Encyclopedia Astronautica
Mitsubishi


Japanese manufacturer of rockets, spacecraft, and rocket engines. Mitsubishi Electric Corp, Japan.

AKA: Mitsubishi Heavy Industries.

More... - Chronology...


Associated Countries
Associated Spacecraft
  • JERS Japanese earth land resources satellite. One launch, 1992.02.11. JERS-1 (Japanese Research Satellite-1; FUYO-1) was Japan's second Earth observation satellite. More...
  • Japanese Space Plane Japanese manned spacecraft. Study 1995. NAL / Mitsubishi Heavy Industries, Ltd. design for a single stage to orbit spaceplane. Crew of ten, empty mass 110 metric tons. LACE / Scramjet engines, 29 m wingspan. More...
  • ADEOS Japanese earth atmosphere satellite. 2 launches, 1996.08.17 (ADEOS) and 2002.12.14 (Adeos 2). The polar orbiting ADEOS spacecraft was to perform Earth, atmospheric, and oceanographic remote sensing. 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...
  • Reimei Japanese technology satellite. One launch, 2005.08.23. Plasma Science Technology. INDEX, renamed Reimei ("Dawn") after launch, was a test satellite with new lightweight satellite components, and a demonstration auroral imager payload. More...
  • DS2000 Japanese communications satellite bus. Operational, first launch 2006.02.18. Mitsubishi Electric developed the DS2000 standard satellite platform based on a design originally created for the DRTS and ETS-8 platforms for NASDA. More...

Associated Engines
  • HIMES Mitsubishi lox/lh2 rocket engine. 137.3 kN. Design 1999. Isp=452s. Used on H-2 HIMES launch vehicle. More...
  • LACE/LE-5 Mitsubishi air augmented Liquid Air/LH2 rocket engine. 147.1 kN. Design 1999. Isp=1200s. Used on H-2 HIMES launch vehicle. More...
  • LE-5 Mitsubishi lox/lh2 rocket engine. 103 kN. Isp=450s. Used on H-1 launch vehicle. First flight 1986. More...
  • LE-5A Mitsubishi lox/lh2 rocket engine. 121.5 kN. Isp=452s. Used on H-2 launch vehicle. First flight 1994. More...
  • 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-7 Mitsubishi lox/lh2 rocket engine for H-2 upper stage. 1078 kN. Staged combustion turbopump. No throttle capability. Isp=446s. First flight 1994. 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
Associated Launch Vehicles
  • S Series of Japanese single-stage sounding rockets designed for low-cost observations of the ionosphere. More...
  • LS-A Japanese test vehicle. Early suborbital test version of the Lambda rocket series. More...
  • Lambda Japanese all-solid orbital launch vehicle. All solid-propellant vehicle, Japan's first satellite launcher. The L-4S project simulated the procedures and demonstrated the capabilities required for orbital satellite launch essential to the follow-on Mu project. More...
  • S-A Japanese sounding rocket. Single stage vehicle. More...
  • S-B Japanese sounding rocket. Single stage vehicle. More...
  • LS-C Japanese test vehicle. Two stage vehicle consisting of 1 x LS-C Booster + 1 x LS-C More...
  • LSC-3 Japanese test vehicle. Early suborbital test version of the Lambda rocket series. More...
  • S-C Japanese sounding rocket. Single stage vehicle. More...
  • N-1 Delta Licensed version of Delta built in Japan using both US and Japanese components. 4 stage vehicle. More...
  • N-2 Licensed version of Delta built in Japan using both US and Japanese components. 4 stage vehicle. More...
  • H-1 Japanese license-built version of Delta launch vehicle, with Japanese-developed upper stages. More...
  • H-II Japanese orbital launch vehicle. 3 stage vehicle consisted of 2 x H-II SRB boosters + core vehicle. More...
  • 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. More...
  • H-II (2S) Japanese orbital launch vehicle. Three stage version consisting of 2 x H-II SSB boosters + 2 x H-II SRB boosters + core vehicle. More...
  • Japanese Space Plane Japanese winged orbital launch vehicle. NAL / Mitsubishi Heavy Industries, Ltd. design for a single stage to orbit spaceplane. Crew of ten, empty mass 110 tonnes. LACE / Scramjet engines, 29 m wingspan. More...
  • 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. More...
  • H-2A 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. More...
  • H-2 HIMES Japanese orbital launch vehicle. Concept of H-2 augmented with Liquid-Air Cycle Engine boosters and advanced HIMES upper stage. More...
  • H-IIA 202 Japanese orbital launch vehicle. Three stage version of H-IIA consisting of 2 x H-II SRB-A + two-stage core vehicle. More...
  • H-IIA 2024 Japanese orbital launch vehicle. Three stage vehicle consisting of 4 x Castor 4XL + 2 x H-II SRB-A boosters + two-stage core vehicle. More...
  • H-IIB Japanese orbital launch vehicle, utilizing H-IIA engines, but with larger-diameter all-new stages. Designed to place Japanese ISS HTV logistics vehicle into orbit. More...

