Encyclopedia Astronautica
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.

Thrust (sl): 1,336.900 kN (300,547 lbf). Thrust (sl): 136,328 kgf. Chamber Pressure: 46.00 bar. Area Ratio: 10.

Gross mass: 70,400 kg (155,200 lb).
Unfuelled mass: 11,250 kg (24,800 lb).
Height: 23.36 m (76.64 ft).
Diameter: 1.81 m (5.93 ft).
Thrust: 1,540.00 kN (346,200 lbf).
Specific impulse: 273 s.
Specific impulse sea level: 237 s.
Burn time: 94 s.
Number: 15 .

More... - Chronology...


Associated Countries
See also
Associated Launch Vehicles
  • H-2 Heavy lift Japanese indigenous launch vehicle. The original H-2 version was cancelled due to high costs and poor reliability and replaced by the substantially redesigned H-2A. More...
  • J-1 Japanese all-solid orbital launch vehicle. Original version. 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
  • H-2-0 Solid propellant rocket stage. Loaded/empty mass 70,400/11,250 kg. Thrust 1,540.00 kN. Vacuum specific impulse 273 seconds. More...
  • 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. More...

Home - Browse - Contact
© / Conditions for Use