M-V

M-V

File:M-V launching ASTRO-E2.jpeg The fifth M-V launches with the ASTRO-EII spacecraft.
Function	All-solid small orbital launch vehicle
	Nissan Motors (-2000) IHI AEROSPACE (-2006)
	Japan
Size
	30.8 m (101 ft)
	2.5 m (8 ft 2 in)
	137,500–139,000 kg (303,100–306,400 lb)
Stages	3 or 4
Capacity
Payload to low Earth orbit
	1,800 kg (4,000 lb)
Payload to polar LEO
	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	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
	HALCA, Nozomi, ASTRO-E, Hayabusa Suzaku, AKARI Hinode
First stage – M-14
	1 solid
	3,780.345 kN (849,855 lbf)
Specific impulse	246 s (2.41 km/s)
Burn time	46 seconds
Propellant	Solid
Second stage – M-24
	1 solid
	1,245.287 kN (279,952 lbf)
Specific impulse	203 s (1.99 km/s)
Burn time	71 seconds
Propellant	Solid
Third stage – M-34
	1 solid
	294 kN (66,000 lbf)
Specific impulse	301 s (2.95 km/s)
Burn time	102 seconds
Propellant	Solid
Fourth stage (M-V KM) – KM-V1
	1 solid
	51.9 kN (11,700 lbf)
Specific impulse	298 s (2.92 km/s)
Burn time	73 seconds
Propellant	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 m (101 ft) high, 2.5 m (8 ft 2 in) in diameter, and weighs about 140,000 kg (310,000 lb). It was capable of launching a satellite weighing 1,800 kg (4,000 lb) 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 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

0.5

1

1.5

2

1997

'98

'99

2000

'01

'02

'03

'04

'05

'06

•   Failure
•   Success

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)				Success
	​
M-V-3	3 July 1998 18:12:00	M-V	Uchinoura M-V	PLANET-B (Nozomi)				Success
	​
M-V-4	10 February 2000 01:30:00	M-V	Uchinoura M-V	ASTRO-E				Failure
	Failure of 1st stage engine nozzle caused control system breakdown and under performance. Later stages could not compensate for under performance leaving payload in 250 miles (400 km) x 50 miles (80 km) orbit and subsequent reentry.
M-V-5	9 May 2003 04:29:25	M-V	Uchinoura M-V	MUSES-C (Hayabusa)				Success
	​
M-V-6	10 July 2005 03:30:00	M-V	Uchinoura M-V	ASTRO-E2 (Suzaku)				Success
	​
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)				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)				Success
	SSSat failed after launch

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

M-V rocket with the ASTRO-E satellite.

Following program

Main article: Epsilon (rocket)

A follow on to the M-V, called the Epsilon Rocket, 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.

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.

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".

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".

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

Comparable solid fuel rockets

Main article: Comparison of solid-fuelled orbital launch systems

• 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 Archived 21 March 2007 at the Wayback Machine
• Epsilon Launch Vehicle at JAXA
• M-V, Encyclopedia Astronautica