Associated Stages
  • LS-A-1 Solid propellant rocket stage. Loaded mass 400 kg. Thrust 60.00 kN. More...
  • LS-A-2 Solid propellant rocket stage. Loaded mass 300 kg. Thrust 10.00 kN. More...
  • LS-C-1 Solid propellant rocket stage. Loaded mass 300 kg. More...
  • LS-C-2 Solid propellant rocket stage. Loaded mass 300 kg. More...
  • NAL-16-1 Solid rocket stage. 10.00 kN (2,248 lbf) thrust. Mass 100 kg (220 lb). More...
  • S-A-1 Solid propellant rocket stage. Loaded mass 100 kg. More...
  • S-B-1 Solid propellant rocket stage. Loaded mass 100 kg. More...
  • S-C-1 Solid propellant rocket stage. Loaded mass 100 kg. More...

Mitsubishi Chronology


2002 September 10 - . 08:20 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024. LV Configuration: H-IIA 2024 H-IIA-3F.
  • USERS - . Mass: 1,726 kg (3,805 lb). Nation: Japan. Agency: NASDA. Manufacturer: Mitsubishi. Class: Materials. Type: Materials science satellite. Spacecraft: USERS. Decay Date: 2007-06-15 . USAF Sat Cat: 27515 . COSPAR: 2002-042A. Apogee: 508 km (315 mi). Perigee: 497 km (308 mi). Inclination: 30.4000 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.
  • DRTS - . Payload: Kodama (DRTS-W). Mass: 2,800 kg (6,100 lb). Nation: Japan. Agency: NASDA. Manufacturer: Mitsubishi. Class: Communications. Type: Civilian communications satellite. Spacecraft: DRTS. USAF Sat Cat: 27516 . COSPAR: 2002-042B. Apogee: 35,804 km (22,247 mi). Perigee: 35,770 km (22,220 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Launch delayed from August 2002. First operational flight of H-2A booster. DRTS (Data Relay Transponder Satellite) was a Japanese geostationary communications spacecraft which was to relay images and data procured by the to-be-launched ADEOS 2 and ALOS satellites, and the KIBO module on ISS, after being parked over 90 E. However the engine failed after a couple of burns. As of 2007 Mar 11 located at 90.76E drifting at 0.005W degrees per day.

2002 December 14 - . 23:04 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202. LV Configuration: H-IIA 202 H-IIA-4F.
  • Adeos 2 - . Payload: Midori 2. Mass: 3,730 kg (8,220 lb). Nation: Japan. Agency: NASDA. Manufacturer: Mitsubishi. Class: Earth. Type: Earth resources satellite. Spacecraft: Adeos. USAF Sat Cat: 27597 . COSPAR: 2002-056A. Apogee: 806 km (500 mi). Perigee: 804 km (499 mi). Inclination: 98.7000 deg. Period: 101.00 min. Summary: Environment Monitoring, Aeronomy..

