Solid propellant rocket stage. Loaded/empty mass 12,800/2,400 kg. Thrust 524.80 kN. Vacuum specific impulse 282 seconds. Version for J-1 F2 has 300 kg heavier empty mass.
AKA: M-23.
Status: In development.
Gross mass: 12,800 kg (28,200 lb).
Unfuelled mass: 2,400 kg (5,200 lb).
Height: 2.70 m (8.80 ft).
Diameter: 1.40 m (4.50 ft).
Span: 1.40 m (4.50 ft).
Thrust: 524.80 kN (117,980 lbf).
Specific impulse: 282 s.
Burn time: 73 s.
Number: 1 .
More... - Chronology...
Associated Countries
Associated Engines
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M-23-J Nissan solid rocket engine. 524.8 kN. In development. Isp=282s. Used on J-1 launch vehicle. First flight 1996. More...
Associated Launch Vehicles
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J-1 Japanese all-solid orbital launch vehicle. Original version. More...
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J-1 F2 Japanese all-solid orbital launch vehicle. Lower cost alternate to the original J-1 design. Uses the SRB-A of the H-2A vehicle as the first stage, the second and third stages of the J-1, with updated avionics. More...
Associated Propellants
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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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