M-V
{{Short description|Japanese solid-fuel rocket designed to launch scientific satellites}}
{{Use American English|date=September 2021}}
{{Use dmy dates|date=September 2021}}
{{Infobox rocket
| name = M-V
| image = M-V launching ASTRO-E2.jpeg
| caption = The fifth M-V launches with the ASTRO-EII spacecraft.
| function = All-solid small orbital launch vehicle
| manufacturer = Nissan Motors{{cite book|author=Travis S. Taylor|title=Introduction to Rocket Science and Engineering|url=https://books.google.com/books?id=dQHMBQAAQBAJ&pg=PA25|year=2009 |publisher=CRC Press|isbn=978-1-4200-7529-8|page=25}} (-2000)
IHI AEROSPACE (-2006){{cite web|url=http://www.ihi.co.jp/ia/en/product/rocket.html |title=Projects&Products|publisher=IHI AEROSPACE|access-date=2011-03-08|url-status=dead|archive-url=https://web.archive.org/web/20110406035626/http://www.ihi.co.jp/ia/en/product/rocket.html|archive-date=2011-04-06}}
| country-origin = Japan
| height = {{cvt|30.8|m}}
| diameter = {{cvt|2.5|m}}
| mass = {{cvt|137500|-|139000|kg}}
| stages = 3 or 4
| capacities =
{{Infobox rocket/payload
| location = low Earth orbit
| kilos = {{cvt|1800|kg}}
}}
{{Infobox rocket/payload
| kilos = {{cvt|1300|kg}}
}}
| payloads = HALCA, Nozomi,
ASTRO-E, Hayabusa
Suzaku, AKARI
Hinode
| status = Retired
| sites = Uchinoura M-V
| first = M-V: 10 February 2000
M-V KM: 12 February 1997
| last = M-V: 22 September 2006
M-V KM: 9 May 2003
| launches = 7 (M-V: 4, M-V KM: 3)
| success = 6 (M-V: 3, M-V KM: 3)
| fail = 1 (M-V)
| stagedata =
{{Infobox rocket/stage
| type = stage
| stageno = First
| name = M-14
| engines = 1 solid
| solid = yes
| thrust = {{cvt|3780.345|kN}}
| SI = {{cvt|246|isp}}
| burntime = 46 seconds
| fuel = Solid
}}
{{Infobox rocket/stage
| type = stage
| stageno = Second
| name = M-24
| engines = 1 solid
| solid = yes
| thrust = {{cvt|1245.287|kN}}
| SI = {{cvt|203|isp}}
| burntime = 71 seconds
| fuel = Solid
}}
{{Infobox rocket/stage
| type = stage
| stageno = Third
| name = M-34
| engines = 1 solid
| solid = yes
| thrust = {{cvt|294|kN}}
| SI = {{cvt|301|isp}}
| burntime = 102 seconds
| fuel = Solid
}}
{{Infobox rocket/stage
| type = stage
| diff = M-V KM
| stageno = Fourth
| name = KM-V1
| engines = 1 solid
| solid = yes
| thrust = {{cvt|51.9|kN}}
| SI = {{cvt|298|isp}}
| burntime = 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 {{cvt|30.7|m}} high, {{cvt|2.5|m}} in diameter, and weighs about {{cvt|140000|kg}}. It was capable of launching a satellite weighing {{cvt|1800|kg}} into an orbit as high as {{cvt|250|km}}.
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
| class="wikitable plainrowheaders" |
| scope="col" | Flight No.
! scope="col" | Date and time, UTC ! scope="col" | Rocket, ! scope="col" | Launch site ! scope="col" | Payload ! scope="col" | Payload ! scope="col" | Orbit ! scope="col" | Customer ! scope="col" | Launch |
|---|
| scope="row" rowspan=2 style="text-align:center;" | M-V-1
| 12 February 1997 | M-V | Uchinoura M-V | MUSES-B (HALCA){{Cite web|url=http://www.isas.ac.jp/e/enterp/missions/halca/rocket.shtml|title=HALCA > Launch Vehicle|last=Japan Aerospace Exploration Agency {{!}} JAXA|publisher=Institute of Space and Astronautical Science|url-status=live|archive-url=https://web.archive.org/web/20050702014842/http://www.isas.ac.jp/e/enterp/missions/halca/rocket.shtml|archive-date=2 July 2005}} | | | | {{Success}} |
| colspan="8" | {{zwsp}} |
| scope="row" rowspan=2 style="text-align:center;" | M-V-3
| 3 July 1998 | M-V | Uchinoura M-V | PLANET-B (Nozomi) | | | | {{Success}} |
| colspan="8" | {{zwsp}} |
| scope="row" rowspan=2 style="text-align:center;" | M-V-4
| 10 February 2000 | M-V | Uchinoura M-V | ASTRO-E | | | | {{Failure}} |
| colspan="8" | Failure of 1st stage engine nozzle caused control system breakdown and under performance.{{Cite web |title=History ｜ ISAS |url=https://www.isas.jaxa.jp/en/about/history/ |access-date=2024-01-02 |website=History |language=en}}{{Cite web |title=1 How did M-V-4 fly? |url=https://www.isas.jaxa.jp/docs/sat/astro-e/how.html |access-date=2024-01-02 |website=www.isas.jaxa.jp}} Later stages could not compensate for under performance leaving payload in {{Convert|250|mi|km}} x {{Convert|50|mi|km}} orbit and subsequent reentry.{{Cite web |last=Ray |first=Justin |date=February 10, 2000 |title=Spaceflight Now {{!}} Breaking News {{!}} Astro-E believed lost following botched launch |url=https://spaceflightnow.com/m5/astroe/000210failure.html |access-date=2024-01-02 |website=spaceflightnow.com}} |
