Mu-3C

The Japanese Mu launcher series provided a flexible all-solid propellant launch vehicle for access to space.

Manufacturer: Nissan. Launches: 24. Failures: 3. Success Rate: 87.50%. First Launch Date: 1969-08-17. Last Launch Date: 1995-01-15. Launch data is: complete. LEO Payload: 770 kg (1,690 lb). to: 185 km Orbit. Payload: 520 kg (1,140 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: Astro, Corsa A, EXOS, Express 1, Hagoromo, Hiten, Solar, SS, Tansei. Liftoff Thrust: 1,740.000 kN (391,160 lbf). Total Mass: 62,610 kg (138,030 lb). Core Diameter: 1.50 m (4.90 ft). Total Length: 28.00 m (91.00 ft). Launch Price $: 30.000 million. in: 1994 price dollars.

4 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). Apogee: 3,500 km (2,100 mi). Liftoff Thrust: 1,932.000 kN (434,330 lbf). Total Mass: 41,600 kg (91,700 lb). Core Diameter: 1.41 m (4.62 ft). Total Length: 20.20 m (66.20 ft).

5 stage vehicle consisting of 8 x SB-310 + 1 x M-10 + 1 x M-20 + 1 x M-30 + 1 x M-40

Apogee: 160 km (90 mi). Liftoff Thrust: 1,932.000 kN (434,330 lbf). Total Mass: 40,000 kg (88,000 lb). Core Diameter: 1.41 m (4.62 ft). Total Length: 23.60 m (77.40 ft).

5 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). Apogee: 1,000 km (600 mi). Liftoff Thrust: 2,150.000 kN (483,330 lbf). Total Mass: 44,700 kg (98,500 lb). Core Diameter: 1.41 m (4.62 ft). Total Length: 23.80 m (78.00 ft).

4 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). Apogee: 1,000 km (600 mi). Liftoff Thrust: 2,150.000 kN (483,330 lbf). Total Mass: 49,300 kg (108,600 lb). Core Diameter: 1.41 m (4.62 ft). Total Length: 23.80 m (78.00 ft).

4 stage vehicle consisting of 2 x SB-735 + 1 x M-13 + 1 x M-23 + 1 x M-3B

LEO Payload: 800 kg (1,760 lb). Apogee: 1,400 km (800 mi). Liftoff Thrust: 1,930.000 kN (433,880 lbf). Total Mass: 61,700 kg (136,000 lb). Core Diameter: 1.41 m (4.62 ft). Total Length: 27.80 m (91.20 ft).

5 stage vehicle consisting of 8 x SB-310 + 1 x M-10 + 1 x M-20 + 1 x M-30 + 1 x M-40

LEO Payload: 180 kg (390 lb). Apogee: 6,500 km (4,000 mi). Liftoff Thrust: 1,932.000 kN (434,330 lbf). Total Mass: 43,600 kg (96,100 lb). Core Diameter: 1.41 m (4.62 ft). Total Length: 23.60 m (77.40 ft).

• Stage Number: 0. 2 x Stage: Mu-3S-0. Gross Mass: 5,100 kg (11,200 lb). Empty Mass: 1,080 kg (2,380 lb). Thrust (vac): 327.830 kN (73,699 lbf). Isp: 263 sec. Burn time: 38 sec. Isp(sl): 238 sec. Diameter: 0.73 m (2.39 ft). Span: 0.73 m (2.39 ft). Length: 8.25 m (27.06 ft). Propellants: Solid. No Engines: 1. Engine: SB-735. Other designations: SB-735.

• Stage Number: 1. 1 x Stage: Mu-3S-1. Gross Mass: 34,800 kg (76,700 lb). Empty Mass: 7,640 kg (16,840 lb). Thrust (vac): 1,262.419 kN (283,803 lbf). Isp: 263 sec. Burn time: 70 sec. Isp(sl): 238 sec. Diameter: 1.41 m (4.62 ft). Span: 5.00 m (16.40 ft). Length: 14.75 m (48.39 ft). Propellants: Solid. No Engines: 1. Engine: M-13. Other designations: M-13.

