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H-2
Orbital launch vehicle. Country: Japan. Status: Active. Other Designations: H-II.

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

Manufacturer: Mitsubishi. Launches: 20. Failures: 3. Success Rate: 85.00%. First Launch Date: 1994-02-03. Last Launch Date: 2007-09-14. Launch data is: continuing. LEO Payload: 10,060 kg (22,170 lb). to: 200 km Orbit. at: 30.40 degrees. Payload: 3,930 kg (8,660 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: ADEOS, ETS, ETS-7, ETS-7 Target, FS-1300, Fuji, GMS, Kakehashi, OREX, SFU, TRMM, VEP. Liftoff Thrust: 3,970.000 kN (892,490 lbf). Total Mass: 260,000 kg (570,000 lb). Core Diameter: 4.00 m (13.10 ft). Total Length: 49.00 m (160.00 ft). Development Cost $: 2,300.000 million. in: 1998 average dollars. Launch Price $: 190.000 million. in: 1994 price dollars. Cost comments: Development cost includes $ 800 million spent on LE-7 engine development. Version:

H-II.
H-2 Liftoff
Credit - NASDA
Status: Retired 1999.

3 stage vehicle consisted of 2 x H-II SRB boosters + core vehicle.

Launches: 7. Failures: 2. First Launch Date: 1994-02-03. Last Launch Date: 1999-11-15. LEO Payload: 10,060 kg (22,170 lb). to: 200 km Orbit. at: 30.40 degrees. Payload: 3,930 kg (8,660 lb). to a: Geosynchronous transfer trajectory. Liftoff Thrust: 3,970.000 kN (892,490 lbf). Total Mass: 260,000 kg (570,000 lb). Core Diameter: 4.00 m (13.10 ft). Total Length: 49.00 m (160.00 ft).

  • Stage0: 2 x H-2-0. Gross Mass: 70,400 kg (155,200 lb). Empty Mass: 11,250 kg (24,800 lb). Motor: 1 x H-2-0. Thrust (vac): 1,539.997 kN (346,205 lbf). Isp: 273 sec. Burn time: 94 sec. Length: 23.36 m (76.64 ft). Diameter: 1.81 m (5.93 ft). Propellants: Solid.
  • Stage1: 1 x H-2-1. Gross Mass: 98,100 kg (216,200 lb). Empty Mass: 11,900 kg (26,200 lb). Motor: 1 x LE-7. Thrust (vac): 1,077.996 kN (242,343 lbf). Isp: 446 sec. Burn time: 346 sec. Length: 28.00 m (91.00 ft). Diameter: 4.00 m (13.10 ft). Propellants: Lox/LH2.
  • Stage2: 1 x LE-5EC. Gross Mass: 16,700 kg (36,800 lb). Empty Mass: 2,700 kg (5,900 lb). Motor: 1 x LE-5A. Thrust (vac): 121.500 kN (27,314 lbf). Isp: 452 sec. Burn time: 600 sec. Length: 10.60 m (34.70 ft). Diameter: 4.00 m (13.10 ft). Propellants: Lox/LH2.
Version:

H-II (2S).

Three stage version consisting of 2 x H-II SSB boosters + 2 x H-II SRB boosters + core vehicle.

Payload: 3,930 kg (8,660 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 40,000 km (24,000 mi). Liftoff Thrust: 4,600.000 kN (1,034,100 lbf). Total Mass: 281,000 kg (619,000 lb). Core Diameter: 4.00 m (13.10 ft). Total Length: 49.00 m (160.00 ft).

