Encyclopedia Astronautica
Mu-3S



mu3c.jpg
Mu-3C
Mu-3C - COSPAR 1975-014
Japanese all-solid orbital launch vehicle. Four stage vehicle consisting of 8 x SB-310 + 1 x M-13TVC + 1 x M-22TVC + 1 x M-3A

LEO Payload: 300 kg (660 lb).

Gross mass: 49,300 kg (108,600 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: 1980.02.17.
Last Launch: 1984.02.14.
Number: 4 .

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...
  • Astro Japanese x-ray astronomy satellite. 4 launches, 1981.02.21 (SS-07 Hinotori) to 1993.02.20 (Asuka). X-ray experiments. Launching organization: ISAS (Institute of Space and Astronautical Science). More...

Associated Engines
  • M-13 Nissan solid rocket engine. 1262.4 kN. Isp=263s. Used on Mu-3S launch vehicle. First flight 1969. More...
  • M-23-Mu Nissan solid rocket engine. 524 kN. Isp=285s. Used on Mu-3S launch vehicle. First flight 1969. More...
  • M-3B-Mu Nissan solid rocket engine. 132.1 kN. Isp=294s. Used on Mu-3S launch vehicle. First flight 1969. More...
  • SB-735 Nissan solid rocket engine. 327.8 kN. Isp=263s. Used on Mu-3S launch vehicle. First flight 1969. 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-13TVC Solid rocket stage. 1020.00 kN (229,305 lbf) thrust. Mass 34,200 kg (75,398 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 Chronology


1980 February 17 - . 00:40 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3S. LV Configuration: Mu-3S M-3S-1.
  • Tansei 4 - . Payload: MS T4. Mass: 134 kg (295 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Tansei. Decay Date: 1983-05-12 . USAF Sat Cat: 11706 . COSPAR: 1980-015A. Apogee: 608 km (377 mi). Perigee: 517 km (321 mi). Inclination: 38.7000 deg. Period: 95.90 min.

1981 February 21 - . 00:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3S. LV Configuration: Mu-3S M-3S-2.
  • SS-07 Hinotori - . Payload: Astro A. Mass: 185 kg (407 lb). Nation: Japan. Agency: ISAS. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: Astro. Decay Date: 1991-07-11 . USAF Sat Cat: 12307 . COSPAR: 1981-017A. Apogee: 279 km (173 mi). Perigee: 274 km (170 mi). Inclination: 31.3000 deg. Period: 90.10 min. Summary: Hinotori (ASTRO-A). Launching organisation: Institute of Space and Aeronautical Science, University of Tokyo. Investigation of solar flare by X-ray telescope and spectrograph. .

1983 February 20 - . 05:10 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. Launch Pad: M1. LV Family: Mu. Launch Vehicle: Mu-3S. LV Configuration: Mu-3S M-3S-3.
  • SS-08 Tenma - . Payload: Astro B. Mass: 185 kg (407 lb). Nation: Japan. Agency: ISAS. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: Astro. Decay Date: 1988-12-17 . USAF Sat Cat: 13829 . COSPAR: 1983-011A. Apogee: 438 km (272 mi). Perigee: 431 km (267 mi). Inclination: 31.5000 deg. Period: 93.30 min. X-ray experiments. Astro-B (Tenma). Launch 0510 GMT. Launching organization: ISAS (Institute of Space and Astronautical Science). X-ray observation of X-ray stars in our galaxy as well as X-ray galaxies using a scintillating proportional counter, a transient X-ray source mo nitor, an X-ray foucsing collector, a radiation belt monitor, a gamma ray burst detector and a star sensor.

1984 February 14 - . 08:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. Launch Pad: M1. LV Family: Mu. Launch Vehicle: Mu-3S. LV Configuration: Mu-3S M-3S-4.
  • SS-09 Onzora - . Payload: Exos C. Mass: 180 kg (390 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Ionosphere satellite. Spacecraft: EXOS. Decay Date: 1988-12-26 . USAF Sat Cat: 14722 . COSPAR: 1984-015A. Apogee: 331 km (205 mi). Perigee: 247 km (153 mi). Inclination: 74.6000 deg. Period: 90.30 min. Optical investigations of ionosphere. EXOS-C (OHZORA). Optical study of the stratosphere and middle atmosphere. Study of the specific phenomena of the ionospheric plasma over the southern Atlantic geomagnetic anomaly zone which was discovered by the third scientific satellite 'TAIYO'. Launch vehicle Mu-3S-4, launching organization ISAS (Institute of Space and Astronautical Science). Launch time 0800 GMT.

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