• Stage Number: 2. 1 x Stage: Mu-3S-2. Gross Mass: 13,100 kg (28,800 lb). Empty Mass: 2,800 kg (6,100 lb). Thrust (vac): 523.998 kN (117,799 lbf). Isp: 285 sec. Burn time: 70 sec. Isp(sl): 220 sec. Diameter: 1.41 m (4.62 ft). Span: 1.41 m (4.62 ft). Length: 6.19 m (20.30 ft). Propellants: Solid. No Engines: 1. Engine: M-23-Mu. Other designations: M-23.

• Stage Number: 3. 1 x Stage: Mu-3S-3. Gross Mass: 3,590 kg (7,910 lb). Empty Mass: 490 kg (1,080 lb). Thrust (vac): 132.115 kN (29,701 lbf). Isp: 294 sec. Burn time: 85 sec. Isp(sl): 0 sec. Diameter: 1.50 m (4.90 ft). Span: 1.50 m (4.90 ft). Length: 2.68 m (8.79 ft). Propellants: Solid. No Engines: 1. Engine: M-3B-Mu. Other designations: M-3B.

1969 August 17 - Launch Site: Kagoshima. Launch Complex: M. Launch Vehicle: Mu-3. Model: Mu-3D. LV Configuration: Mu-3D M-3D-1.

• Test mission Nation: Japan. Agency: ISAS. Apogee: 160 km (90 mi). References: 1592.

• SS Nation: Japan. Payload: MS-F1. Class: Earth. Type: Magnetosphere. Spacecraft: SS. Agency: ISAS. Apogee: 712 km (442 mi). COSPAR: F700925A. Decay Date: 1970-09-25. References: 5, 126.

• Tansei 1 Nation: Japan. Payload: MS T1. Mass: 62 kg (136 lb). Class: Technology. Spacecraft: Tansei. Agency: ISAS. Perigee: 986 km (612 mi). Apogee: 1,106 km (687 mi). Inclination: 29.70 deg. Period: 106.10 min. COSPAR: 1971-011A. USAF Sat Cat: 4952. Engineering test for the launching of scientific satellites. Injection point 29.7 N, 145.8 E References: 1, 2, 5, 6.

• SS-01 Shinsei Nation: Japan. Payload: MS-F2. Mass: 65 kg (143 lb). Class: Earth. Type: Magnetosphere. Spacecraft: SS. Agency: ISAS. Perigee: 872 km (541 mi). Apogee: 1,866 km (1,159 mi). Inclination: 32.00 deg. Period: 113.10 min. COSPAR: 1971-080A. USAF Sat Cat: 5485. Scientific observations in outer space. Injection point 29 deg 7 min N, 145 deg 8 min E. References: 1, 2, 5, 6.

• SS-02 Denpa Nation: Japan. Payload: REXS. Mass: 75 kg (165 lb). Class: Earth. Type: Magnetosphere. Spacecraft: SS. Agency: ISAS. Perigee: 238 km (147 mi). Apogee: 6,322 km (3,928 mi). Inclination: 31.00 deg. Period: 157.40 min. COSPAR: 1972-064A. USAF Sat Cat: 6152. Decay Date: 1980-05-19. Ionospheric experiments. Scientific observations in the ionosphere and magnetosphere. Interjection point 31 deg 15' N 11 deg 05' E. References: 1, 2, 5, 6.

• Tansei 2 Nation: Japan. Payload: MS T2. Mass: 65 kg (143 lb). Class: Technology. Spacecraft: Tansei. Agency: ISAS. Perigee: 284 km (176 mi). Apogee: 3,231 km (2,007 mi). Inclination: 31.20 deg. Period: 121.70 min. COSPAR: 1974-008A. USAF Sat Cat: 7122. Decay Date: 1983-01-22. Attitude control satellite (performance test of launch vehicle). References: 1, 2, 5, 6.