  • Stage-1: 2 x H-2A SSB. Gross Mass: 15,200 kg (33,500 lb). Empty Mass: 2,100 kg (4,600 lb). Motor: 1 x Castor 4AXL. Thrust (vac): 626.600 kN (140,865 lbf). Isp: 283 sec. Burn time: 60 sec. Length: 14.90 m (48.80 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.
  • Stage0: 2 x H-2-0. Gross Mass: 70,400 kg (155,200 lb). Empty Mass: 11,250 kg (24,800 lb). Motor: 1 x H-2-0. Thrust (vac): 1,539.997 kN (346,205 lbf). Isp: 273 sec. Burn time: 94 sec. Length: 23.36 m (76.64 ft). Diameter: 1.81 m (5.93 ft). Propellants: Solid.
  • Stage1: 1 x H-2-1. Gross Mass: 98,100 kg (216,200 lb). Empty Mass: 11,900 kg (26,200 lb). Motor: 1 x LE-7. Thrust (vac): 1,077.996 kN (242,343 lbf). Isp: 446 sec. Burn time: 346 sec. Length: 28.00 m (91.00 ft). Diameter: 4.00 m (13.10 ft). Propellants: Lox/LH2.
  • Stage2: 1 x LE-5EC. Gross Mass: 16,700 kg (36,800 lb). Empty Mass: 2,700 kg (5,900 lb). Motor: 1 x LE-5A. Thrust (vac): 121.500 kN (27,314 lbf). Isp: 452 sec. Burn time: 600 sec. Length: 10.60 m (34.70 ft). Diameter: 4.00 m (13.10 ft). Propellants: Lox/LH2.
Version:

H-2 HIMES. Status: Design 1999.

Concept of H-2 augmented with Liquid-Air Cycle Engine boosters and advanced HIMES upper stage.

Liftoff Thrust: 2,167.440 kN (487,260 lbf). Total Mass: 183,700 kg (404,900 lb). Core Diameter: 4.00 m (13.10 ft). Total Length: 50.00 m (164.00 ft). Flyaway Unit Cost $: 170.000 million. in: 1985 unit dollars.

  • Stage0: 9 x LACE. Gross Mass: 8,000 kg (17,600 lb). Empty Mass: 2,000 kg (4,400 lb). Motor: 1 x LACE/LE-5. Thrust (vac): 147.000 kN (33,046 lbf). Isp: 1,200 sec. Burn time: 470 sec. Length: 8.00 m (26.20 ft). Diameter: 2.40 m (7.80 ft). Propellants: Liquid Air/LH2.
  • Stage1: 1 x H-2-1. Gross Mass: 98,100 kg (216,200 lb). Empty Mass: 11,900 kg (26,200 lb). Motor: 1 x LE-7. Thrust (vac): 1,077.996 kN (242,343 lbf). Isp: 446 sec. Burn time: 346 sec. Length: 28.00 m (91.00 ft). Diameter: 4.00 m (13.10 ft). Propellants: Lox/LH2.
  • Stage2: 1 x HIMES. Gross Mass: 13,600 kg (29,900 lb). Empty Mass: 3,100 kg (6,800 lb). Motor: 2 x HIMES. Thrust (vac): 274.000 kN (61,597 lbf). Isp: 452 sec. Burn time: 167 sec. Length: 13.60 m (44.60 ft). Diameter: 2.40 m (7.80 ft). Propellants: Lox/LH2.
Version:

H-2A.
H-2 Cutaway view
Credit - NASDA
Status: In production. Other Designations: H-IIA 2024.

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: 300 km Orbit. at: 30.40 degrees. Payload: 5,000 kg (11,000 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: DASH 2002, IGS, LRE, MDS, USERS, VEP. Other Associated Spacecraft: NASDA H-2 Transfer Vehicle. Liftoff Thrust: 4,680.000 kN (1,052,100 lbf). Total Mass: 289,000 kg (637,000 lb). Core Diameter: 4.00 m (13.10 ft). Total Length: 49.00 m (160.00 ft). Development Cost $: 800.000 million. in: 1999 average dollars. Launch Price $: 90.000 million. in: 1999 price dollars. Cost comments: The H-2A 202 (no SSB's) is priced at $ 75 million, and the H-2A 2022 (2 SSB's) at $ 80 million. Version:

H-IIA 202. Status: Active.

