Mu-3C

All-solid orbital launch vehicle. Country: Japan. Status: Retired 1995.

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.

Manufacturer: Nissan. Launches: 27. Failures: 3. Success Rate: 88.89%. First Launch Date: 1966-10-31. Last Launch Date: 1995-01-15. Launch data is: complete. Version:

Mu-1. Test vehicle.

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

Launches: 1. First Launch Date: 1966-10-31. Last Launch Date: 1966-10-31. Apogee: 50 km (31 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: 21.90 m (71.80 ft).

• Stage0: 8 x Mu-3C-0. Gross Mass: 500 kg (1,100 lb). Empty Mass: 190 kg (410 lb). Motor: 1 x SB-310. Thrust (vac): 95.000 kN (21,356 lbf). Burn time: 7.40 sec. Length: 5.80 m (19.00 ft). Diameter: 0.31 m (1.01 ft). Propellants: Solid.

• Stage1: 1 x Mu-4S-1. Gross Mass: 26,600 kg (58,600 lb). Empty Mass: 5,907 kg (13,022 lb). Motor: 1 x M-10. Thrust (vac): 737.000 kN (165,684 lbf). Burn time: 61 sec. Length: 13.00 m (42.00 ft). Diameter: 1.41 m (4.62 ft). Propellants: Solid.

• Stage2: 1 x M-20. Gross Mass: 9,900 kg (21,800 lb). Empty Mass: 2,779 kg (6,126 lb). Motor: 1 x M-20. Thrust (vac): 285.000 kN (64,070 lbf). Burn time: 66 sec. Length: 4.70 m (15.40 ft). Diameter: 1.41 m (4.62 ft). Propellants: Solid.

• Stage3: 1 x Mu-3D-3. Gross Mass: 2,800 kg (6,100 lb). Empty Mass: 773 kg (1,704 lb). Motor: 1 x M-30. Thrust (vac): 128.000 kN (28,775 lbf). Burn time: 42 sec. Length: 4.00 m (13.10 ft). Diameter: 0.86 m (2.82 ft). Propellants: Solid.

• Stage4: 1 x Mu-4S-4. Gross Mass: 400 kg (880 lb). Empty Mass: 73 kg (160 lb). Motor: 1 x M-40. Thrust (vac): 26.500 kN (5,957 lbf). Burn time: 40 sec. Length: 1.80 m (5.90 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

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. Version:

Mu-3C.

Four stage vehicle consisting of 8 x SB-310 + 1 x M-10 + 1 x M-22TVC + 1 x M-3A

Launches: 4. Failures: 1. First Launch Date: 1974-02-16. Last Launch Date: 1979-02-21. 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).

• Stage0: 8 x Mu-3C-0. Gross Mass: 500 kg (1,100 lb). Empty Mass: 190 kg (410 lb). Motor: 1 x SB-310. Thrust (vac): 95.000 kN (21,356 lbf). Burn time: 7.40 sec. Length: 5.80 m (19.00 ft). Diameter: 0.31 m (1.01 ft). Propellants: Solid.

• Stage1: 1 x Mu-4S-1. Gross Mass: 26,600 kg (58,600 lb). Empty Mass: 5,907 kg (13,022 lb). Motor: 1 x M-10. Thrust (vac): 737.000 kN (165,684 lbf). Burn time: 61 sec. Length: 13.00 m (42.00 ft). Diameter: 1.41 m (4.62 ft). Propellants: Solid.

• Stage2: 1 x M-22. Gross Mass: 9,800 kg (21,600 lb). Empty Mass: 2,607 kg (5,747 lb). Motor: 1 x M-22. Thrust (vac): 285.000 kN (64,070 lbf). Burn time: 66 sec. Length: 5.00 m (16.40 ft). Diameter: 1.41 m (4.62 ft). Propellants: Solid.

• Stage3: 1 x M-3A. Gross Mass: 1,100 kg (2,400 lb). Empty Mass: 130 kg (280 lb). Motor: 1 x M-3A. Thrust (vac): 61.000 kN (13,713 lbf). Burn time: 54 sec. Length: 2.30 m (7.50 ft). Diameter: 1.14 m (3.74 ft). Propellants: Solid.