• SS-03 Taiyo Nation: Japan. Payload: SRATS. Mass: 86 kg (189 lb). Class: Earth. Type: Magnetosphere. Spacecraft: SS. Agency: ISAS. Perigee: 254 km (157 mi). Apogee: 3,125 km (1,941 mi). Inclination: 31.50 deg. Period: 120.20 min. COSPAR: 1975-014A. USAF Sat Cat: 7671. Decay Date: 1980-06-29. 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. References: 1, 2, 5, 6.

• Corsa A Nation: Japan. Mass: 92 kg (202 lb). Class: Technology. Spacecraft: Corsa A. Agency: ISAS. COSPAR: F760204A. Decay Date: 1976-02-04. References: 5, 126.

• Tansei 3 Nation: Japan. Payload: MS T3. Mass: 230 kg (500 lb). Class: Technology. Spacecraft: Tansei. Agency: ISAS. Perigee: 799 km (496 mi). Apogee: 3,802 km (2,362 mi). Inclination: 65.80 deg. Period: 134.10 min. COSPAR: 1977-012A. USAF Sat Cat: 9841. 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.References: 1, 2, 5, 6.

• SS-05 Kyokko Nation: Japan. Payload: Exos A. Mass: 103 kg (227 lb). Class: Earth. Type: Ionosphere. Spacecraft: EXOS. Agency: ISAS. Perigee: 639 km (397 mi). Apogee: 3,952 km (2,455 mi). Inclination: 65.40 deg. Period: 134.00 min. COSPAR: 1978-014A. USAF Sat Cat: 10664. 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.References: 1, 2, 5, 6.

• SS-06 Jikiken Nation: Japan. Payload: Exos B. Mass: 100 kg (220 lb). Class: Earth. Type: Ionosphere. Spacecraft: EXOS. Agency: ISAS. Perigee: 251 km (155 mi). Apogee: 21,192 km (13,168 mi). Inclination: 31.30 deg. Period: 370.90 min. COSPAR: 1978-087A. USAF Sat Cat: 11027. 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.References: 1, 2, 5, 6.

• SS-04 Hakucho Nation: Japan. Payload: Corsa B. Mass: 100 kg (220 lb). Class: Earth. Type: Magnetosphere. Spacecraft: SS. Agency: ISAS. Perigee: 543 km (337 mi). Apogee: 566 km (351 mi). Inclination: 29.80 deg. Period: 95.70 min. COSPAR: 1979-014A. USAF Sat Cat: 11272. Decay Date: 1985-04-15. 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.References: 1, 2, 5, 6.

• Tansei 4 Nation: Japan. Payload: MS T4. Mass: 134 kg (295 lb). Class: Technology. Spacecraft: Tansei. Agency: ISAS. Perigee: 517 km (321 mi). Apogee: 608 km (377 mi). Inclination: 38.70 deg. Period: 95.90 min. COSPAR: 1980-015A. USAF Sat Cat: 11706. Decay Date: 1983-05-12. References: 1, 2, 5, 6.

• SS-07 Hinotori Nation: Japan. Payload: Astro A. Mass: 185 kg (407 lb). Class: Astronomy. Spacecraft: Astro. Agency: ISAS. Perigee: 274 km (170 mi). Apogee: 279 km (173 mi). Inclination: 31.30 deg. Period: 90.10 min. COSPAR: 1981-017A. USAF Sat Cat: 12307. Decay Date: 1991-07-11. Hinotori (ASTRO-A). Launching organisation: Institute of Space and Aeronautical Science, University of Tokyo. Investigation of solar flare by X-ray telescope and spectrograph. References: 1, 2, 5, 6.

• SS-08 Tenma Nation: Japan. Payload: Astro B. Mass: 185 kg (407 lb). Class: Astronomy. Spacecraft: Astro. Agency: ISAS. Perigee: 431 km (267 mi). Apogee: 438 km (272 mi). Inclination: 31.50 deg. Period: 93.30 min. COSPAR: 1983-011A. USAF Sat Cat: 13829. Decay Date: 1988-12-17. 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.References: 1, 2, 5, 6.