Three stage version of H-IIA consisting of 2 x H-II SRB-A + two-stage core vehicle.

Launches: 3. First Launch Date: 2001-08-29. Last Launch Date: 2006-09-11. LEO Payload: 10,000 kg (22,000 lb). Payload: 4,100 kg (9,000 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 40,000 km (24,000 mi). Liftoff Thrust: 5,600.000 kN (1,258,900 lbf). Total Mass: 285,000 kg (628,000 lb). Core Diameter: 4.00 m (13.10 ft). Total Length: 53.00 m (173.00 ft).

  • Stage0: 2 x H-2A SRB-A. Gross Mass: 76,400 kg (168,400 lb). Empty Mass: 10,400 kg (22,900 lb). Motor: 1 x SRB-A. Thrust (vac): 2,250.000 kN (505,820 lbf). Isp: 280 sec. Burn time: 101 sec. Length: 15.20 m (49.80 ft). Diameter: 2.50 m (8.20 ft). Propellants: Solid.
  • Stage1: 1 x H-2A-1. Gross Mass: 113,600 kg (250,400 lb). Empty Mass: 13,600 kg (29,900 lb). Motor: 1 x LE-7A. Thrust (vac): 1,098.000 kN (246,840 lbf). Isp: 440 sec. Burn time: 390 sec. Length: 37.20 m (122.00 ft). Diameter: 4.00 m (13.10 ft). Propellants: Lox/LH2.
  • Stage2: 1 x LE-5B. Gross Mass: 19,600 kg (43,200 lb). Empty Mass: 3,000 kg (6,600 lb). Motor: 1 x LE-5B. Thrust (vac): 137.000 kN (30,798 lbf). Isp: 447 sec. Burn time: 534 sec. Length: 9.20 m (30.10 ft). Diameter: 4.00 m (13.10 ft). Propellants: Lox/LH2.
Version:

H-IIA 2022. Status: Active.

Launches: 3. First Launch Date: 2005-02-26. Last Launch Date: 2007-09-14. LEO Payload: 5,000 kg (11,000 lb). Total Mass: 348,000 kg (767,000 lb). Core Diameter: 4.00 m (13.10 ft). Total Length: 57.00 m (187.00 ft).

  • Stage-1: 2 x Castor 4XL. Gross Mass: 15,400 kg (33,900 lb). Empty Mass: 2,500 kg (5,500 lb). Motor: 1 x Castor 4AXL. Thrust (vac): 745.000 kN (167,482 lbf). Isp: 283 sec. Burn time: 60 sec. Length: 14.90 m (48.80 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.
  • Stage0: 2 x H-2A SRB-A. Gross Mass: 76,400 kg (168,400 lb). Empty Mass: 10,400 kg (22,900 lb). Motor: 1 x SRB-A. Thrust (vac): 2,250.000 kN (505,820 lbf). Isp: 280 sec. Burn time: 101 sec. Length: 15.20 m (49.80 ft). Diameter: 2.50 m (8.20 ft). Propellants: Solid.
  • Stage1: 1 x H-2A-1. Gross Mass: 113,600 kg (250,400 lb). Empty Mass: 13,600 kg (29,900 lb). Motor: 1 x LE-7A. Thrust (vac): 1,098.000 kN (246,840 lbf). Isp: 440 sec. Burn time: 390 sec. Length: 37.20 m (122.00 ft). Diameter: 4.00 m (13.10 ft). Propellants: Lox/LH2.
  • Stage2: 1 x LE-5B. Gross Mass: 19,600 kg (43,200 lb). Empty Mass: 3,000 kg (6,600 lb). Motor: 1 x LE-5B. Thrust (vac): 137.000 kN (30,798 lbf). Isp: 447 sec. Burn time: 534 sec. Length: 9.20 m (30.10 ft). Diameter: 4.00 m (13.10 ft). Propellants: Lox/LH2.
Version:

H-IIA 2024. Status: Active. Other Designations: H-IIA 2024.

