Encyclopedia Astronautica
M14


Nissan solid rocket engine. 3780.3 kN. Isp=276s. Used on M-V launch vehicle. First flight 1997.

Thrust (sl): 3,369.400 kN (757,471 lbf). Thrust (sl): 343,587 kgf. Chamber Pressure: 59.00 bar. Area Ratio: 11.

Gross mass: 83,560 kg (184,210 lb).
Unfuelled mass: 12,070 kg (26,600 lb).
Height: 13.80 m (45.20 ft).
Diameter: 2.50 m (8.20 ft).
Thrust: 3,780.30 kN (849,845 lbf).
Specific impulse: 276 s.
Specific impulse sea level: 246 s.
Burn time: 46 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-1 Solid propellant rocket stage. Loaded/empty mass 83,560/12,070 kg. Thrust 3,780.35 kN. Vacuum specific impulse 276 seconds. More...

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