| scope="row" rowspan=2 style="text-align:center;" | M-V-5
| 9 May 2003 | M-V | Uchinoura M-V | MUSES-C (Hayabusa) | | | | {{Success}} |
| colspan="8" | {{zwsp}} |
| scope="row" rowspan=2 style="text-align:center;" | M-V-6
| 10 July 2005 | M-V | Uchinoura M-V | ASTRO-E2 (Suzaku) | | | | {{Success}} |
| colspan="8" | {{zwsp}} |
| scope="row" rowspan=2 style="text-align:center;" | M-V-8
| 21 February 2006 | M-V | Uchinoura M-V | ASTRO-F (Akari) | | | | {{Success}} |
| colspan="8" | SSP failed to open completely |
| scope="row" rowspan=2 style="text-align:center;" | M-V-7
| 22 September 2006 | M-V | Uchinoura M-V | SOLAR-B (Hinode) | | | | {{Success}} |
| colspan="8" | SSSat failed after launch |
File:M-V with Astro-E satellite.jpg satellite.]]
Following program
{{Main|Epsilon (rocket)}}
A follow on to the M-V, called the Epsilon Rocket,{{cite web|url=http://www.jaxa.jp/projects/rockets/epsilon/index_e.html|title=Epsilon launch vehicle|access-date=2010-04-01|publisher=JAXA|archive-date=21 January 2013|archive-url=https://web.archive.org/web/20130121050940/http://www.jaxa.jp/projects/rockets/epsilon/index_e.html|url-status=dead}} 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.{{cite news|url=http://www.spaceflightnow.com/news/n1008/11japan/|title=Asteroid probe, rocket get nod from Japanese panel|publisher=Spaceflight Now|date=11 August 2010|access-date=29 October 2012}}
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,{{citation needed|date=September 2013}} of Epsilon, with up to a 500 kilogram LEO payload capability.{{cite web|url=http://www.jaxa.jp/article/interview/vol58/index_e.html|title=Interview: Yasuhiro Morita, Project Manager, Epsilon Launch Vehicle|publisher=JAXA|access-date=29 October 2012|archive-date=23 November 2012|archive-url=https://web.archive.org/web/20121123052200/http://www.jaxa.jp/article/interview/vol58/index_e.html|url-status=dead}}
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".{{cite news |url=http://www.freep.com/news/nw/djapan11_20030711.htm|title=Japan ponders nuclear weapons|author=Karl Schoenberger|newspaper=Detroit Free Press|date=July 11, 2003|archive-url=https://web.archive.org/web/20040625104149/http://www.freep.com/news/nw/djapan11_20030711.htm|archive-date=June 25, 2004}}
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".{{cite news|url=https://www.wsj.com/articles/SB10001424052970203658804576638392537430156|title=In Japan, Provocative Case for Staying Nuclear|author=Chester Dawson|newspaper=Wall Street Journal|date=28 October 2011|access-date=13 November 2011}}
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.{{cite report|url=http://www.strategicstudiesinstitute.army.mil/pdffiles/PUB367.pdf#page=88|title=Paths Diverging? The Next Decade in the US-Japan Security Alliance|page=82|author=William E. Rapp|publisher=Strategic Studies Institute, U.S. Army War College|date=January 2004|access-date=29 October 2012|quote=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|archive-date=25 June 2006|archive-url=https://web.archive.org/web/20060625024741/http://www.strategicstudiesinstitute.army.mil/pdffiles/PUB367.pdf#page=88|url-status=dead}} The M-V is comparable in performance to the LGM-118 Peacekeeper ICBM.
Comparable solid fuel rockets
{{Main|Comparison of solid-fuelled orbital launch systems}}
See also
{{Portal|Spaceflight}}
References
{{Reflist|30em}}
External links
{{Commons|M-V (rocket)}}
- [https://web.archive.org/web/20050709085839/http://www.isas.jaxa.jp/e/enterp/rockets/vehicles/m-v/index.shtml M-V page] in [http://www.isas.jaxa.jp/e/index.shtml ISAS site] of [http://www.jaxa.jp/index_e.html JAXA] {{Webarchive|url=https://web.archive.org/web/20070321160909/http://www.jaxa.jp/index_e.html |date=21 March 2007 }}
- [https://web.archive.org/web/20100104024255/http://www.jaxa.jp/projects/rockets/solid/index_e.html Epsilon Launch Vehicle at JAXA]
- [https://web.archive.org/web/20051122111020/http://www.astronautix.com/lvs/mv.htm M-V], Encyclopedia Astronautica
{{Expendable launch systems}}
{{Japanese launch systems}}