Three stage vehicle consisting of 4 x Castor 4XL + 2 x H-II SRB-A boosters + two-stage core vehicle.

Launches: 6. Failures: 1. First Launch Date: 2002-02-04. Last Launch Date: 2007-02-24. LEO Payload: 11,730 kg (25,860 lb). to: 300 km Orbit. at: 30.40 degrees. Payload: 5,000 kg (11,000 lb). to a: Geosynchronous transfer trajectory. Liftoff Thrust: 4,680.000 kN (1,052,100 lbf). Total Mass: 289,000 kg (637,000 lb). Core Diameter: 4.00 m (13.10 ft). Total Length: 49.00 m (160.00 ft). Development Cost $: 800.000 million. in: 1999 average dollars. Launch Price $: 90.000 million. in: 1999 price dollars. Cost comments: The H-2A 202 (no SSB's) is priced at $ 75 million, and the H-2A 2022 (2 SSB's) at $ 80 million.

  • Stage-1: 4 x Castor 4XL. Gross Mass: 15,400 kg (33,900 lb). Empty Mass: 2,500 kg (5,500 lb). Motor: 1 x Castor 4AXL. Thrust (vac): 745.000 kN (167,482 lbf). Isp: 283 sec. Burn time: 60 sec. Length: 14.90 m (48.80 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.
  • Stage0: 2 x H-2A SRB-A. Gross Mass: 76,400 kg (168,400 lb). Empty Mass: 10,400 kg (22,900 lb). Motor: 1 x SRB-A. Thrust (vac): 2,250.000 kN (505,820 lbf). Isp: 280 sec. Burn time: 101 sec. Length: 15.20 m (49.80 ft). Diameter: 2.50 m (8.20 ft). Propellants: Solid.
  • Stage1: 1 x H-2A-1. Gross Mass: 113,600 kg (250,400 lb). Empty Mass: 13,600 kg (29,900 lb). Motor: 1 x LE-7A. Thrust (vac): 1,098.000 kN (246,840 lbf). Isp: 440 sec. Burn time: 390 sec. Length: 37.20 m (122.00 ft). Diameter: 4.00 m (13.10 ft). Propellants: Lox/LH2.
  • Stage2: 1 x LE-5B. Gross Mass: 19,600 kg (43,200 lb). Empty Mass: 3,000 kg (6,600 lb). Motor: 1 x LE-5B. Thrust (vac): 137.000 kN (30,798 lbf). Isp: 447 sec. Burn time: 534 sec. Length: 9.20 m (30.10 ft). Diameter: 4.00 m (13.10 ft). Propellants: Lox/LH2.
Version:

H-IIA 204. Status: Active.

Launches: 1. First Launch Date: 2006-12-16. Last Launch Date: 2006-12-16.

  • Stage0: 2 x H-2A SRB-A. Gross Mass: 76,400 kg (168,400 lb). Empty Mass: 10,400 kg (22,900 lb). Motor: 1 x SRB-A. Thrust (vac): 2,250.000 kN (505,820 lbf). Isp: 280 sec. Burn time: 101 sec. Length: 15.20 m (49.80 ft). Diameter: 2.50 m (8.20 ft). Propellants: Solid.
  • Stage1: 2 x H-2A SSB. Gross Mass: 15,200 kg (33,500 lb). Empty Mass: 2,100 kg (4,600 lb). Motor: 1 x Castor 4AXL. Thrust (vac): 626.600 kN (140,865 lbf). Isp: 283 sec. Burn time: 60 sec. Length: 14.90 m (48.80 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.
  • Stage2: 2 x H-2A SSB. Gross Mass: 15,200 kg (33,500 lb). Empty Mass: 2,100 kg (4,600 lb). Motor: 1 x Castor 4AXL. Thrust (vac): 626.600 kN (140,865 lbf). Isp: 283 sec. Burn time: 60 sec. Length: 14.90 m (48.80 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.
  • Stage3: 1 x H-2A-1. Gross Mass: 113,600 kg (250,400 lb). Empty Mass: 13,600 kg (29,900 lb). Motor: 1 x LE-7A. Thrust (vac): 1,098.000 kN (246,840 lbf). Isp: 440 sec. Burn time: 390 sec. Length: 37.20 m (122.00 ft). Diameter: 4.00 m (13.10 ft). Propellants: Lox/LH2.
  • Stage4: 1 x LE-5B. Gross Mass: 19,600 kg (43,200 lb). Empty Mass: 3,000 kg (6,600 lb). Motor: 1 x LE-5B. Thrust (vac): 137.000 kN (30,798 lbf). Isp: 447 sec. Burn time: 534 sec. Length: 9.20 m (30.10 ft). Diameter: 4.00 m (13.10 ft). Propellants: Lox/LH2.
Version:

H-2A 212. Status: In production. Other Designations: H-IIA 212.

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: 300 km Orbit. at: 30.40 degrees. Payload: 7,500 kg (16,500 lb). to a: Geosynchronous transfer trajectory. Liftoff Thrust: 6,400.000 kN (1,438,700 lbf). Total Mass: 406,000 kg (895,000 lb). Core Diameter: 4.00 m (13.10 ft). Total Length: 52.50 m (172.20 ft).

  • Stage0: 2 x H-2A SRB-A. Gross Mass: 76,400 kg (168,400 lb). Empty Mass: 10,400 kg (22,900 lb). Motor: 1 x SRB-A. Thrust (vac): 2,250.000 kN (505,820 lbf). Isp: 280 sec. Burn time: 101 sec. Length: 15.20 m (49.80 ft). Diameter: 2.50 m (8.20 ft). Propellants: Solid.
  • Stage1: 1 x H-2A LRB. Gross Mass: 117,000 kg (257,000 lb). Empty Mass: 17,800 kg (39,200 lb). Motor: 2 x LE-7A. Thrust (vac): 2,196.000 kN (493,680 lbf). Isp: 440 sec. Burn time: 193 sec. Length: 36.70 m (120.40 ft). Diameter: 4.00 m (13.10 ft). Propellants: Lox/LH2.
  • Stage2: 1 x H-2A-1. Gross Mass: 113,600 kg (250,400 lb). Empty Mass: 13,600 kg (29,900 lb). Motor: 1 x LE-7A. Thrust (vac): 1,098.000 kN (246,840 lbf). Isp: 440 sec. Burn time: 390 sec. Length: 37.20 m (122.00 ft). Diameter: 4.00 m (13.10 ft). Propellants: Lox/LH2.
  • Stage3: 1 x LE-5B. Gross Mass: 19,600 kg (43,200 lb). Empty Mass: 3,000 kg (6,600 lb). Motor: 1 x LE-5B. Thrust (vac): 137.000 kN (30,798 lbf). Isp: 447 sec. Burn time: 534 sec. Length: 9.20 m (30.10 ft). Diameter: 4.00 m (13.10 ft). Propellants: Lox/LH2.
H-2 Chronology

1994 February 3 - 22:20 GMT - Tanegashima Y. H-II H-II-1F OREX Mass: 865 kg (1,906 lb). Spacecraft: OREX. Agency: NASDA/NA. Perigee: 450 km (270 mi). Apogee: 451 km (280 mi). Inclination: 30.50 deg. Period: 93.50 min. Orbital Reentry Experiment. Orbital Re-entry Experiment Vehicle (OREX) Ryusei. Acquisition of data related to atmospheric reentry. Launch vehicle H-II rocket test flight H-II 1F. Launching organization NASDA. Launch time 2220:00 UT.

1994 August 28 - 07:50 GMT - Tanegashima Y. H-II H-II-2F FAILURE: LAPS apogee kick motor failed to ignite. Partial Failure. Kiku 6 Mass: 3,800 kg (8,300 lb). Spacecraft: ETS. Agency: NASDA. Perigee: 8,565 km (5,322 mi). Apogee: 38,677 km (24,032 mi). Inclination: 13.23 deg. Period: 861.84 min. Failed to reach geostationary orbit; Engineering Test Satellite; partial mission success. Also tested ion engines for NSSK.