• SS-09 Onzora Nation: Japan. Payload: Exos C. Mass: 180 kg (390 lb). Class: Earth. Type: Ionosphere. Spacecraft: EXOS. Agency: ISAS. Perigee: 247 km (153 mi). Apogee: 331 km (205 mi). Inclination: 74.60 deg. Period: 90.30 min. COSPAR: 1984-015A. USAF Sat Cat: 14722. Decay Date: 1988-12-26. 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.References: 1, 2, 5, 6.

• SS-10 Sagikake Nation: Japan. Payload: MS T5. Mass: 141 kg (310 lb). Class: Technology. Spacecraft: Tansei. Agency: ISAS. COSPAR: 1985-001A. USAF Sat Cat: 15464. Sakigake ('Pioneer') was a test spacecraft similar to Suisei (Planet-A). Objectives were :verification of fundamental technology related to interplanetary missions, including deep-space communication, attitude control, attitude determination; study and observation of solar wind and plasma waves and interplanetary magnetic field. It carried three instruments to measure plasma wave spectra, solar wind ions, and interplanetary magnetic fields. The spacecraft was spin-stabilized at two different rates (5 and 0.2 rpm). It was equipped with hydrazine thrusters for attitude and velocity control, star and sun sensors for attitude determination, and a mechanically despun off-set parabolic dish for long-range communication. Launched into an initial heliocentric orbit with a period of 318.8 days, at 151.4 x 121.9 million km (0.815 x 1.012 AU), 1.439 degree inclination. Flew by Comet Halley on its sunward side at a distance of about 7 million kilometers on March 11, 1986. It later made an Earth swingby on January 8, 1992 with a closest approach of 88,997 km. This was the first planet-swingby for a Japanese spacecraft. During the approach, Sakigake observed the geotail, with passage occurring at 290 Re on 14 June 1993 before ISTP's multi-spacecraft investigation of that region. The second Earth swingby was on June 14, 1993 at 40 Re, and the third on October 28, 1994 at 86 Re. Almost no hydrazine remained so no further maneuvers were accomplished. Telemetry contact was lost on 15 November 1995 at a distance of 106 million km. Future mission planning had included a 23.6 km/s, 10,000 km flyby of Comet Honda-Mrkos-Pajdusakova on Feb 3, 1996 (approaching the nucleus along the tail) some 0.17 AU from the Sun, and a 14 million km passage of Comet Giacobini-Zinner on Nov 29, 1998.References: 1, 2, 5, 6, 296.

• SS-11 Suisei Nation: Japan. Payload: Planet A. Mass: 141 kg (310 lb). Class: Earth. Type: Magnetosphere. Spacecraft: SS. Agency: ISAS. COSPAR: 1985-073A. USAF Sat Cat: 15967. Rendezvoused with comet Halley 3/8/86. Solar Orbit (Heliocentric). PLANET-A (SUISEI). Launch time 2333 GMT. Imaging of the hydrogen coma of Halley's comet by the hydrogen Lyman alpha line. Measurement of the solar wind in the cruising phase and in the vicinity of the comet. Launching organiza tion ISAS. Heliocentric orbit parameters 282 days, inclination 0.888 deg, 151.42 x 100.5 million km (1.0122 x 0.6718 AU).References: 1, 2, 5, 6.

• Ginga Nation: Japan. Payload: Astro C. Mass: 420 kg (920 lb). Class: Astronomy. Spacecraft: Astro. Agency: ISAS. Perigee: 395 km (245 mi). Apogee: 450 km (270 mi). Inclination: 31.00 deg. Period: 93.00 min. COSPAR: 1987-012A. USAF Sat Cat: 17480. Decay Date: 1991-11-01. Studyied galactic gamma ray, X-ray sources. ASTRO-C (Ginga). Observation of variabilities of X-rays from active galactic nuclei and galactic compact sources. Launching organization ISAS. Launch time 0630 GMT. References: 1, 2, 5, 6.