• Stage0: 8 x Mu-3C-0. Gross Mass: 500 kg (1,100 lb). Empty Mass: 190 kg (410 lb). Motor: 1 x SB-310. Thrust (vac): 95.000 kN (21,356 lbf). Burn time: 7.40 sec. Length: 5.80 m (19.00 ft). Diameter: 0.31 m (1.01 ft). Propellants: Solid.

• Stage1: 1 x Mu-4S-1. Gross Mass: 26,600 kg (58,600 lb). Empty Mass: 5,907 kg (13,022 lb). Motor: 1 x M-10. Thrust (vac): 737.000 kN (165,684 lbf). Burn time: 61 sec. Length: 13.00 m (42.00 ft). Diameter: 1.41 m (4.62 ft). Propellants: Solid.

• Stage2: 1 x M-20. Gross Mass: 9,900 kg (21,800 lb). Empty Mass: 2,779 kg (6,126 lb). Motor: 1 x M-20. Thrust (vac): 285.000 kN (64,070 lbf). Burn time: 66 sec. Length: 4.70 m (15.40 ft). Diameter: 1.41 m (4.62 ft). Propellants: Solid.

• Stage3: 1 x Mu-3D-3. Gross Mass: 2,800 kg (6,100 lb). Empty Mass: 773 kg (1,704 lb). Motor: 1 x M-30. Thrust (vac): 128.000 kN (28,775 lbf). Burn time: 42 sec. Length: 4.00 m (13.10 ft). Diameter: 0.86 m (2.82 ft). Propellants: Solid.

• Stage4: 1 x Mu-4S-4. Gross Mass: 400 kg (880 lb). Empty Mass: 73 kg (160 lb). Motor: 1 x M-40. Thrust (vac): 26.500 kN (5,957 lbf). Burn time: 40 sec. Length: 1.80 m (5.90 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage0: 8 x Mu-3C-0. Gross Mass: 500 kg (1,100 lb). Empty Mass: 190 kg (410 lb). Motor: 1 x SB-310. Thrust (vac): 95.000 kN (21,356 lbf). Burn time: 7.40 sec. Length: 5.80 m (19.00 ft). Diameter: 0.31 m (1.01 ft). Propellants: Solid.

• Stage1: 1 x Mu-3S-1. Gross Mass: 34,800 kg (76,700 lb). Empty Mass: 7,640 kg (16,840 lb). Motor: 1 x M-13. Thrust (vac): 1,262.419 kN (283,803 lbf). Isp: 263 sec. Burn time: 70 sec. Length: 14.75 m (48.39 ft). Diameter: 1.41 m (4.62 ft). Propellants: Solid.

• Stage2: 1 x M-22. Gross Mass: 9,800 kg (21,600 lb). Empty Mass: 2,607 kg (5,747 lb). Motor: 1 x M-22. Thrust (vac): 285.000 kN (64,070 lbf). Burn time: 66 sec. Length: 5.00 m (16.40 ft). Diameter: 1.41 m (4.62 ft). Propellants: Solid.

• Stage3: 1 x M-3A. Gross Mass: 1,100 kg (2,400 lb). Empty Mass: 130 kg (280 lb). Motor: 1 x M-3A. Thrust (vac): 61.000 kN (13,713 lbf). Burn time: 54 sec. Length: 2.30 m (7.50 ft). Diameter: 1.14 m (3.74 ft). Propellants: Solid.

• Stage4: 1 x KM-H. Gross Mass: 100 kg (220 lb). Empty Mass: 13 kg (28 lb). Motor: 1 x KM-H. Length: 1.40 m (4.50 ft). Diameter: 0.93 m (3.05 ft). Propellants: Solid.

• Stage0: 8 x Mu-3C-0. Gross Mass: 500 kg (1,100 lb). Empty Mass: 190 kg (410 lb). Motor: 1 x SB-310. Thrust (vac): 95.000 kN (21,356 lbf). Burn time: 7.40 sec. Length: 5.80 m (19.00 ft). Diameter: 0.31 m (1.01 ft). Propellants: Solid.

• Stage1: 1 x M-13TVC. Gross Mass: 34,200 kg (75,300 lb). Empty Mass: 6,987 kg (15,403 lb). Motor: 1 x M-13. Thrust (vac): 1,020.000 kN (229,300 lbf). Burn time: 66 sec. Length: 14.80 m (48.50 ft). Diameter: 1.41 m (4.62 ft). Propellants: Solid.

