Encyclopedia Astronautica
M34


Nissan solid rocket engine. 294.2 kN. Isp=301s. Used on M-V launch vehicle. First flight 1997.

Chamber Pressure: 59.00 bar. Area Ratio: 96.

Gross mass: 11,000 kg (24,000 lb).
Unfuelled mass: 1,000 kg (2,200 lb).
Height: 3.60 m (11.80 ft).
Diameter: 2.20 m (7.20 ft).
Thrust: 294.20 kN (66,139 lbf).
Specific impulse: 301 s.
Burn time: 102 s.
Number: 7 .

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Associated Countries
See also
Associated Launch Vehicles
  • M-V All-solid Japanese satellite launch vehicle. 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-V-3 Solid propellant rocket stage. Loaded/empty mass 11,000/1,000 kg. Thrust 294.00 kN. Vacuum specific impulse 301 seconds. More...

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