1995 March 18 - 08:01 GMT - Tanegashima Y. H-II H-II-3F SFU Mass: 4,000 kg (8,800 lb). Spacecraft: SFU. Agency: NASDA. Perigee: 471 km (292 mi). Apogee: 483 km (300 mi). Inclination: 28.50 deg. Period: 94.10 min. Space Flyer Unit; carried materials, astronomy, biological experiments; retrieved by STS-72 1/20/96.

1996 August 17 - 01:53 GMT - Tanegashima Y. H-II H-II-4F ADEOS Spacecraft: ADEOS. Agency: NASDA. Perigee: 799 km (496 mi). Apogee: 800 km (490 mi). Inclination: 98.60 deg. Period: 100.90 min.

1997 November 27 - 21:27 GMT - Tanegashima Y. H-II H-II-6F TRMM Spacecraft: TRMM. Agency: NASA GSF. Perigee: 395 km (245 mi). Apogee: 403 km (250 mi). Inclination: 35.00 deg. Period: 92.50 min. TRMM was an international mission dedicated to measuring tropical and subtropical rainfall. The spacecraft and four instruments were provided by the USA, while Japan provided one instrument and launch services.

1998 February 21 - 07:55 GMT - Tanegashima Y. H-II H-II-5F Kakehashi Spacecraft: Kakehashi. Agency: NASDA. Perigee: 1,033 km (641 mi). Apogee: 17,727 km (11,015 mi). Inclination: 30.10 deg. Period: 328.10 min. Kakehashi, meaning 'Bridge', was called Communuications and Broadcasting Experimental Test Satellite (COMETS) before launch. It contained Ka-band communications and inter-satellite data relay payloads. Premature shutdown 44 seconds into the H-II second stage second burn put the satellite into a much lower than planned orbit. The on-board Unified Propulsion System was used to raise it to a more useful orbit.

1999 November 15 - 07:29 GMT - Tanegashima Y. H-II H-II-8F FAILURE: Failure during first stage burn. MTSAT Spacecraft: FS-1300. Agency: National Space Development Agency, Japan. Multi-functional Transportation Satellite intended to provide communications and air traffic control for the Japanese transportation ministry and a meteorological data for the Japanese Meteorological Agency. The spacecraft had a mass of 1223 kg dry and was a follow-on to the GMS (Himawari) weather satellite series.

2001 August 29 - 07:00 GMT - Tanegashima Y. H-IIA 202 H-IIA-1F LRE Mass: 3,500 kg (7,700 lb). Spacecraft: LRE. Agency: NASDA (Japan). Perigee: 271 km (168 mi). Apogee: 36,214 km (22,502 mi). Inclination: 28.00 deg. Launch postponed from february, July 22 and August 25. First launch of the H-2A launch vehicle. A failure after all of the problems with the earlier H-2 version would probably have resulted in cancellation of the program. The Laser Ranging Experiment satellite carried 126 laser retro reflectors and separated from the second stage at 0739 GMT into its operational 'Molniya' type orbit. The eventual goal of H-2A was to launch geosynchronous spacecraft at costs comparable to those of other countries. The LRE remained in a simulated geosynchronous transfer orbit; laser reflections from it would be used to precisely ascertain the orbital injection accuracy of the H-2A.