• Stage2: 1 x M-22. Gross Mass: 9,800 kg (21,600 lb). Empty Mass: 2,607 kg (5,747 lb). Motor: 1 x M-22. Thrust (vac): 285.000 kN (64,070 lbf). Burn time: 66 sec. Length: 5.00 m (16.40 ft). Diameter: 1.41 m (4.62 ft). Propellants: Solid.

• Stage3: 1 x M-3A. Gross Mass: 1,100 kg (2,400 lb). Empty Mass: 130 kg (280 lb). Motor: 1 x M-3A. Thrust (vac): 61.000 kN (13,713 lbf). Burn time: 54 sec. Length: 2.30 m (7.50 ft). Diameter: 1.14 m (3.74 ft). Propellants: Solid.

• Stage0: 2 x Mu-3S-0. Gross Mass: 5,100 kg (11,200 lb). Empty Mass: 1,080 kg (2,380 lb). Motor: 1 x SB-735. Thrust (vac): 327.830 kN (73,699 lbf). Isp: 263 sec. Burn time: 38 sec. Length: 8.25 m (27.06 ft). Diameter: 0.73 m (2.39 ft). Propellants: Solid.

• Stage1: 1 x Mu-3S-1. Gross Mass: 34,800 kg (76,700 lb). Empty Mass: 7,640 kg (16,840 lb). Motor: 1 x M-13. Thrust (vac): 1,262.419 kN (283,803 lbf). Isp: 263 sec. Burn time: 70 sec. Length: 14.75 m (48.39 ft). Diameter: 1.41 m (4.62 ft). Propellants: Solid.

• Stage2: 1 x Mu-3S-2. Gross Mass: 13,100 kg (28,800 lb). Empty Mass: 2,800 kg (6,100 lb). Motor: 1 x M-23-Mu. Thrust (vac): 523.998 kN (117,799 lbf). Isp: 285 sec. Burn time: 70 sec. Length: 6.19 m (20.30 ft). Diameter: 1.41 m (4.62 ft). Propellants: Solid.

• Stage3: 1 x M-3B. Gross Mass: 3,590 kg (7,910 lb). Empty Mass: 310 kg (680 lb). Motor: 1 x M-3B-Mu. Thrust (vac): 132.115 kN (29,701 lbf). Isp: 294 sec. Burn time: 87 sec. Length: 2.68 m (8.79 ft). Diameter: 1.50 m (4.90 ft). Propellants: Solid.

• Stage0: 8 x Mu-3C-0. Gross Mass: 500 kg (1,100 lb). Empty Mass: 190 kg (410 lb). Motor: 1 x SB-310. Thrust (vac): 95.000 kN (21,356 lbf). Burn time: 7.40 sec. Length: 5.80 m (19.00 ft). Diameter: 0.31 m (1.01 ft). Propellants: Solid.

• Stage1: 1 x Mu-4S-1. Gross Mass: 26,600 kg (58,600 lb). Empty Mass: 5,907 kg (13,022 lb). Motor: 1 x M-10. Thrust (vac): 737.000 kN (165,684 lbf). Burn time: 61 sec. Length: 13.00 m (42.00 ft). Diameter: 1.41 m (4.62 ft). Propellants: Solid.

• Stage2: 1 x M-20. Gross Mass: 9,900 kg (21,800 lb). Empty Mass: 2,779 kg (6,126 lb). Motor: 1 x M-20. Thrust (vac): 285.000 kN (64,070 lbf). Burn time: 66 sec. Length: 4.70 m (15.40 ft). Diameter: 1.41 m (4.62 ft). Propellants: Solid.

• Stage3: 1 x Mu-3D-3. Gross Mass: 2,800 kg (6,100 lb). Empty Mass: 773 kg (1,704 lb). Motor: 1 x M-30. Thrust (vac): 128.000 kN (28,775 lbf). Burn time: 42 sec. Length: 4.00 m (13.10 ft). Diameter: 0.86 m (2.82 ft). Propellants: Solid.

