M-V

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 Template:Cvt high, Template:Cvt in diameter, and weighs about Template:Cvt. It was capable of launching a satellite weighing Template:Cvt into an orbit as high as Template:Cvt.

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 10 February 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 10 July 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.

Launch outcomes

{{ #invoke:Chart | bar chart | float = center | width = 420 | height = 320 | stack = 1 | group 1 = 0:0:0:1:0:0:0:0:0:0 | group 2 = 1:1:0:0:0:0:1:0:1:2 | colors = FireBrick: Limegreen | group names = Failure: Success | x legends = 1997:'98:'99:2000:'01:'02:'03:'04:'05:'06 }}

Launch history

Flight No.	Date and time, UTC	Rocket, configuration	Launch site	Payload	Payload mass	Orbit	Customer	Launch outcome
M-V-1	12 February 1997 04:50:00	M-V	Uchinoura M-V	MUSES-B (HALCA)<ref>{{#invoke:citation/CS1|citation	CitationClass=web }}</ref>				Template:Success
	Template:Zwsp
M-V-3	3 July 1998 18:12:00	M-V	Uchinoura M-V	PLANET-B (Nozomi)				Template:Success
	Template:Zwsp
M-V-4	10 February 2000 01:30:00	M-V	Uchinoura M-V	ASTRO-E				Template:Failure
	Failure of 1st stage engine nozzle caused control system breakdown and under performance.<ref>{{#invoke:citation/CS1|citation								CitationClass=web }}</ref><ref>{{#invoke:citation/CS1|citation	CitationClass=web }}</ref> Later stages could not compensate for under performance leaving payload in Template:Convert x Template:Convert orbit and subsequent reentry.<ref>{{#invoke:citation/CS1|citation	CitationClass=web }}</ref>
M-V-5	9 May 2003 04:29:25	M-V	Uchinoura M-V	MUSES-C (Hayabusa)				Template:Success
	Template:Zwsp
M-V-6	10 July 2005 03:30:00	M-V	Uchinoura M-V	ASTRO-E2 (Suzaku)				Template:Success
	Template:Zwsp
M-V-8	21 February 2006 21:28:00	M-V	Uchinoura M-V	ASTRO-F (Akari) CUTE-1.7 + APD SSP (solar sail sub payload)				Template:Success
	SSP failed to open completely
M-V-7	22 September 2006 21:36	M-V	Uchinoura M-V	SOLAR-B (Hinode) HIT-SAT SSSat (solar sail)				Template:Success
	SSSat failed after launch

File:M-V with Astro-E satellite.jpg

M-V rocket with the ASTRO-E satellite.

Following program

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A follow on to the M-V, called the Epsilon Rocket,<ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref> features 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 US$70 million launch cost of a M-V.<ref name=sfn-20100811>Template:Cite news</ref>

The first launch, of a small scientific satellite SPRINT-A (Hisaki), took place in September 2013. The initial launches will be of a two-stage version,Template:Citation needed of Epsilon, with up to a 500 kilogram LEO payload capability.<ref name=JAXA-interview>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>

Potential as an 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 JAXA, 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".<ref>Template:Cite news</ref>

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".<ref>Template:Cite news</ref>

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.<ref>Template:Cite report</ref> The M-V is comparable in performance to the LGM-118 Peacekeeper ICBM.

Comparable solid fuel rockets

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• Athena II
• Epsilon
• Minotaur IV
• Shavit
• Minotaur-C
• Vega

See also

• Comparison of orbital launchers families
• Comparison of orbital launch systems

External links

• M-V page in ISAS site of JAXA Template:Webarchive
• Epsilon Launch Vehicle at JAXA
• M-V, Encyclopedia Astronautica