Encyclopedia Astronautica
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.

Cost $ : 20.000 million.

Status: Retired 1999.
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).
Span: 1.81 m (5.93 ft).
Thrust: 1,540.00 kN (346,205 lbf).
Specific impulse: 273 s.
Specific impulse sea level: 237 s.
Burn time: 94 s.
Number: 24 .

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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
  • H-II Japanese orbital launch vehicle. 3 stage vehicle consisted of 2 x H-II SRB boosters + core vehicle. More...
  • H-II (2S) Japanese orbital launch vehicle. Three stage version consisting of 2 x H-II SSB boosters + 2 x H-II SRB boosters + core vehicle. 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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