Encyclopedia Astronautica
Mu-3C


Japanese all-solid orbital launch vehicle. Four stage vehicle consisting of 8 x SB-310 + 1 x M-10 + 1 x M-22TVC + 1 x M-3A

LEO Payload: 195 kg (429 lb). Failures: 1. First Fail Date: 1976-02-04. Last Fail Date: 1976-02-04.

Gross mass: 41,600 kg (91,700 lb).
Payload: 195 kg (429 lb).
Height: 20.20 m (66.20 ft).
Diameter: 1.41 m (4.62 ft).
Thrust: 1,932.00 kN (434,330 lbf).
Apogee: 3,500 km (2,100 mi).
First Launch: 1974.02.16.
Last Launch: 1979.02.21.
Number: 4 .

More... - Chronology...


Associated Countries
Associated Spacecraft
  • SS Japanese earth magnetosphere satellite. 6 launches, 1970.09.25 (SS) to 1985.08.18 (SS-11 Suisei). Scientific observations in outer space. More...
  • 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...
  • Corsa A Japanese technology satellite. One launch, 1976.02.04. Japanese technology satellite. 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
  • 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-4S-1 Solid rocket stage. 737.00 kN (165,684 lbf) thrust. Mass 26,600 kg (58,643 lb). More...

Mu-3C Chronology


1974 February 16 - . 05:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3C. LV Configuration: Mu-3C M-3C-1.
  • Tansei 2 - . Payload: MS T2. Mass: 65 kg (143 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Tansei. Decay Date: 1983-01-22 . USAF Sat Cat: 7122 . COSPAR: 1974-008A. Apogee: 3,231 km (2,007 mi). Perigee: 284 km (176 mi). Inclination: 31.2000 deg. Period: 121.70 min. Summary: Attitude control satellite (performance test of launch vehicle). .

1975 February 24 - . 05:25 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3C. LV Configuration: Mu-3C M-3C-2.
  • SS-03 Taiyo - . Payload: SRATS. Mass: 86 kg (189 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SS. Decay Date: 1980-06-29 . USAF Sat Cat: 7671 . COSPAR: 1975-014A. Apogee: 3,125 km (1,941 mi). Perigee: 254 km (157 mi). Inclination: 31.5000 deg. Period: 120.20 min. Examined solar radiation, thermospheric structure. SRATS (Solar and Thermospheric Radiation Satellite) is the third Japanese scientific satellite, to study the intereffects of solar radiation and the thermosphere of the earth. National name: Taiyo. Launch time 0525 GMT.

1976 February 4 - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3C. LV Configuration: Mu-3C M-3C-3. FAILURE: Stage 2 thrust vector control failure.. Failed Stage: 2.
  • Corsa A - . Mass: 92 kg (202 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Corsa A. Decay Date: 1976-02-04 . COSPAR: F760204A.

1979 February 21 - . 05:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3C. LV Configuration: Mu-3C M-3C-4.
  • SS-04 Hakucho - . Payload: Corsa B. Mass: 100 kg (220 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SS. Decay Date: 1985-04-15 . USAF Sat Cat: 11272 . COSPAR: 1979-014A. Apogee: 566 km (351 mi). Perigee: 543 km (337 mi). Inclination: 29.8000 deg. Period: 95.70 min. Soft X-ray telescope. Launching organization: Institute of Space and Aeronautical Science, University of Tokyo. Function: Observation of X-ray radiation of celestial bodies with good time resolution over a wide spectrum range. Characterstics: weight 96 kg, configuration regula r octagonal prism, height 0.66 m, diameter 0.76m, spin stabilized. Expected life 2 years.

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