H-2 Media Gallery

Heavy lift Japanese indigenous launch vehicle. Cancelled due to high costs and poor reliability by 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: 7. Failures: 2. Success Rate: 71.43%. First Launch Date: 1994-02-03. Last Launch Date: 1999-11-15. Launch data is: complete. 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.

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

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).

3 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 Number: 0. 2 x Stage: H-2-0. Gross Mass: 70,400 kg (155,200 lb). Empty Mass: 11,250 kg (24,800 lb). Thrust (vac): 1,539.997 kN (346,205 lbf). Isp: 273 sec. Burn time: 94 sec. Isp(sl): 237 sec. Diameter: 1.81 m (5.93 ft). Span: 1.81 m (5.93 ft). Length: 23.36 m (76.64 ft). Propellants: Solid. No Engines: 1. Engine: H-2-0.

• Stage Number: 1. 1 x Stage: H-2-1. Gross Mass: 98,100 kg (216,200 lb). Empty Mass: 11,900 kg (26,200 lb). Thrust (vac): 1,077.996 kN (242,343 lbf). Isp: 446 sec. Burn time: 346 sec. Isp(sl): 349 sec. Diameter: 4.00 m (13.10 ft). Span: 4.00 m (13.10 ft). Length: 28.00 m (91.00 ft). Propellants: Lox/LH2. No Engines: 1. Engine: LE-7. Other designations: LE-7.

• Stage Number: 2. 1 x Stage: H-2-2. Gross Mass: 16,700 kg (36,800 lb). Empty Mass: 2,700 kg (5,900 lb). Thrust (vac): 121.500 kN (27,314 lbf). Isp: 452 sec. Burn time: 600 sec. Diameter: 4.00 m (13.10 ft). Span: 4.00 m (13.10 ft). Length: 10.60 m (34.70 ft). Propellants: Lox/LH2. No Engines: 1. Engine: LE-5A. Other designations: LE-5EC.

1994 February 3 - 22:20 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: Y. Launch Vehicle: H-2. Model: H-II. LV Configuration: H-II-1F.

• OREX Nation: Japan. Payload: Ryusei. Mass: 865 kg (1,906 lb). Class: Technology. Type: RV. Spacecraft: OREX. Agency: NASDA/NA. Perigee: 450 km (270 mi). Apogee: 451 km (280 mi). Inclination: 30.50 deg. Period: 93.50 min. COSPAR: 1994-007A. USAF Sat Cat: 22978. Decay Date: 1994-02-03. 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. References: 1, 2, 5, 6.

• VEP Nation: Japan. Payload: Myojo / LAPS. Mass: 2,391 kg (5,271 lb). Class: Technology. Spacecraft: VEP. Agency: NASDA. Perigee: 449 km (278 mi). Apogee: 36,261 km (22,531 mi). Inclination: 28.60 deg. Period: 645.00 min. COSPAR: 1994-007B. USAF Sat Cat: 22979. Vehicle Evaluation Payload; monitored H-2 performance. Vehicle Evaluation Payload (VEP) MYOJO. Provides a ranging function as well as functions to measure the acceleration and deformation, in order to confirm the accuracy of the H-II rocket orbit injection and understand the environment of the payload equipme nt. Launch vehicle H-II rocket test flight H-II 1F. Launching organization NASDA. Launch time 2220:00 UT.References: 1, 2, 5, 6.

• Kiku 6 Nation: Japan. Payload: ETS 6. Mass: 3,800 kg (8,300 lb). Class: Technology. 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. COSPAR: 1994-056A. USAF Sat Cat: 23230. Failed to reach geostationary orbit; Engineering Test Satellite; partial mission success. Also tested ion engines for NSSK. References: 2, 5, 6.

• SFU Nation: Japan. Mass: 4,000 kg (8,800 lb). Class: Materials. Spacecraft: SFU. Agency: NASDA. Perigee: 471 km (292 mi). Apogee: 483 km (300 mi). Inclination: 28.50 deg. Period: 94.10 min. COSPAR: 1995-011A. USAF Sat Cat: 23521. Decay Date: 1996-01-20. Space Flyer Unit; carried materials, astronomy, biological experiments; retrieved by STS-72 1/20/96. References: 2, 5, 6.

