View source for Engineering:H-IIB

{{Infobox rocket
|name           = H-IIB
|image          = H-ⅡBロケット8号機.jpg
|caption        = H-IIB No. F8 at the launch pad in September 2019

|function       = [[Engineering:Medium-lift launch vehicle|Medium-lift launch vehicle]]
|manufacturer   = [[Company:Mitsubishi Heavy Industries|Mitsubishi Heavy Industries]]
|country-origin = Japan
|cpl-year       = 
|cpl            = {{US$|112.5 million[http://www.gao.gov/products/GAO-17-609]}}
|height         = {{cvt|56.6|m}}
|diameter       = {{cvt|5.2|m}}
|mass           = {{cvt|531000|kg}}

|stages         = 2
|family         = H-II
|derivatives    = [[Engineering:H3 (rocket)|H3]]
| comparable    = {{flatlist|
* [[Engineering:Ariane 5#Variants|Ariane 5 ES]]
* [[Engineering:Atlas V#Capabilities|Atlas V 541]]
* [[Engineering:Falcon 9 Full Thrust|Falcon 9 Full Thrust]]
* [[Engineering:Proton-M|Proton-M]]
* GSLV Mk III
}}
|capacities     = <!--insert one of the following templates for each payload:-->
  {{Infobox rocket/payload
  |location     = [[Astronomy:Low Earth orbit|LEO]]
  |kilos        = {{cvt|19000|kg}}<ref name="SASAKIIMADA2009">{{cite journal|last1=SASAKI|first1=Hiroshi|last2=IMADA|first2=Takane|last3=TAKATA|first3=Shinichi|title=Development Plan for Future Mission from HTV System|journal=Transactions of the Japan Society for Aeronautical and Space Sciences, Space Technology Japan|volume=7|issue=ists26|year=2009|pages=Tk_77–Tk_82|issn=1347-3840|doi=10.2322/tstj.7.Tk_77|doi-access=free}}</ref>
  }}
{{Infobox rocket/payload
  |location     = ISS (carrying the HTV)
  |kilos        = {{cvt|16500|kg}}<ref>{{cite web|title=About H-IIB Launch Vehicle|url=https://global.jaxa.jp/projects/rockets/h2b/index.html|website=Japan Aerospace Exploration Agency|publisher=JAXA |access-date=18 September 2019}}</ref>
  }}
  {{Infobox rocket/payload
  |location     = [[Astronomy:Geostationary transfer orbit|GTO]]
  |kilos        = {{cvt|8000|kg}}<ref name=GSP-H2B>{{cite web|url= http://space.skyrocket.de/doc_lau/h-2b.htm|title=H-2B|first=Gunter|last=Krebs|work=Gunter's Space Page|access-date=28 January 2017}}</ref>
  }}

|status         = Retired
|sites          = Tanegashima, LC-Y2
|first          = 10 September 2009
|last           = 20 May 2020
|launches       = 9
|success        = 9
|payloads       = [[Engineering:H-II Transfer Vehicle|H-II Transfer Vehicle]]

|stagedata = {{Infobox rocket/stage
  |type         = booster
  |name         = [[Engineering:SRB-A|SRB-A3]]
  |number       = 4
  |length       = {{cvt|15|m}}
  |diameter     = {{cvt|2.5|m}}
  |empty        = <!--empty mass of a single booster/stage in kilograms, use {{cvt|EMPTYMASS|kg}}, optional-->
  |gross        = {{cvt|76,500|kg}} each
  |propmass     = {{cvt|66,000|kg}} each 
  |solid        = yes
  |thrust       = {{cvt|2305|kN}}
  |total        = {{cvt|9220|kN}}
  |SI           = {{cvt|283.6|isp}} (Vacuum)
  |burntime     = 114 seconds
  |fuel         = HTPB
  }}
  {{Infobox rocket/stage
  |type         = stage
  |diff         = 
  |stageno      = First
  |name         = 
  |number       = 
  |length       = {{cvt|38|m}}
  |diameter     = {{cvt|5.2|m}}
  |empty        = <!--empty mass of a single stage in kg, optional, use {{cvt}}-->
  |gross        = {{cvt|202000|kg}}
  |propmass     = {{cvt|177800|kg}}
  |engines      = 2 LE-7A
  |thrust       = {{cvt|2196|kN}} (vacuum)
  |total        = 
  |SI           = {{convert|440|isp}} (vacuum)
  |burntime     = 352 seconds
  |fuel         = LH<sub>2</sub> / [[Astronomy:LOX|LOX]]
  }}
  {{Infobox rocket/stage
  |type       = stage
  |diff       = 
  |stageno    = Second
  |name       = 
  |number     = 
  |length     = {{cvt|11|m}}
  |diameter   = {{cvt|4.0|m}}
  |empty      = <!--empty mass of a single booster/stage in kilograms, optional, use {{convert}}-->
  |gross      = {{cvt|20000|kg}}
  |propmass   = {{cvt|16600|kg}}
  |engines    = 1 LE-5B
  |thrust     = {{cvt|137|kN}} (vacuum)
  |total      = 
  |SI         = {{cvt|448|isp}} (vacuum)
  |burntime   = 499 seconds
  |fuel       = LH<sub>2</sub> / [[Astronomy:LOX|LOX]]
  }}
}}

