Encyclopedia Astronautica
J-1-1


Solid propellant rocket stage. Loaded/empty mass 71,100/11,900 kg. Thrust 1,556.60 kN. Vacuum specific impulse 273 seconds. Shorter monolithic motor using filament-wound case technology from Thiokol. Version for J-1 has 1,000 kg less propellant and 1,200 kg less empty mass than later H-2 SRB.

Status: In production.
Gross mass: 71,100 kg (156,700 lb).
Unfuelled mass: 11,900 kg (26,200 lb).
Height: 18.00 m (59.00 ft).
Diameter: 1.80 m (5.90 ft).
Span: 1.80 m (5.90 ft).
Thrust: 1,556.60 kN (349,938 lbf).
Specific impulse: 273 s.
Specific impulse sea level: 248 s.
Burn time: 94 s.
Number: 1 .

More... - Chronology...


Associated Countries
Associated Engines
  • H-2-0 Nissan solid rocket engine. 1540 kN. Isp=273s. Used as strap-on booster on H-2, first stage on J-1. First flight 1994. More...

Associated Launch Vehicles
  • J-1 Japanese all-solid orbital launch vehicle. Original version. 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...

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