2002 February 4 - 02:45 GMT - Tanegashima Y. H-IIA 2024 H-IIA-2F MDS-1 Mass: 304 kg (670 lb). Spacecraft: MDS. Agency: NASDA (Japan). Perigee: 373 km (231 mi). Apogee: 35,753 km (22,215 mi). Inclination: 28.30 deg. Period: 633.80 min. Technology qualification flight - maiden flight of H-2A booster. Launch delayed from January 31 and February 3. The second stage began its first burn at 0251 UTC and at 0257 UTC entered a 500 km circular parking orbit. After a 12 minute coast the second burn put stage 2 in geostationary transfer orbit. At 0315 UTC the small DASH vehicle was meant to separate from the upper adapter, but this apparently did not occur. At 0325 UTC VEP-3/upper adapter/DASH combination separated from the second stage, followed by two semi-cylindrical side panels, revealing the previously enclosed MDS-1 technology satellite which was ejected at 0331 UTC. At 0425 UTC the second stage was scheduled to make a third burn to test engine restart, completing the H-2A-2F mission.

2002 September 10 - 08:20 GMT - Tanegashima Y. H-IIA 2024 H-IIA-3F USERS Mass: 1,726 kg (3,805 lb). Spacecraft: USERS. Agency: NASDA (Japan). Perigee: 497 km (308 mi). Apogee: 508 km (315 mi). Inclination: 30.40 deg. Period: 94.70 min. Launch delayed from August 2002. First operational flight of H-2A booster. USERS (Unmanned Space Experiment Recovery System) was a Japanese microgravity experimental satellite. After 8.5 months in orbit, a reentry vehicle was to be returned to earth with the materials manufacturered in space.

2002 December 14 - 23:04 GMT - Tanegashima Y. H-IIA 202 H-IIA-4F Adeos 2 Mass: 3,730 kg (8,220 lb). Spacecraft: Adeos. Agency: NASDA (Japan). Perigee: 804 km (499 mi). Apogee: 806 km (500 mi). Inclination: 98.70 deg. Period: 101.00 min. Environment Monitoring, Aeronomy.

2003 March 28 - 01:27 GMT - Tanegashima Y. H-IIA 2024 H-IIA-5F IGS-1a Mass: 850 kg (1,870 lb). Spacecraft: IGS. Perigee: 483 km (300 mi). Apogee: 495 km (307 mi). Inclination: 97.30 deg. Period: 94.20 min. Optical reconnaisance satellite. First Japanese military space mission. Dual payload. Delayed from February 2003. The Tanegashima facility was under strict security, guarded by 400 police officers wearing bullet-proof vests. Waters near the pad were patrolled by the coast guard.

2003 November 29 - 04:33 GMT - Tanegashima Y. H-IIA 2024 H-IIA-6F FAILURE: Destroyed by range safety after solid booster nozzle burn-through resulted in motor not separating from core. IGS-2a Mass: 850 kg (1,870 lb). Spacecraft: IGS. The launch failure meant that Japan's planned intelligence satellite constellation was crippled. The system was already in trouble due to the reported poor performance of the first two elements launched.

2005 February 26 - 09:25 GMT - Tanegashima Y. H-IIA 2022 H-IIA-7F Himawari 6 Mass: 3,300 kg (7,200 lb). Spacecraft: FS-1300. Agency: Ministry of Land, Infrastructure and Transport. Perigee: 35,778 km (22,231 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.20 min. Return to flight after earlier failure; first commercial mission for H-2A. Delayed from August 2003, January 2004, and February 24, 2005. The dual-purpose satellite was to provide weather data for the Japanese Meteorological Agency (as with others in the Himawari-GMS series), and air traffic control support (airplane-ATC voice/data links, GPS augmentation and airplane position tracking) for the Japanese Civil Aviation Bureau. As of 2007 Mar 11 located at 140.26E drifting at 0.000E degrees per day.

2006 January 24 - 01:33 GMT - Tanegashima Y. H-IIA 2022 H-IIA-8F Daichi Mass: 3,850 kg (8,480 lb). Spacecraft: Daichi. Agency: JAXA. Perigee: 693 km (430 mi). Apogee: 697 km (433 mi). Inclination: 98.20 deg. Period: 98.70 min. Advanced Land Observing Satellite, which carried an L-band synthetic aperture radar, an optical 2.5-meter resolution mapping camera, and a 10-meter resolution visible/near-infrared radiometer.