'''H-IIB''' ('''H2B''') was an [[Engineering:Expendable launch system|expendable space launch system]] jointly developed by the Japanese government's space agency [[Organization:JAXA|JAXA]] and [[Company:Mitsubishi Heavy Industries|Mitsubishi Heavy Industries]]. It was used to launch the [[Engineering:H-II Transfer Vehicle|H-II Transfer Vehicle]] (HTV, or ''Kōnotori'') cargo spacecraft for the [[Astronomy:International Space Station|International Space Station]]. The H-IIB was a liquid-fueled rocket, with solid-fuel [[Engineering:Modular rocket|strap-on]] boosters and was launched from the Tanegashima Space Center in southern Japan. H-IIB made its first flight in 2009, and had made a total of nine flights through 2020 with no failures.

H-IIB was able to carry a payload of up to {{cvt|8000|kg}} to [[Astronomy:Geostationary transfer orbit|Geostationary transfer orbit]] (GTO),<ref name=GSP-H2B/> compared with the payload of 4000-6000 kg for the [[Engineering:H-IIA|H-IIA]], a predecessor design. Its performance to [[Astronomy:Low Earth orbit|low Earth orbit]] (LEO) was sufficient for the {{cvt|16500|kg}} [[Engineering:H-II Transfer Vehicle|H-II Transfer Vehicle]] (HTV).<ref name=GSP-H2B/> The first H-IIB was launched in September 2009 and the last H-IIB was launched in May 2020.<ref name=GSP-H2B/>

== Development ==
[[File:H-II series.png|thumb|left|270px|H-II series]]

The H-IIB was a space launch vehicle jointly designed, manufactured and operated by [[Organization:JAXA|JAXA]] and [[Company:Mitsubishi Heavy Industries|Mitsubishi Heavy Industries]] to launch the [[Engineering:H-II Transfer Vehicle|H-II Transfer Vehicle]]. The system was designed to adopt methods and components that have already been verified by flights on the [[Engineering:H-IIA|H-IIA]], so that manufacturing the new launch vehicle would be more cost-effective, with less risk, in a shorter period of time. JAXA was in charge of preliminary design, readiness of the ground facility, and the development of new technologies for the H-IIB, in which the private sector has limited competencies, while the Mitsubishi Heavy Industries was responsible for manufacturing. JAXA successfully conducted eight firing tests of the new cluster design with the simulated first-stage propulsion system, called Battleship Firing Tests, since March 2008, at MHI's Tashiro Test Facility in Ōdate, Akita Prefecture.<ref>{{cite web|url=http://www.jaxa.jp/article/special/transportation/nakamura01_e.html|title=A new stage in Japanese space transportation |date=2007-07-15|publisher=JAXA|work=Tomihisa Nakamura|access-date=2009-09-10}}</ref>

