Encyclopedia Astronautica
H-2A 212


Japanese orbital launch vehicle. This version uses two core stages side-by-side in an asymmetric configuration, supplemented by two SRB-A solid rocket boosters.

LEO Payload: 17,280 kg (38,090 lb) to a 300 km orbit at 30.40 degrees. Payload: 7,500 kg (16,500 lb) to a GTO.

AKA: H-IIA 212.
Status: In production.
Gross mass: 406,000 kg (895,000 lb).
Payload: 17,280 kg (38,090 lb).
Height: 52.50 m (172.20 ft).
Diameter: 4.00 m (13.10 ft).
Thrust: 6,400.00 kN (1,438,700 lbf).
Apogee: 300 km (180 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • LE-5B Mitsubishi lox/lh2 rocket engine. 137 kN. In production. Isp=447s. Improved model of the LE-5A for second stage of the H-II rocket; used hydrogen for the cooling of the thrust chamber, then as the gas to drive the turbine. First flight 2001. More...
  • LE-7A Mitsubishi lox/lh2 rocket engine. 1098 kN. In production. Isp=438s. Improved model of the original LE-7 for the first stage of the H-II rocket with a two stage combustion cycle system. First flight 2001. More...

See also
  • 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.

    3 stage vehicle consisted of 2 x H-II SRB + 1 x H-II stage 1 + 1 x H-II stage 2 More...


Associated Manufacturers and Agencies
  • Mitsubishi Japanese manufacturer of rockets, spacecraft, and rocket engines. Mitsubishi Electric Corp, Japan. More...

Associated Stages
  • H-2A-1 Lox/LH2 propellant rocket stage. Loaded/empty mass 113,600/13,600 kg. Thrust 1,098.00 kN. Vacuum specific impulse 440 seconds. Lower cost version of H-2 first stage. Can be throttled to 72% thrust. More...
  • H-2A LRB Lox/LH2 propellant rocket stage. Loaded/empty mass 117,000/17,800 kg. Thrust 2,196.00 kN. Vacuum specific impulse 440 seconds. Two-engine version of H-2A-1 used as strap-on booster. More...
  • H-2A SRB-A Solid propellant rocket stage. Loaded/empty mass 76,400/10,400 kg. Thrust 2,250.00 kN. Vacuum specific impulse 280 seconds. More...
  • LE-5B Lox/LH2 propellant rocket stage. Loaded/empty mass 19,600/3,000 kg. Thrust 137.00 kN. Vacuum specific impulse 447 seconds. Lower cost version of H-2 second stage. More...

Home - Browse - Contact
© / Conditions for Use