• Akebono Nation: Japan. Payload: Exos D. Mass: 295 kg (650 lb). Class: Earth. Type: Ionosphere. Spacecraft: EXOS. Agency: ISAS. Perigee: 272 km (169 mi). Apogee: 8,554 km (5,315 mi). Inclination: 75.10 deg. Period: 185.90 min. COSPAR: 1989-016A. USAF Sat Cat: 19822. Studied aurora borealis, auroral australis. EXOS-D (Akebono). Observation in high precision of behaviour and acceleration mechanism of aurora particles in Earth magnetosphere. Launching organization ISAS. Launch time 2330 GMT. References: 1, 2, 5, 6.

• Hiten Nation: Japan. Program: Muses. Payload: Muses A. Mass: 185 kg (407 lb). Class: Planetary. Type: Lunar. Spacecraft: Hiten. Agency: ISAS. Perigee: 262 km (162 mi). Apogee: 286,183 km (177,825 mi). Inclination: 30.60 deg. Period: 9,597.60 min. COSPAR: 1990-007A. USAF Sat Cat: 20448. Decay Date: 1993-04-11. MUSES-A was renamed Hiten after launch. It developed of lunar swingby techniques for future missions and ejected a lunar orbiter. Launching organization ISAS. On 1990 Jan 25: Period 6.665 days, inclination 30.63 deg, 262.49 x 286182.72 km. On 1992 Feb 17: Period 4.53 days, inclination 38.90 deg, perilune 2289.67 km, apolune 49013.93 km.References: 1, 2, 5, 6.

• Hagoromo Nation: Japan. Program: Muses. Payload: Muses A. Mass: 12 kg (26 lb). Class: Planetary. Type: Lunar. Spacecraft: Hagoromo. Agency: ISAS. COSPAR: 1990-007B. USAF Sat Cat: 20618. Lunar orbiter ejected from Muses A 3/19/90; contact lost after release; engineering test. Lunar Orbit (Selenocentric). References: 2, 5, 6.

• Solar-A Nation: Japan. Payload: Yohkoh. Mass: 420 kg (920 lb). Class: Solar. Spacecraft: Solar. Agency: ISAS. Perigee: 516 km (320 mi). Apogee: 754 km (468 mi). Inclination: 31.30 deg. Period: 97.40 min. COSPAR: 1991-062A. USAF Sat Cat: 21694. Decay Date: 2005-09-12. X-ray imaging of Sun. References: 1, 2, 5, 6.

• Asuka Nation: Japan. Payload: Astro D. Mass: 420 kg (920 lb). Class: Astronomy. Spacecraft: Astro. Agency: ISAS. Perigee: 539 km (334 mi). Apogee: 646 km (401 mi). Inclination: 31.10 deg. Period: 96.50 min. COSPAR: 1993-011A. USAF Sat Cat: 22521. Decay Date: 2001-03-02. X-ray imaging and astronomy. Imaging and spectroscopic observations of various astronomical objects (stars and galaxies) in the X-ray band. Launching organization ISAS. Launch time 0200 GMT. Astro-D 'ASCA'. References: 1, 2, 5, 6.

• Express 1 Nation: Japan. Class: Materials. Spacecraft: Express 1. Agency: ISAS. COSPAR: F950115A. Decay Date: 1995-01-15. At first thought not to have reached orbit. Later the re-entry vehicle was discovered in Ghana having reentered and deployed its parachute on January 15. At T+103 sec, during the second stage burn, the vehicle veered off course. The payload service module entered a 110 x 250 km x 33 degree orbit, instead of the intended 270 x 380 km and re-entered on its second orbit. The re-entry capsule was found later in Ghana. A failure of the second stage attitude control system was blamed, although it was considered likely that the payload was too heavy for the vehicle, being twice the mass of earlier MU-3S payloads.References: 5.

• 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.

• Evgrafov, V N, et. al., Katalog - Raketnaya i Kosmicheskaya Tekhnika, Kaluga, 1992. Tsiolokovskiy Museum catalog