• Stage4: 1 x Mu-4S-4. Gross Mass: 400 kg (880 lb). Empty Mass: 73 kg (160 lb). Motor: 1 x M-40. Thrust (vac): 26.500 kN (5,957 lbf). Burn time: 40 sec. Length: 1.80 m (5.90 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage0: 8 x Mu-3C-0. Gross Mass: 500 kg (1,100 lb). Empty Mass: 190 kg (410 lb). Motor: 1 x SB-310. Thrust (vac): 95.000 kN (21,356 lbf). Burn time: 7.40 sec. Length: 5.80 m (19.00 ft). Diameter: 0.31 m (1.01 ft). Propellants: Solid.

• Stage1: 1 x Mu-4S-1. Gross Mass: 26,600 kg (58,600 lb). Empty Mass: 5,907 kg (13,022 lb). Motor: 1 x M-10. Thrust (vac): 737.000 kN (165,684 lbf). Burn time: 61 sec. Length: 13.00 m (42.00 ft). Diameter: 1.41 m (4.62 ft). Propellants: Solid.

• Stage2: 1 x .

1966 October 31 - 05:04 GMT - Kagoshima M. Mu-1 M-1-1 Test mission Agency: ISAS. Apogee: 34 km (21 mi).

1969 August 17 - Kagoshima M. Mu-3D M-3D-1 Test mission Agency: ISAS. Apogee: 160 km (90 mi).

1970 September 25 - Kagoshima M. Mu-4S M-4S-1 FAILURE: Fourth stage failed to ignite. SS Spacecraft: SS. Agency: ISAS. Apogee: 712 km (442 mi).

1971 February 16 - 04:00 GMT - Kagoshima M. Mu-4S M-4S-2 Tansei 1 Mass: 62 kg (136 lb). Spacecraft: Tansei. Agency: ISAS. Perigee: 986 km (612 mi). Apogee: 1,106 km (687 mi). Inclination: 29.70 deg. Period: 106.10 min. Engineering test for the launching of scientific satellites. Injection point 29.7 N, 145.8 E

1971 September 28 - 04:00 GMT - Kagoshima M. Mu-4S M-4S-3 SS-01 Shinsei Mass: 65 kg (143 lb). Spacecraft: SS. Agency: ISAS. Perigee: 872 km (541 mi). Apogee: 1,866 km (1,159 mi). Inclination: 32.00 deg. Period: 113.10 min. Scientific observations in outer space. Injection point 29 deg 7 min N, 145 deg 8 min E.

1972 August 19 - 02:40 GMT - Kagoshima M. Mu-4S M-4S-4 SS-02 Denpa Mass: 75 kg (165 lb). Spacecraft: SS. Agency: ISAS. Perigee: 238 km (147 mi). Apogee: 6,322 km (3,928 mi). Inclination: 31.00 deg. Period: 157.40 min. Ionospheric experiments. Scientific observations in the ionosphere and magnetosphere. Interjection point 31 deg 15' N 11 deg 05' E.

1974 February 16 - 05:00 GMT - Kagoshima M. Mu-3C M-3C-1 Tansei 2 Mass: 65 kg (143 lb). Spacecraft: Tansei. Agency: ISAS. Perigee: 284 km (176 mi). Apogee: 3,231 km (2,007 mi). Inclination: 31.20 deg. Period: 121.70 min. Attitude control satellite (performance test of launch vehicle).

1974 September 2 - 06:00 GMT - Tanegashima Q. ETV-1 Test mission Agency: NASDA. Apogee: 128 km (79 mi).

1975 February 5 - 06:00 GMT - Tanegashima Q. ETV-2 Test mission Agency: NASDA. Apogee: 167 km (103 mi).

1975 February 24 - 05:25 GMT - Kagoshima M. Mu-3C M-3C-2 SS-03 Taiyo Mass: 86 kg (189 lb). Spacecraft: SS. Agency: ISAS. Perigee: 254 km (157 mi). Apogee: 3,125 km (1,941 mi). Inclination: 31.50 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 - Kagoshima M. Mu-3C M-3C-3 FAILURE: Stage 2 thrust vector control failure. Corsa A Mass: 92 kg (202 lb). Spacecraft: Corsa A. Agency: ISAS.