2005 August 23 - . 21:10 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC109. Launch Pad: LC109/95. LV Family: R-36M. Launch Vehicle: Dnepr. LV Configuration: Dnepr 1.
  • Reimei - . Payload: Index. Mass: 60 kg (132 lb). Nation: Japan. Agency: JAXA. Manufacturer: Mitsubishi. Class: Technology. Type: Navigation technology satellite. Spacecraft: Reimei. USAF Sat Cat: 28810 . COSPAR: 2005-031B. Apogee: 650 km (400 mi). Perigee: 601 km (373 mi). Inclination: 97.8000 deg. Period: 97.20 min. Summary: Plasma Science Technology. INDEX, renamed Reimei ("Dawn") after launch, was a test satellite with new lightweight satellite components, and a demonstration auroral imager payload..

2006 February 18 - . 06:27 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024. LV Configuration: H-IIA 2024 H-IIA-9F.
  • MTSAT-2 - . Payload: MT-Sat 2. Mass: 3,000 kg (6,600 lb). Nation: Japan. Agency: MLIT. Manufacturer: Mitsubishi. Class: Earth. Type: Weather satellite. Spacecraft: DS2000. USAF Sat Cat: 28937 . COSPAR: 2006-004A. Apogee: 35,803 km (22,246 mi). Perigee: 35,771 km (22,227 mi). Inclination: 0.0000 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.

2007 September 14 - . 01:31 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2022. LV Configuration: H-IIA 2022 H-IIA-13.
  • Kaguya - . Payload: Selene. Nation: Japan. Agency: Mitsubishi. Class: Moon. Type: Lunar probe. Spacecraft: Kaguya. USAF Sat Cat: 32054 . COSPAR: 2007-039A. 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.
  • Okina - . Payload: Selene. Nation: Japan. Agency: Mitsubishi. Class: Moon. Type: Lunar probe. Spacecraft: Kaguya. USAF Sat Cat: 32055 . COSPAR: 2007-039B. Summary: The Okina relay satellite was released from Kaguya into a 115 km x 2,399 km lunar orbit at 00:36 GMT on 9 October 2007..
  • Ouna - . Payload: Selene. Nation: Japan. Agency: Mitsubishi. Class: Moon. Type: Lunar probe. Spacecraft: Kaguya. USAF Sat Cat: 32056 . COSPAR: 2007-039C. Summary: The Ouna (VRAD) subsatellite was released from Kaguya into a 127 km x 795 km lunar orbit at 04:28 GMT on 12 October 2007..

2008 February 23 - . 08:55 GMT - . Launch Site: Tanegashima. LV Family: H-2. Launch Vehicle: H-IIA 2024. LV Configuration: H-IIA 2024 s/n F14.
  • Kizuna - . Mass: 2,700 kg (5,900 lb). Nation: Japan. Agency: Mitsubishi. Class: Communications. Type: Military communications satellite. Spacecraft: Kizuna. USAF Sat Cat: 32500 . COSPAR: 2008-007A. Apogee: 35,799 km (22,244 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.0000 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.

