impulse: 263 s.
Specific impulse sea level: 238 s.
Burn time: 70 s.
Number: 12 .

More... - Chronology...


Associated Countries
Associated Engines
  • M-13 Nissan solid rocket engine. 1262.4 kN. Isp=263s. Used on Mu-3S launch vehicle. First flight 1969. More...

Associated Launch Vehicles
  • Mu-3H Japanese all-solid orbital launch vehicle. Five stage vehicle consisting of 8 x SB-310 + 1 x M-13 + 1 x M-22TVC + 1 x M-3A + 1 x KM-H More...
  • Mu-3S-II Japanese all-solid orbital launch vehicle. Four stage vehicle consisting of 2 x SB-735 + 1 x M-13 + 1 x M-23 + 1 x M-3B 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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