2006 February 18 - 06:27 GMT - Tanegashima Y. H-IIA 2024 H-IIA-9F MTSAT-2 Mass: 3,000 kg (6,600 lb). Spacecraft: DS2000. Agency: Ministry of Land, Infrastructure and Transport. Perigee: 35,771 km (22,227 mi). Apogee: 35,803 km (22,246 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Multifunctional Transport Satellite. An aeronautical payload provided communications relay between aircraft and air traffic control; GPS augmentation navigation for aircraft; and transmitted the location of aircraft to air traffic control. A Japan Advanced Meteorological Imager weather camera had one visible and four infrared channels. MTSAT-2 was built by Mitsubishi using the new DS2000 bus. As of 2007 Mar 8 located at 144.93E drifting at 0.016W degrees per day.

2006 September 11 - 04:35 GMT - Tanegashima Y. H-IIA 202 H-IIA-10 IGS-3A Mass: 850 kg (1,870 lb). Spacecraft: IGS. Agency: JIDF. Perigee: 484 km (300 mi). Apogee: 491 km (305 mi). Inclination: 97.30 deg. Information Gathering Satellite / Optical-2 military surveillance satellite, launched to replace IGS O-1 launched in 2003, which demonstrated technical problems. The first replacement, IGS-O-2, was lost in a launch failure in 2003.

2006 December 16 - 06:32 GMT - Tanegashima Y. H-IIA 204 H-IIA-11 Kiku 8 Mass: 5,817 kg (12,824 lb). Spacecraft: ETS. Agency: JAXA. Perigee: 35,775 km (22,229 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.0500 deg. Period: 1,436.11 min. Engineering Test Satellite-8 was a Japanese prototype/operational demonstration for a number of new technologies: a large satellite bus, large-scale deployable 40-m-span antennae, mobile satellite communications system, mobile satellite digital multimedia broadcasting, and basic positioning using high-accuracy time standard devices. It will be positioned in geosynchronous orbit at 146 degrees East. JAXA developed two portable terrestrial systems to communicate directly with the satellite - a tiny telephone and a portable laptop computer. The satellite was to have a lifetime of ten years. As of 2007 Mar 11 located at 145.97E drifting at 0.010W degrees per day.

2007 February 24 - 04:41 GMT - Tanegashima Y. H-IIA 2024 H-IIA-12 IGS-2 Mass: 1,200 kg (2,600 lb). Spacecraft: IGS. Agency: JAXA/CSICE. Information Gathering Satellite Radar-2. Japanese military satellite using a synthetic aperture radar for all-weather, 24-hour, high-resolution surveillance of the earth.

2007 September 14 - 01:31 GMT - Tanegashima Y. H-IIA 2022 H-IIA-13 Kaguya Spacecraft: Kaguya. Another of a series of new lunar probes to be launched in the next few years by China, India, Japan, USA, and Europe. Selene was dubbed Kaguya, a Japanese moon goddess, after launch. It included an HDTV camera. In lunar orbit two subsatellites would be released to provide continuous communications as well as better characterize the moon's gravity field. By 30 September Kaguya was in a 2243 km x 378,132 km lunar transfer orbit. On 3 October at 21:00 GMT it entered its initial 101 km x 11741 km x 95 deg lunar orbit. It then began maneuvers to enter its operational 100 km circular orbit, releasing the subsatellites on 9 and 12 October.

2008 February 23 - 08:55 GMT - Tanegashima . Kizuna Mass: 2,700 kg (5,900 lb). Spacecraft: Kizuna. Perigee: 35,775 km (22,229 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.00 deg. Period: 1,436.10 min. WINDS, the Wide-band Internetworking Engineering Test and Demonstration Satellite, was designed to demonstrate delivery of high bandwidth Ka-band Internet service to remote areas of Japan and Southeast Asia from geostationary orbit at 143 deg E. Users with a small 45 cm in diameter antenna could receive data at up to 155 Mbps and transmit data at up to 6 Mbps.

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