• Himawari 5 Nation: Japan. Payload: GMS 5. Mass: 746 kg (1,644 lb). Class: Earth. Type: Weather. Spacecraft: GMS. Agency: NASDA. Perigee: 35,784 km (22,235 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.60 deg. Period: 1,436.00 min. COSPAR: 1995-011B. USAF Sat Cat: 23522. Geostationary Meteorological Satellite; carried search and rescue package. Stationed at 140.2 deg E. Positioned in geosynchronous orbit at 160 deg E in 1995; 140 deg E in 1995-1999 As of 5 September 2001 located at 139.99 deg E drifting at 0.028 deg W per day. As of 2007 Mar 10 located at 45.88E drifting at 3.134W degrees per day.References: 2, 5, 6.

• ADEOS Nation: Japan. Class: Earth. Type: Atmosphere. Spacecraft: ADEOS. Agency: NASDA. Perigee: 799 km (496 mi). Apogee: 800 km (490 mi). Inclination: 98.60 deg. Period: 100.90 min. COSPAR: 1996-046A. USAF Sat Cat: 24277. References: 4.

• JAS-2 Nation: Japan. Class: Communications. Spacecraft: Fuji. Agency: JARL. Perigee: 801 km (497 mi). Apogee: 1,323 km (822 mi). Inclination: 98.60 deg. Period: 106.50 min. COSPAR: 1996-046B. USAF Sat Cat: 24278. Japanese amateur radio satellite. References: 4.

• TRMM Nation: USA. Class: Earth. Type: Atmosphere. Spacecraft: TRMM. Agency: NASA GSF. Manufacturer: NASA Goddard Space Flight Center, Greenbelt. Perigee: 395 km (245 mi). Apogee: 403 km (250 mi). Inclination: 35.00 deg. Period: 92.50 min. COSPAR: 1997-074A. USAF Sat Cat: 25063. 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. References: 4.

• Hikoboshi Nation: Japan. Payload: ETS-7. Class: Technology. Spacecraft: ETS-7. Agency: NASDA. Manufacturer: Toshiba Corp., Tokyo. Perigee: 545 km (338 mi). Apogee: 548 km (340 mi). Inclination: 35.00 deg. Period: 95.50 min. COSPAR: 1997-074B. USAF Sat Cat: 25064. The Orihime and Hikoboshi satellites undocked and redocked on July 7 1998 in the FP-1 test of automated docking systems. Despite claims of the NASDA space agency that this is a first, automated Russian craft have docked on many occasions since the Kosmos-186/188 docking in 1968.References: 4.

• Orihime Nation: Japan. Payload: ETS-7 Target. Class: Technology. Spacecraft: ETS-7 Target. Agency: NASDA. Manufacturer: Toshiba Corp., Tokyo. Perigee: 346 km (214 mi). Apogee: 458 km (284 mi). Inclination: 34.50 deg. Period: 92.60 min. COSPAR: 1997-074E. USAF Sat Cat: 25424. Decay Date: 1999-01-27. Attached to Hikoboshi. It would later separate and serve as a passive docking target for the Hikobishi active automatic docking technology spacecraft. References: 4, 276.

• Kakehashi Nation: Japan. Payload: COMETS. Class: Communications. Spacecraft: Kakehashi. Agency: NASDA. Manufacturer: Toshiba/NEC. Perigee: 1,033 km (641 mi). Apogee: 17,727 km (11,015 mi). Inclination: 30.10 deg. Period: 328.10 min. COSPAR: 1998-011A. USAF Sat Cat: 25175. 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.References: 4, 276.

• MTSAT Nation: Japan. Class: Communications. Spacecraft: FS-1300. Agency: National Space Development Agency, Japan. Manufacturer: Space Systems/Loral, Palo Alto. COSPAR: F991115A. 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.

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.

• Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition). ISBN: 1563473534. Superseded by the later editions. More at amazon.com...

• Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al. ISBN: 0710618107. The most comprehensive source of information for current space projects. Too expensive for human beings and most libraries. More at amazon.com...

• Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004. ISBN: 156347591X. The best reference on launch vehicles ever produced. More at amazon.com...