M-V

M-V
	The fifth M-V launches with the ASTRO-EII spacecraft.
Function	All-solid small orbital launch vehicle
Manufacturer	Nissan Motors[1] (-2000); IHI AEROSPACE (-2006)[2]
Country of origin	Japan
Size
Height	30.8 m (101 ft)
Diameter	2.5 m (8.2 ft)
Mass	137,500–139,000 kg (303,100–306,400 lb)
Stages	3 or 4
Capacity
Payload to LEO
Mass	1,800 kg (4,000 lb)
Payload to Polar LEO
Mass	1,300 kg (2,900 lb)
Launch history
Status	Retired
Launch sites	Uchinoura M-V
Total launches	7 (M-V: 4, M-V KM: 3)
Success(es)	6 (M-V: 3, M-V KM: 3)
Failure(s)	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
Motor	1 Solid
Thrust	3,780.345 kN (849,855 lbf)
Specific impulse	246 s (2.41 km/s)
Burn time	46 seconds
Fuel	Solid
Second stage – M-24
Motor	1 Solid
Thrust	1,245.287 kN (279,952 lbf)
Specific impulse	203 s (1.99 km/s)
Burn time	71 seconds
Fuel	Solid
Third stage – M-34
Motor	1 Solid
Thrust	294 kN (66,000 lbf)
Specific impulse	301 s (2.95 km/s)
Burn time	102 seconds
Fuel	Solid
Fourth stage (M-V KM) – KM-V1
Motor	1 Solid
Thrust	51.9 kN (11,700 lbf)
Specific impulse	298 s (2.92 km/s)
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 (101 ft) high, 2.5 meters (8 ft 2 in) 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.

Launch outcomes

0.5

1

1.5

2

1997

'98

'99

2000

'01

'02

'03

'04

'05

'06

Failure
Success

Launch history

Flight №	Date / time (UTC)	Rocket, Configuration	Launch site	Payload	Launch outcome
M-V-1	February 12, 1997 04:50:00	M-V	Uchinoura M-V	MUSES-B (HALCA)[3]	Success
M-V-1
M-V-3	July 3, 1998 18:12:00	M-V	Uchinoura M-V	PLANET-B (Nozomi)	Success
M-V-3
M-V-4	February 10, 2000 01:30:00	M-V	Uchinoura M-V	ASTRO-E	Failure
M-V-4
M-V-5	May 9, 2003 04:29:25	M-V	Uchinoura M-V	MUSES-C (Hayabusa)	Success
M-V-5
M-V-6	July 10, 2005 03:30:00	M-V	Uchinoura M-V	ASTRO-E2 (Suzaku)	Success
M-V-6
M-V-8	February 21, 2006 21:28:00	M-V	Uchinoura M-V	ASTRO-F (Akari) CUTE-1.7 + APD SSP (solar sail sub payload)	Success
M-V-8	SSP failed to open completely
M-V-7	September 22, 2006 21:36	M-V	Uchinoura M-V	SOLAR-B (Hinode) HIT-SAT SSSat (solar sail)	Success
M-V-7	SSSat failed after launch

M-V rocket with the ASTRO-E satellite.

Following program

A follow on to the M-V, called the Epsilon Rocket,[4] 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 $70 million launch cost of a M-V.[5]

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, of Epsilon, with up to a 500 kilogram LEO payload capability.[6]

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."[7]

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."[8]

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.[9] The M-V is comparable in performance to the LGM-118 Peacekeeper ICBM.

Comparable solid fuel rockets

References

Travis S. Taylor (2009). Introduction to Rocket Science and Engineering. CRC Press. p. 25. ISBN 978-1-4200-7529-8.
"Projects&Products". IHI AEROSPACE. Archived from the original on 2011-04-06. Retrieved 2011-03-08.
Japan Aerospace Exploration Agency | JAXA. "HALCA > Launch Vehicle". Institute of Space and Astronautical Science. Archived from the original on 2 July 2005.
"Epsilon launch vehicle". JAXA. Retrieved 2010-04-01.
"Asteroid probe, rocket get nod from Japanese panel". Spaceflight Now. 11 August 2010. Retrieved 29 October 2012.
"Interview: Yasuhiro Morita, Project Manager, Epsilon Launch Vehicle". JAXA. Retrieved 29 October 2012.
Karl Schoenberger (July 11, 2003). "Japan ponders nuclear weapons". Detroit Free Press. Archived from the original on June 25, 2004.
Chester Dawson (28 October 2011). "In Japan, Provocative Case for Staying Nuclear". Wall Street Journal. Retrieved 13 November 2011.
William E. Rapp (January 2004). "Paths Diverging? The Next Decade in the US-Japan Security Alliance" (PDF). Strategic Studies Institute, U.S. Army War College: 82. Retrieved 29 October 2012. 119. Japan has the weapons grade plutonium, technology for weaponization, and delivery means in the M-V-5 rocket, indigenous, solid fueled, 1800 kg payload capacity, to go nuclear very rapidly should it choose. This dramatic step, however, would require a complete loss of faith in the American nuclear umbrella Cite journal requires |journal= (help)

External links

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[1] Travis S. Taylor (2009). Introduction to Rocket Science and Engineering. CRC Press. p. 25. ISBN 978-1-4200-7529-8.

