Encyclopedia Astronautica
H-2A



h2cutway.jpg
H-2 Cutaway view
Credit: NASDA
Japanese orbital launch vehicle. Low-cost version of H-2 developed for the commercial market. The two SRB-A solid rocket boosters can be supplemented by 4 smaller SSB solid boosters. 0 or 2 SSB's can be fitted for reduced 9,940 kg or 10,740 kg LEO payloads.

LEO Payload: 11,730 kg (25,860 lb) to a 300 km orbit at 30.40 degrees. Payload: 5,000 kg (11,000 lb) to a GTO. Development Cost $: 800.000 million. Launch Price $: 90.000 million in 1999 dollars in 1999 dollars.

Stage Data - H-2A

  • Stage 0. 2 x H-2A SRB-A. Gross Mass: 76,400 kg (168,400 lb). Empty Mass: 10,400 kg (22,900 lb). Thrust (vac): 2,250.000 kN (505,820 lbf). Isp: 280 sec. Burn time: 101 sec. Isp(sl): 230 sec. Diameter: 2.50 m (8.20 ft). Span: 2.50 m (8.20 ft). Length: 15.20 m (49.80 ft). Propellants: Solid. No Engines: 1. Engine: SRB-A. Status: In production. Comments: 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.
  • Stage 1. 2 x H-2A SSB. Gross Mass: 15,200 kg (33,500 lb). Empty Mass: 2,100 kg (4,600 lb). Thrust (vac): 626.600 kN (140,865 lbf). Isp: 283 sec. Burn time: 60 sec. Diameter: 1.00 m (3.20 ft). Span: 1.00 m (3.20 ft). Length: 14.90 m (48.80 ft). Propellants: Solid. No Engines: 1. Engine: Castor 4AXL. Status: In production. Comments: Provides supplemental thrust for H-2 or H-2A.
  • Stage 2. 2 x H-2A SSB. Gross Mass: 15,200 kg (33,500 lb). Empty Mass: 2,100 kg (4,600 lb). Thrust (vac): 626.600 kN (140,865 lbf). Isp: 283 sec. Burn time: 60 sec. Diameter: 1.00 m (3.20 ft). Span: 1.00 m (3.20 ft). Length: 14.90 m (48.80 ft). Propellants: Solid. No Engines: 1. Engine: Castor 4AXL. Status: In production. Comments: Provides supplemental thrust for H-2 or H-2A.
  • Stage 3. 1 x H-2A-1. Gross Mass: 113,600 kg (250,400 lb). Empty Mass: 13,600 kg (29,900 lb). Thrust (vac): 1,098.000 kN (246,840 lbf). Isp: 440 sec. Burn time: 390 sec. Isp(sl): 338 sec. Diameter: 4.00 m (13.10 ft). Span: 4.00 m (13.10 ft). Length: 37.20 m (122.00 ft). Propellants: Lox/LH2. No Engines: 1. Engine: LE-7A. Status: In production. Comments: Can be throttled to 72% thrust.
  • Stage 4. 1 x H-2A-2. Gross Mass: 19,600 kg (43,200 lb). Empty Mass: 3,000 kg (6,600 lb). Thrust (vac): 137.000 kN (30,798 lbf). Isp: 447 sec. Burn time: 534 sec. Diameter: 4.00 m (13.10 ft). Span: 4.00 m (13.10 ft). Length: 9.20 m (30.10 ft). Propellants: Lox/LH2. No Engines: 1. Engine: LE-5B. Status: In production. Comments: Lower cost version of H-2 second stage.

AKA: H-IIA 2024.
Status: In production.
Gross mass: 289,000 kg (637,000 lb).
Payload: 11,730 kg (25,860 lb).
Height: 49.00 m (160.00 ft).
Diameter: 4.00 m (13.10 ft).
Thrust: 4,680.00 kN (1,052,100 lbf).
Apogee: 300 km (180 mi).

More... - Chronology...


Associated Countries
Associated Spacecraft
  • HTV Japanese unmanned spacecraft designed for launch by the H-IIB launch vehicle for International Space Station resupply. The HTV carried International Standard Payload Racks, and was docked using the ISS robot arm after rendezvous with the station. First launched 2009.09.10. More...
  • VEP Japanese technology satellite. 2 launches, 1994.02.03 (VEP) and 2001.08.29 (VEP-2). Monitored H-2 launch vehicle performance. National name MYOJO. More...
  • LRE Japanese earth geodetic satellite. One launch, 2001.08.29. The 87 kg Laser Ranging Experiment was a passive mirror ball of diameter 51 cm and carried 24 glass sheets and 126 prisms on its surface. More...
  • MDS Japanese technology satellite. One launch, 2002.02.04. MDS (Mission Demonstration Satellite) was a technology demonstrator to flight-qualify commercial subsystems. More...
  • DASH 2002 Japanese re-entry vehicle technology satellite. One launch, 2002.02.04, DASH. DASH (Demonstrator of Atmospheric Reentry System and Hypervelocity) was a small secondary payload built by ISAS, the scientific space agency which was to merge with NASDA. More...
  • USERS Japanese materials science satellite. One launch, 2002.09.10. USERS (Unmanned Space Experiment Recovery System) was a Japanese microgravity experimental satellite. More...
  • IGS Japanese military surveillance satellite. Operational, first launched 2003.03.28. Japan's first military reconnaissance satellites, launched in optical and radar versions. More...

Associated Engines
  • SRB-A Nissan solid rocket engine. 2250 kN. In production. Monolithic motor, shorter than that for H-2, using Thiokol filament wound composite structure. Isp=280s. 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...

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