1977 February 19 - 05:15 GMT - Kagoshima M. Mu-3H M-3H-1 Tansei 3 Mass: 230 kg (500 lb). Spacecraft: Tansei. Agency: ISAS. Perigee: 799 km (496 mi). Apogee: 3,802 km (2,362 mi). Inclination: 65.80 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 - Kagoshima M. Mu-3H M-3H-2 SS-05 Kyokko Mass: 103 kg (227 lb). Spacecraft: EXOS. Agency: ISAS. Perigee: 639 km (397 mi). Apogee: 3,952 km (2,455 mi). Inclination: 65.40 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 - Kagoshima M. Mu-3H M-3H-3 SS-06 Jikiken Mass: 100 kg (220 lb). Spacecraft: EXOS. Agency: ISAS. Perigee: 251 km (155 mi). Apogee: 21,192 km (13,168 mi). Inclination: 31.30 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.

1979 February 21 - 05:00 GMT - Kagoshima M. Mu-3C M-3C-4 SS-04 Hakucho Mass: 100 kg (220 lb). Spacecraft: SS. Agency: ISAS. Perigee: 543 km (337 mi). Apogee: 566 km (351 mi). Inclination: 29.80 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.

1980 February 17 - 00:40 GMT - Kagoshima M. Mu-3S M-3S-1 Tansei 4 Mass: 134 kg (295 lb). Spacecraft: Tansei. Agency: ISAS. Perigee: 517 km (321 mi). Apogee: 608 km (377 mi). Inclination: 38.70 deg. Period: 95.90 min.

1981 February 21 - 00:30 GMT - Kagoshima M. Mu-3S M-3S-2 SS-07 Hinotori Mass: 185 kg (407 lb). Spacecraft: Astro. Agency: ISAS. Perigee: 274 km (170 mi). Apogee: 279 km (173 mi). Inclination: 31.30 deg. Period: 90.10 min. 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 - Kagoshima M. Mu-3S M-3S-3 SS-08 Tenma Mass: 185 kg (407 lb). Spacecraft: Astro. Agency: ISAS. Perigee: 431 km (267 mi). Apogee: 438 km (272 mi). Inclination: 31.50 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 - Kagoshima M. Mu-3S M-3S-4 SS-09 Onzora Mass: 180 kg (390 lb). Spacecraft: EXOS. Agency: ISAS. Perigee: 247 km (153 mi). Apogee: 331 km (205 mi). Inclination: 74.60 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.

1985 January 7 - 19:26 GMT - Kagoshima M. Mu-3S-II M-3S2-1 SS-10 Sagikake Mass: 141 kg (310 lb). Spacecraft: Tansei. Agency: ISAS. 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.

1985 August 18 - 23:33 GMT - Kagoshima M. Mu-3S-II M-3S2-2 SS-11 Suisei Mass: 141 kg (310 lb). Spacecraft: SS. Agency: ISAS. 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).

1987 February 5 - 06:30 GMT - Kagoshima M. Mu-3S-II M-3S2-3 Ginga Mass: 420 kg (920 lb). Spacecraft: Astro. Agency: ISAS. Perigee: 395 km (245 mi). Apogee: 450 km (270 mi). Inclination: 31.00 deg. Period: 93.00 min. 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.

1989 February 21 - 23:30 GMT - Kagoshima M. Mu-3S-II M-3S2-4 Akebono Mass: 295 kg (650 lb). Spacecraft: EXOS. Agency: ISAS. Perigee: 272 km (169 mi). Apogee: 8,554 km (5,315 mi). Inclination: 75.10 deg. Period: 185.90 min. 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.

1990 January 24 - 11:46 GMT - Kagoshima M. Mu-3S-II M-3S2-5 Hiten Mass: 185 kg (407 lb). 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. 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.

1991 August 30 - 02:30 GMT - Kagoshima M. Mu-3S-II M-3S2-6 Solar-A Mass: 420 kg (920 lb). Spacecraft: Solar. Agency: ISAS. Perigee: 516 km (320 mi). Apogee: 754 km (468 mi). Inclination: 31.30 deg. Period: 97.40 min. X-ray imaging of Sun.

1993 February 20 - 02:20 GMT - Kagoshima M. Mu-3S-II M-3S2-7 Asuka Mass: 420 kg (920 lb). Spacecraft: Astro. Agency: ISAS. Perigee: 539 km (334 mi). Apogee: 646 km (401 mi). Inclination: 31.10 deg. Period: 96.50 min. 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'.

1995 January 15 - 13:45 GMT - Kagoshima M. Mu-3S-II M-3S2-8 FAILURE: Failure of second stage attitude control system. Express 1 Spacecraft: Express 1. Agency: ISAS. 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.