Encyclopedia Astronautica
M-V-4


Nissan solid rocket engine. 52 kN. Isp=298s. Used on M-V launch vehicle. First flight 1997.

Chamber Pressure: 49.00 bar. Area Ratio: 89.

Gross mass: 1,430 kg (3,150 lb).
Unfuelled mass: 118 kg (260 lb).
Height: 1.50 m (4.90 ft).
Diameter: 1.20 m (3.90 ft).
Thrust: 52.00 kN (11,690 lbf).
Specific impulse: 298 s.
Burn time: 73 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-4 Solid propellant rocket stage. Loaded/empty mass 1,430/118 kg. Thrust 51.90 kN. Vacuum specific impulse 298 seconds. More...

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