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Mu (rocket)
Encyclopedia
The Mu, also known as M, was a series of Japan
ese solid-fuelled
carrier rockets, which were launched from Uchinoura
between 1966 and 2006. Originally developed by Japan's Institute of Space and Astronautical Science
, Mu rockets were later operated by Japan Aerospace Exploration Agency
following its merger with ISAS.
made a single, sub-orbital, test flight, on 31 October 1966. Subsequently a series of rockets were produced, designated Mu-3 and Mu-4. In 1969 a suborbital test launch of the Mu-3D was conducted. The first orbital launch attempt for the Mu family, using a Mu-4S, was conducted on 25 September 1970, however the fourth stage did not ignite, and the rocket failed to reach orbit. On 16 February 1971, Tansei 1 was launched by another Mu-4S rocket. Two further Mu-4S launches took place during 1971 and 1972. The Mu-4S was replaced by the Mu-3C, was launched four times between 1974 and 1979, with three successes and one failure, and the Mu-3H, which was launched three times in 1977 and 1978. The Mu-3S was used between 1980 and 1984, making four launches. The final member of the Mu-3 family was the Mu-3SII, which was launched eight times between 1985 and 1995. The Mu-3 was replaced in service by the M-V.
, or Mu-5, was introduced in 1997 and retired in 2006. Seven launches, six of which were successful, were conducted. Typically, the M-V flew in a three-stage configuration, however a four-stage configuration, designated M-V KM was used 3 times, with the MUSES-B
(HALCA) satellite in 1997, Nozomi (PLANET-B) spacecraft in 1998, and the Hayabusa
(MUSES-C) spacecraft in 2003. The three-stage configuration had a maximum payload of 1800 kg (3,968.3 lb) for an orbit with altitude of 200 km (124.3 mi) and inclination of 30°, and 1300 kg (2,866 lb) to a polar orbit (90° inclination), with an altitude of 200 km (124.3 mi). The M-V KM could launch 1800 kg (3,968.3 lb) to an orbit with 30° inclination and 400 km (248.5 mi) altitude.
The three stage M-V had a total launch mass of 137500 kg (303,135.6 lb), whilst the total mass of a four-stage M-V KM was 139000 kg (306,442.5 lb).
Japan
Japan is an island nation in East Asia. Located in the Pacific Ocean, it lies to the east of the Sea of Japan, China, North Korea, South Korea and Russia, stretching from the Sea of Okhotsk in the north to the East China Sea and Taiwan in the south...
ese solid-fuelled
Solid rocket
A solid rocket or a solid-fuel rocket is a rocket engine that uses solid propellants . The earliest rockets were solid-fuel rockets powered by gunpowder; they were used by the Chinese in warfare as early as the 13th century and later by the Mongols, Arabs, and Indians.All rockets used some form of...
carrier rockets, which were launched from Uchinoura
Uchinoura Space Center
The is a space launch facility close to the Japanese town of Kimotsuki, in Kagoshima Prefecture. Before the establishment of the JAXA space agency in 2003, it was simply called the . All Japan's scientific satellites were launched from Uchinoura prior to the M-V launch vehicles being decommissioned...
between 1966 and 2006. Originally developed by Japan's Institute of Space and Astronautical Science
Institute of Space and Astronautical Science
is a Japanese national research organization of astrophysics using rockets, astronomical satellites and interplanetary probes. It is a division of Japan Aerospace Exploration Agency .- History :...
, Mu rockets were later operated by Japan Aerospace Exploration Agency
Japan Aerospace Exploration Agency
The , or JAXA, is Japan's national aerospace agency. Through the merger of three previously independent organizations, JAXA was formed on October 1, 2003, as an Independent Administrative Institution administered by the Ministry of Education, Culture, Sports, Science and Technology and the...
following its merger with ISAS.
Early Japanese carrier rockets
The first Mu rocket, the Mu-1MU-1
Mu-1 may refer to*Midwest MU-1, a glider*Mu-1 rocket, a Japanese rocket...
made a single, sub-orbital, test flight, on 31 October 1966. Subsequently a series of rockets were produced, designated Mu-3 and Mu-4. In 1969 a suborbital test launch of the Mu-3D was conducted. The first orbital launch attempt for the Mu family, using a Mu-4S, was conducted on 25 September 1970, however the fourth stage did not ignite, and the rocket failed to reach orbit. On 16 February 1971, Tansei 1 was launched by another Mu-4S rocket. Two further Mu-4S launches took place during 1971 and 1972. The Mu-4S was replaced by the Mu-3C, was launched four times between 1974 and 1979, with three successes and one failure, and the Mu-3H, which was launched three times in 1977 and 1978. The Mu-3S was used between 1980 and 1984, making four launches. The final member of the Mu-3 family was the Mu-3SII, which was launched eight times between 1985 and 1995. The Mu-3 was replaced in service by the M-V.
M-V
The M-VM-5 rocket
The M-V rocket, also called M-5 or Mu-5, was a Japanese solid-fuel rocket designed to launch scientific satellites. It was a member of the Mu family of rockets. The Institute of Space and Astronautical Science began developing the M-V in 1990 at a cost of 15 billion yen...
, or Mu-5, was introduced in 1997 and retired in 2006. Seven launches, six of which were successful, were conducted. Typically, the M-V flew in a three-stage configuration, however a four-stage configuration, designated M-V KM was used 3 times, with the MUSES-B
HALCA
The HALCA , also known for its project name VSOP , or the code name MUSES-B for the second of the Mu Space Engineering Spacecraft series, is a Japanese 8 meter diameter radio telescope satellite which was used for Very Long Baseline Interferometry...
(HALCA) satellite in 1997, Nozomi (PLANET-B) spacecraft in 1998, and the Hayabusa
Hayabusa
was an unmanned spacecraft developed by the Japan Aerospace Exploration Agency to return a sample of material from a small near-Earth asteroid named 25143 Itokawa to Earth for further analysis....
(MUSES-C) spacecraft in 2003. The three-stage configuration had a maximum payload of 1800 kg (3,968.3 lb) for an orbit with altitude of 200 km (124.3 mi) and inclination of 30°, and 1300 kg (2,866 lb) to a polar orbit (90° inclination), with an altitude of 200 km (124.3 mi). The M-V KM could launch 1800 kg (3,968.3 lb) to an orbit with 30° inclination and 400 km (248.5 mi) altitude.
The three stage M-V had a total launch mass of 137500 kg (303,135.6 lb), whilst the total mass of a four-stage M-V KM was 139000 kg (306,442.5 lb).