[IHIAERO-2] "Projects&Products". IHI AEROSPACE. Archived from the original on 2011-04-06. Retrieved 2011-03-08.

[3] Japan Aerospace Exploration Agency | JAXA. "HALCA > Launch Vehicle". Institute of Space and Astronautical Science. Archived from the original on 2 July 2005.

[4] "Epsilon launch vehicle". JAXA. Retrieved 2010-04-01.

[sfn-20100811-5] "Asteroid probe, rocket get nod from Japanese panel". Spaceflight Now. 11 August 2010. Retrieved 29 October 2012.

[JAXA-interview-6] "Interview: Yasuhiro Morita, Project Manager, Epsilon Launch Vehicle". JAXA. Retrieved 29 October 2012.

[7] Karl Schoenberger (July 11, 2003). "Japan ponders nuclear weapons". Detroit Free Press. Archived from the original on June 25, 2004.

[8] Chester Dawson (28 October 2011). "In Japan, Provocative Case for Staying Nuclear". Wall Street Journal. Retrieved 13 November 2011.

[9] William E. Rapp (January 2004). "Paths Diverging? The Next Decade in the US-Japan Security Alliance" (PDF). Strategic Studies Institute, U.S. Army War College: 82. Retrieved 29 October 2012. 119. Japan has the weapons grade plutonium, technology for weaponization, and delivery means in the M-V-5 rocket, indigenous, solid fueled, 1800 kg payload capacity, to go nuclear very rapidly should it choose. This dramatic step, however, would require a complete loss of faith in the American nuclear umbrella Cite journal requires |journal= (help)

Orbital launch systems
List of orbital launch systems Comparison of orbital launch systems
Current	Angara A5 Antares 230+ Ariane 5 Atlas V Ceres-1 Delta IV Heavy Electron Epsilon Falcon 9 Block 5 Falcon Heavy GSLV Mk II Mk III H-IIA Hyperbola-1 Jielong 1 Kuaizhou 1 1A 11^† Kaituozhe 2 LauncherOne Long March 2C 2D 2F 3A 3B/E 3C 4B 4C 5 5B 6 7 7A^† 8 11 Minotaur I IV V C OS-M1^† Pegasus XL Proton-M PSLV Qased Rocket 3^† Safir Shavit Simorgh^† Soyuz-2 2.1a / STA 2.1b / STB 2-1v Unha Vega Zenit 3SL 3SLB 3F Zhuque-1^†
In development	Amur Angara 1.2 Ariane 6 Bloostar Cyclone-4M Eris Firefly Alpha Beta H3 Hyperbola-2 Irtysh Kuaizhou 21 31 Long March 921 rocket 9 Miura 5 New Glenn New Line 1 Nuri OS-M2 OS-M4 Orbex Prime SLS Soyuz-7 SSLV Starship Terran 1 Vega C Vega E Vulcan Zero Zhuque-2
Retired	Antares 110 120 130^† 230 Ariane 1 2 3 4 ASLV Athena I II Atlas B D E/F G H I II III LV-3B SLV-3 Able Agena Centaur Black Arrow Conestoga^† Delta A B C D E G J L M N 0100 1000 2000 3000 4000 5000 II III IV Diamant Dnepr Energia Europa^† Falcon 1 Falcon 9 v1.0 v1.1 v1.2 "Full Thrust" Feng Bao 1 GSLV Mk I H-I H-II H-IIB Juno I Juno II Kaituozhe-1 Kosmos 1 2I 3 3M Lambda 4S Long March 1 1D^† 2A 2E 3 3B 4A Mu 4S 3C 3H 3S 3SII V N1^† N-I N-II Naro-1 Paektusan Pilot-2^† R-7 Luna Molniya M L Polyot Soyuz original FG L M U U2 Soyuz/Vostok Sputnik Voskhod Vostok L K 2 2M R-29 Shtil' Volna^† Saturn I IB V Scout SLV Space Shuttle SPARK^† Sparta SS-520 Start-1 Thor Able Ablestar Agena Burner Delta DSV-2U Thorad-Agena Titan II GLV IIIA IIIB IIIC IIID IIIE 34D 23G CT-3 IV Tsyklon original 2 3 Universal Rocket UR-500 Proton Proton-K Rokot Strela Vanguard VLS-1^† Zenit 2 2M
Classes	Sounding rocket Small-lift launch vehicle Medium-lift launch vehicle Heavy-lift launch vehicle Super heavy-lift launch vehicle
This Template lists historical, current, and future space rockets that at least once attempted (but not necessarily succeeded in) an orbital launch or that are planned to attempt such a launch in the future Symbol ^† indicates historical or current rockets that attempted orbital launches but did not ever succeed (never did or has performed a successful orbital launch)

M-V