Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
H-IIA
Part of H-2 Family

H-2 Cutaway view

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.

AKA: H-2A;H-IIA 2024. Status: Active. First Launch: 2014-10-07. Last Launch: 2014-10-07. Number: 1 . Payload: 11,730 kg (25,860 lb). Thrust: 4,680.00 kN (1,052,100 lbf). Gross mass: 289,000 kg (637,000 lb). Height: 49.00 m (160.00 ft). Diameter: 4.00 m (13.10 ft). Apogee: 300 km (180 mi).

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.



Family: orbital launch vehicle. Country: Japan. Spacecraft: HTV, VEP, LRE, DASH 2002, MDS, USERS, IGS, DS2000. Stages: SRB-A. Agency: Mitsubishi.

2014 October 7 - . 05:16 GMT - . Launch Site: Tanegashima. LV Family: H-2. Launch Vehicle: H-IIA.
  • Himawari-8 - . Mass: 3,500 kg (7,700 lb). Nation: Japan. Class: Earth. Type: Weather satellite. Spacecraft: DS2000. USAF Sat Cat: 40267 . COSPAR: 2014-060A. Apogee: 35,791 km (22,239 mi). Perigee: 35,782 km (22,233 mi). Inclination: 0.0200 deg. Period: 1,436.08 min. Japan Meteorological Agency weather satellite. Stationed in geosynchronous orbit at 141 deg east..


Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
© 1997-2017 Mark Wade - Contact
© / Conditions for Use