M-V
 The fifth M-V launches with the ASTRO-EII spacecraft. |
|
| Function | All-solid small orbital launch vehicle |
|---|---|
| Manufacturer | Nissan Motors (-2000) IHI AEROSPACE (-2006)[1] |
| Country of origin | Japan |
| Size | |
| Height | 30.8 m (101 ft) |
| Diameter | 2.5 m (8.2 ft) |
| Mass | 137,500 - 139,000 kg (303,100 - 306,000 lb) |
| Stages | 3 or 4 |
| Capacity | |
| Payload to LEO | 1,800 kg (3,900 lb) |
| Payload to Polar LEO |
1,300 kg (2,800 lb) |
| Launch history | |
| Status | Retired |
| Launch sites | Kagoshima |
| Total launches | 7 (M-V: 4, M-V KM: 3) |
| Successes | 6 (M-V: 3, M-V KM: 3) |
| Failures | 1 (M-V) |
| First flight | M-V: 10 February 2000 M-V KM: 12 February 1997 |
| Last flight | M-V: 22 September 2006 M-V KM: 9 May 2003 |
| Notable payloads | HALCA, Nozomi, ASTRO-E, Hayabusa Suzaku, AKARI Hinode |
| First stage - M-14 | |
| Engines | 1 Solid |
| Thrust | 3,780.345 kN (849,855 lbf) |
| Specific impulse | 246 sec |
| Burn time | 46 seconds |
| Fuel | Solid |
| Second stage - M-24 | |
| Engines | 1 Solid |
| Thrust | 1,245.287 kN (279,952 lbf) |
| Specific impulse | 203 sec |
| Burn time | 71 seconds |
| Fuel | Solid |
| Third stage - M-34 | |
| Engines | 1 Solid |
| Thrust | 294 kN (66,093 lbf) |
| Specific impulse | 301 sec |
| Burn time | 102 seconds |
| Fuel | Solid |
| Fourth stage - KM-V1 | |
| Engines | 1 Solid |
| Thrust | 51.9 kN (11,668 lbf) |
| Specific impulse | 298 sec |
| Burn time | 73 seconds |
| Fuel | Solid |
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 (ISAS) began developing the M-V in 1990 at a cost of 15 billion yen. It has three stages and is 30.7 meters high, 2.5 meters in diameter, and weighs about 140 tonnes (310,000 pounds). It was capable of launching a satellite weighing 1.8 tonnes (2 short tons) into an orbit as high as 250 km (160 mi).
The first M-V rocket launched the HALCA radio astronomy satellite in 1997, and the second the Nozomi Mars explorer in July 1998. The third rocket attempted to launch the Astro-E X-ray satellite on February 10, 2000 but failed.
ISAS recovered from this setback and launched Hayabusa to 25143 Itokawa in 2003.
The following M-V launch was the scientific Astro-E2 satellite, a replacement for Astro-E, which took place on July 10, 2005.
The final launch was that of the Hinode (SOLAR-B) spacecraft, along with the SSSat microsat and a nanosatellite, HIT-SAT, on 22 September 2006.
Contents
M-V flights
| Date (UTC) | Flight | Payload | Result |
|---|---|---|---|
| February 12, 1997 04:50:00 | M-V-1 | Muses B (HALCA) | Success |
| July 3, 1998 18:12:00 | M-V-3 | Planet B (Nozomi) | Success |
| February 10, 2000 01:30:00 | M-V-4 | ASTRO-E | Failure |
| May 9, 2003 04:29:25 | M-V-5 | Muses C (Hayabusa) | Success |
| July 10, 2005 03:30:00 | M-V-6 | ASTRO-E2 (Suzaku) | Success |
| February 21, 2006 21:28:00 | M-V-8 | ASTRO-F (Akari) CUTE-1.7-APD SSP (solar sail sub payload) |
Success SSP failed to open completely |
| September 22, 2006 21:36 | M-V-7 | Solar-B (Hinode) HIT-SAT SSSAT (solar sail) |
Success SSSat failed after launch |
Following program
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A follow on to the M-V, called the Epsilon Rocket,[2] featured a lower 1.2 tonne LEO payload capability. The development aim is to reduce costs, primarily by using the H-IIA solid rocket booster as the first stage and through shorter launch preparation time. Epsilon launches are intended to cost much less than the $70 million launch cost of a M-V.[3]
The first launch, of a small scientific satellite SPRINT-A, took place in September 2013. The initial launches will be of a two-stage version,[citation needed] of Epsilon, with up to a 500 kilogram LEO payload capability.[4]
Potential Intercontinental ballistic missile
Solid fuel rockets are the design of choice for military applications as they can remain in storage for long periods, and then reliably launch at short notice.
Lawmakers made national security arguments for keeping Japan's solid-fuel rocket technology alive after ISAS was merged into the Japan Aerospace Exploration Agency, which also has the H-IIA liquid-fuelled rocket, in 2003. The ISAS director of external affairs, Yasunori Matogawa, said, "It seems the hard-line national security proponents in parliament are increasing their influence, and they aren't getting much criticism…I think we’re moving into a very dangerous period. When you consider the current environment and the threat from North Korea, it’s scary."[5]
Toshiyuki Shikata, a Tokyo Metropolitan Government adviser and former lieutenant general, claimed that part of the rationale for the fifth M-V Hayabusa mission was that the reentry and landing of its return capsule demonstrated "that Japan's ballistic missile capability is credible."[6]
At a technical level the M-V design could be weaponised quickly (as an Intercontinental ballistic missile, since only payload and guidance have to be changed) although this would be politically unlikely.[7] The M-V is comparable in performance to the LGM-118 Peacekeeper ICBM.
Comparable solid fuel rockets
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See also
References
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External links
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