Encyclopedia Astronautica
M24


Nissan solid rocket engine. 1245.3 kN. Isp=288s. Used on M-V launch vehicle. First flight 1997.

Thrust (sl): 877.700 kN (197,315 lbf). Thrust (sl): 89,506 kgf. Chamber Pressure: 59.00 bar. Area Ratio: 31.

Gross mass: 34,470 kg (75,990 lb).
Unfuelled mass: 3,410 kg (7,510 lb).
Height: 6.80 m (22.30 ft).
Diameter: 2.50 m (8.20 ft).
Thrust: 1,245.30 kN (279,955 lbf).
Specific impulse: 288 s.
Specific impulse sea level: 203 s.
Burn time: 71 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-2 Solid propellant rocket stage. Loaded/empty mass 34,470/3,410 kg. Thrust 1,245.29 kN. Vacuum specific impulse 288 seconds. More...

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