2009 January 23 - . 03:54 GMT - . Launch Site: Tanegashima. LV Family: H-2. Launch Vehicle: H-IIA 202.
  • Ibuki - . Mass: 1,750 kg (3,850 lb). Nation: Japan. Agency: JAXA. Manufacturer: Mitsubishi. Class: Earth. Type: Earth resources satellite. Spacecraft: Ibuki. USAF Sat Cat: 33492 . COSPAR: 2009-002A. Apogee: 672 km (417 mi). Perigee: 669 km (415 mi). Inclination: 98.0000 deg. Period: 98.20 min. Summary: Greenhouse Gas Observing Satellite, renamed Ibuki after launch. The satellite carried a TANSO-FTS IR spectrometer and TANSO-CAI cloud and aerosol imager..
  • PRISM - . Mass: 5.00 kg (11.00 lb). Nation: Japan. Agency: Mitsubishi. Class: Surveillance. Type: Military surveillance radar satellite. Spacecraft: PRISM. USAF Sat Cat: 33493 . COSPAR: 2009-002B. Apogee: 641 km (398 mi). Perigee: 614 km (381 mi). Inclination: 98.0000 deg. Period: 97.30 min. Summary: Remote sensing picosatellite built by the University of Tokyo, with a 10-cm aperture Earth imager on a 1-meter deployable boom..
  • SDS-1 - . Mass: 100 kg (220 lb). Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Navigation technology satellite. Spacecraft: JAXA SDS. USAF Sat Cat: 33494 . COSPAR: 2009-002C. Apogee: 668 km (415 mi). Perigee: 663 km (411 mi). Inclination: 98.0000 deg. Period: 98.00 min. Summary: JAXA Small Demonstration Satellite, a microsatellite with a camera, GPS receiver and sun sensor..
  • SOHLA-1 - . Mass: 50 kg (110 lb). Nation: Japan. Agency: Mitsubishi. Class: Surveillance. Type: Military surveillance radar satellite. Spacecraft: SOHLA. USAF Sat Cat: 33495 . COSPAR: 2009-002D. Apogee: 667 km (414 mi). Perigee: 654 km (406 mi). Inclination: 98.0000 deg. Period: 98.00 min. Summary: Satellite built by the Space Oriented Higashi-osaka Leading Association, Osaka, carrying a cloud cover imager..
  • SpriteSat - . Mass: 50 kg (110 lb). Nation: Japan. Agency: Mitsubishi. Class: Earth. Type: Earth resources satellite. Spacecraft: SpriteSat. USAF Sat Cat: 33496 . COSPAR: 2009-002E. Apogee: 668 km (415 mi). Perigee: 658 km (408 mi). Inclination: 98.0000 deg. Period: 98.00 min. Summary: Microsatellite stabilized by a gravity gradient boom to study atmospheric sprites, built by by Tohoku University, Sendai..
  • Kagayaki - . Mass: 28 kg (61 lb). Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Navigation technology satellite. Spacecraft: Kagayaki. USAF Sat Cat: 33497 . COSPAR: 2009-002F. Apogee: 670 km (410 mi). Perigee: 668 km (415 mi). Inclination: 98.0000 deg. Period: 98.10 min. Summary: Technology satellite built by Sorun Corporation, Tokyo, with several technology payloads..
  • Kukai - . Mass: 5.00 kg (11.00 lb). Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Navigation technology satellite. Spacecraft: Kukai. USAF Sat Cat: 33498 . COSPAR: 2009-002G. Apogee: 667 km (414 mi). Perigee: 647 km (402 mi). Inclination: 98.0000 deg. Period: 97.90 min. Summary: Also named STARS, a Kagawa University picosatellite demonstrating a tethered space robot. It consisted of two tethered box-shaped packages, dubbed Ku and Kai..
  • KKS 1 - . Mass: 3.00 kg (6.60 lb). Nation: Japan. Agency: Mitsubishi. Class: Surveillance. Type: Military surveillance radar satellite. Spacecraft: KKS. USAF Sat Cat: 33499 . COSPAR: 2009-002H. Apogee: 667 km (414 mi). Perigee: 651 km (404 mi). Inclination: 98.0000 deg. Period: 97.90 min. Summary: Picosatellite built by Kouku-kosen, the Tokyo Metropolitan College of Aeronautical Engineering, carrying an Earth imager..

2009 November 28 - . 01:21 GMT - . Launch Site: Tanegashima. LV Family: H-2. Launch Vehicle: H-IIA 202. LV Configuration: H-IIA 202 s/n F16.
  • IGS O-3 - . Nation: USA. Agency: Mitsubishi. Spacecraft: IGS. USAF Sat Cat: 36104 . COSPAR: 2009-066A. Summary: Information Gathering Satellite, an optical surveillance satellite operated by Japan's Cabinet Satellite Intelligence Center..

