Encyclopedia Astronautica
Mu-3H


Japanese all-solid orbital launch vehicle. Five stage vehicle consisting of 8 x SB-310 + 1 x M-13 + 1 x M-22TVC + 1 x M-3A + 1 x KM-H

LEO Payload: 300 kg (660 lb).

Gross mass: 44,700 kg (98,500 lb).
Payload: 300 kg (660 lb).
Height: 23.80 m (78.00 ft).
Diameter: 1.41 m (4.62 ft).
Thrust: 2,150.00 kN (483,330 lbf).
Apogee: 1,000 km (600 mi).
First Launch: 1977.02.19.
Last Launch: 1978.09.16.
Number: 3 .

More... - Chronology...


Associated Countries
Associated Spacecraft
  • Tansei Japanese technology satellite. 5 launches, 1971.02.16 (Tansei 1) to 1985.01.07 (SS-10 Sagikake). Series of spacecraft of varying configurations built for engineering tests of scientific satellite equipment. More...
  • EXOS Japanese earth ionosphere satellite. 4 launches, 1978.02.04 (SS-05 Kyokko) to 1989.02.21 (Akebono). Optical investigations of ionosphere. EXOS-C (OHZORA). More...

See also
  • Mu The Japanese Mu launcher series provided a flexible all-solid propellant launch vehicle for access to space. It was the first Japanese launch vehicle designed from the start as an orbital launch vehicle. More...

Associated Manufacturers and Agencies
  • Nissan Japanese manufacturer of rocket engines and rockets. Nissan, Japan. More...

Associated Launch Sites
  • Kagoshima Japanese launch center for solid fueled sounding rockets and satellite launchers. Limited to two months a year due to disturbance of local fisheries. More...

Associated Stages
  • KM-H Solid rocket stage. Mass 100 kg (220 lb). More...
  • M-22 Solid rocket stage. 285.00 kN (64,071 lbf) thrust. Mass 9,800 kg (21,605 lb). More...
  • M-3A Solid rocket stage. 61.00 kN (13,713 lbf) thrust. Mass 1,100 kg (2,425 lb). More...
  • Mu-3C-0 Solid rocket stage. 95.00 kN (21,357 lbf) thrust. Mass 500 kg (1,102 lb). More...
  • Mu-3S-1 Solid propellant rocket stage. Loaded/empty mass 34,800/7,640 kg. Thrust 1,262.42 kN. Vacuum specific impulse 263 seconds. More...

Mu-3H Chronology


1977 February 19 - . 05:15 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3H. LV Configuration: Mu-3H M-3H-1.
  • Tansei 3 - . Payload: MS T3. Mass: 230 kg (500 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Tansei. USAF Sat Cat: 9841 . COSPAR: 1977-012A. Apogee: 3,802 km (2,362 mi). Perigee: 799 km (496 mi). Inclination: 65.8000 deg. Period: 134.10 min. Tentative name before launching: MS-T3. Launching organization: Institute of Space and Aeronautical Science, University of Tokyo. Radio frequencies: 136.725 MHz, tracking; 400.500 MHz, telemetry. Active life: two weeks. Function: (1) Test of the overall p erformance of the newly developed launch vehicle, M-3H-1. (2) Experiment of magnetic stabilization. (3) Observation of ultraviolet radiation.

1978 February 4 - . 07:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3H. LV Configuration: Mu-3H M-3H-2.
  • SS-05 Kyokko - . Payload: Exos A. Mass: 103 kg (227 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Ionosphere satellite. Spacecraft: EXOS. USAF Sat Cat: 10664 . COSPAR: 1978-014A. Apogee: 3,952 km (2,455 mi). Perigee: 639 km (397 mi). Inclination: 65.4000 deg. Period: 134.00 min. Auroral studies. Active life - two years. Function: 1) Observation of wide angle global auroral pictures using UV television camera. 2) Spectrophotometry of ultraviolet air glow. 3) Observation of the energy spectrum of photoelectrons and auroral electrons. 4) Mass spect rometry of the ionized atmospheric species in the thermosphere. 5) Measurements of density and temperature of ambient electrons in the thermosphere. 6) Observation of electromagnetic and plasma waves and the emission associated with auroral phenomena.

1978 September 16 - . 05:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3H. LV Configuration: Mu-3H M-3H-3.
  • SS-06 Jikiken - . Payload: Exos B. Mass: 100 kg (220 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Ionosphere satellite. Spacecraft: EXOS. USAF Sat Cat: 11027 . COSPAR: 1978-087A. Apogee: 21,192 km (13,168 mi). Perigee: 251 km (155 mi). Inclination: 31.3000 deg. Period: 370.90 min. Launching organization: Institute of Space and Aeronautical Science, University of Tokyo. Stimulated plasma wave experiment, natural plasma wave measurement, plasma parameter measurement by VLF Doppler technique, electric field probe and plasma density me asurement, energetic particle analysis, and controlled electron beam emission experiment. Characteristics: weight 90.5 kg, configuration - polyhedron with 38 faces, height 0.6m , diameter 0.75m, attitude control spin stabilization, life two years.

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