2010 May 20 - . 21:58 GMT - . Launch Site: Tanegashima. LV Family: H-2. Launch Vehicle: H-IIA 202.
  • Hayato - . Payload: K-SAT. Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: Mitsubishi. Spacecraft: Cubesat. Decay Date: 2010-06-28 . USAF Sat Cat: 36573 . COSPAR: 2010-020A. Apogee: 172 km (106 mi). Perigee: 166 km (103 mi). Inclination: 30.0000 deg. Period: 87.90 min. Summary: Cubesat for Kagoshima University, released in parking orbit..
  • Waseda-SAT2 - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: Mitsubishi. Class: Surveillance. Type: Surveillance satellite. Spacecraft: Cubesat. Decay Date: 2010-07-12 . USAF Sat Cat: 36574 . COSPAR: 2010-020B. Apogee: 183 km (113 mi). Perigee: 177 km (109 mi). Inclination: 30.0000 deg. Period: 88.10 min. Summary: Cubesat for Waseda University, Tokyo, released in parking orbit..
  • Negai - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: Mitsubishi. Class: Surveillance. Type: Surveillance satellite. Spacecraft: Cubesat. Decay Date: 2010-06-26 . USAF Sat Cat: 36575 . COSPAR: 2010-020C. Apogee: 190 km (110 mi). Perigee: 176 km (109 mi). Inclination: 30.0000 deg. Period: 88.20 min. Summary: Cubesat for Soka University, Tokyo, released in parking orbit..
  • Akatsuki - . Payload: Planet-C. Mass: 320 kg (700 lb). Nation: Japan. Agency: Mitsubishi. Class: Venus. Type: Venus probe. Spacecraft: Akatsuki. USAF Sat Cat: 36576 . COSPAR: 2010-020D. Summary: Venus-orbiting weather satellite with visible, infrared and ultraviolet cameras. Reached Venus on 6 December 2010 but the main engine malfunctioned, preventing the braking burn into Venus orbit. The spacecraft sailed past Venus into solar orbit..
  • Ikaros - . Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Solar sail technology satellite. Spacecraft: Ikaros. USAF Sat Cat: 36577 . COSPAR: 2010-020E. Solar sail test vehicle. Released in solar orbit 0.72 AU x 1.07 AU x 2.0 deg. Deployed sail by 11 June, and acceleration due to the pressure of the light from the sun was as expected. Flyby of Venus at 80,000 km distance at 07:39 GMT on 8 December 2010 returned images of sail with crescent Vensu in the background.
  • Unitec-1 - . Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Technology satellite. Spacecraft: Unitec. USAF Sat Cat: 36578 . COSPAR: 2010-020F. Summary: Space qualification of university-built computers. Released in solar orbit 0.72 AU x 1.07 AU x 2.0 deg..

2010 September 11 - . 11:17 GMT - . Launch Site: Tanegashima. LV Family: H-2. Launch Vehicle: H-IIA 202.
  • QZS-1 - . Payload: Michibiki. Nation: Japan. Agency: Mitsubishi. Class: Navigation. Type: Navigation satellite. Spacecraft: QZS. USAF Sat Cat: 37158 . COSPAR: 2010-045A. Apogee: 38,944 km (24,198 mi). Perigee: 32,632 km (20,276 mi). Inclination: 40.9000 deg. Period: 1,436.20 min. Quasi-Zenith Satellite System; carried an L-band navigation package to augment GPS and a C-band transponder for communications. Placed in an inclined geosynchronous orbit that brings nearly overhead of Japan at peak usage hours, providing a better navigation and communications signal to users which normally would have equatorial geosynchronous satellite and medium-earth-orbit navigation satellite signals interfered with by tall buildings or steep canyons.

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