Before launch, two Captive Firing Tests were conducted on the H-IIB. The first test, which consisted of firing the first stage for ten seconds, was originally scheduled to occur at 02:30 [[Physics:Coordinated Universal Time|UTC]] on 27 March 2009, however it was cancelled after the launch pad's coolant system failed to activate.<ref>{{cite web|url=http://www.jaxa.jp/press/2009/03/20090327_cft_e.html|title=Postponement of the First Captive Firing Test (CFT) of the First Stage Flight Model Tank for the H-IIB Launch Vehicle|publisher=JAXA|access-date=2009-08-12|date=2009-03-27}}</ref> This was later discovered to have been due to a manual supply valve not being open.<ref>{{cite web|url=http://www.jaxa.jp/press/2009/03/20090330_cft_e.html|title=The First Captive Firing Test for the First Stage Flight Model Tank for the H-IIB Launch Vehicle |date=2009-03-30|publisher=JAXA|access-date=2009-08-12}}</ref> The test was rescheduled for 1 April 2009, but then postponed again due to a leak in a pipe associated with the launch facility's fire suppression system.<ref>{{cite web|url=http://www.jaxa.jp/press/2009/04/20090401_cft_e.html|title=Suspension of the First Captive Firing Test (CFT) of the First Stage Flight Model Tank for the H-IIB Launch Vehicle |date=2009-04-01|publisher=JAXA|access-date=2009-08-12}}</ref> The test was rescheduled for 2 April 2009,<ref>{{cite web|url=http://www.jaxa.jp/press/2009/04/20090401_cft2_e.html|title=The First Captive Firing Test for the First Stage Flight Model Tank for the H-IIB Launch Vehicle|publisher=JAXA|date=2009-04-01|access-date=2009-08-12}}</ref> when it was successfully conducted at 05:00 UTC.<ref>{{cite web|url=http://www.jaxa.jp/press/2009/04/20090402_cft_e.html|title=Result of the First Captive Firing Test for the First Stage Flight Model Tank of the H-IIB Launch Vehicle|date=2009-04-02|publisher=JAXA|access-date=2009-08-12|archive-date=14 September 2009|archive-url=https://web.archive.org/web/20090914082629/http://www.jaxa.jp/press/2009/04/20090402_cft_e.html|url-status=dead}}</ref> Following this, the second test, which involved a 150-second burn of the first stage, was scheduled for 20 April.<ref>{{cite web|url=http://www.jaxa.jp/press/2009/04/20090417_cft_e.html |title=The Second Captive Firing Test for the First Stage Flight Model Tank for the H-IIB Launch Vehicle|date=2009-04-17|publisher=JAXA|access-date=2009-08-12}}</ref> This was successfully conducted at 04:00 UTC on 22 April 2009,<ref>{{cite web|url=http://www.jaxa.jp/press/2009/04/20090422_cft_e.html|title=Result of the Second Captive Firing Test for the First Stage Flight Model Tank of the H-IIB Launch Vehicle|date=2009-04-22|publisher=JAXA|access-date=2009-08-12|archive-date=25 April 2009|archive-url=https://web.archive.org/web/20090425043723/http://www.jaxa.jp/press/2009/04/20090422_cft_e.html|url-status=dead}}</ref> following a two-day delay due to unfavorable weather conditions.<ref>{{cite web|url=http://www.jaxa.jp/press/2009/04/20090419_cft_e.html |title=Postponement of the Second Captive Firing Test (CFT) of the First Stage Flight Model Tank for the H-IIB Launch Vehicle|date=2009-04-19|publisher=JAXA|access-date=2009-08-12}}</ref> A ground test, using a [[Engineering:Battleship (rocketry)|battleship]] mockup of the rocket was subsequently conducted on 11 July 2009.<ref>{{cite web|url=http://www.jaxa.jp/press/2009/07/20090711_gtv_e.html|title=Results of the H-IIB Launch Vehicle Ground Test Vehicle (GTV) Test|publisher=JAXA|date=2009-07-11|access-date=2009-08-12|archive-date=15 July 2009|archive-url=https://web.archive.org/web/20090715013021/http://www.jaxa.jp/press/2009/07/20090711_gtv_e.html|url-status=dead}}</ref>

By 2009, the development program of the H-IIB had cost approximately 27 billion yen.<ref>[http://robot.watch.impress.co.jp/docs/news/20090710_301383.html JAXA、H-IIBロケットの地上総合試験(GTV)について説明], Robot Watch, 2009-7-10</ref>

== Vehicle description ==
The H-IIB launch vehicle was a two-stage rocket. The first stage used [[Physics:Liquid oxygen|liquid oxygen]] and [[Chemistry:Liquid hydrogen|liquid hydrogen]] as propellants and had four strap-on solid rocket boosters ([[Engineering:SRB-A|SRB-A3]]) powered by [[Chemistry:Polybutadiene|polybutadiene]]. The first stage was powered by two LE-7A engines, instead of one for the [[Engineering:H-IIA|H-IIA]]. It had four SRB-As attached to the body, while the standard version of H-IIA had two SRB-As. In addition, the first-stage body of the H-IIB was 5.2 m in diameter compared with 4 m for the H-IIA. The total length of the first stage was extended by 1 m from that of H-IIA. As a result, the H-IIB first stage held 70% more propellant than that of the H-IIA. The second stage was powered by a single LE-5B engine, which was also propelled by a hydrogen/oxygen fuel and oxidizer.<ref>{{cite web |url=http://www.jaxa.jp/pr/brochure/pdf/01/rocket05.pdf|title=H-IIB|date=2009-07-15|publisher=Japanese Aerospace Exploration Agency|work=H-IIB Launch Vehicle|access-date=2009-09-04|archive-url=https://web.archive.org/web/20140326132047/http://www.jaxa.jp/pr/brochure/pdf/01/rocket05.pdf|archive-date=2014-03-26}}</ref>

== Launch history ==
{{main|Engineering:List of H-II and H3 launches}}

The first launch of the H-IIB occurred on 10 September 2009 at 17:01:46 UTC. It successfully launched the [[Engineering:HTV-1|HTV-1]], which was on a mission to resupply the [[Astronomy:International Space Station|International Space Station (ISS)]].<ref>{{cite web|url=http://news.bbc.co.uk/2/hi/science/nature/8249357.stm|title=Japan's space freighter in orbit |date=2009-08-10|publisher=BBC|work=Jonathan Amos|access-date=2009-09-10}}</ref>

{| class="wikitable"
|+H-IIB flights from Tanegashima LC-Y2.
|-
! Flight No.
! Date of Launch ([[UTC]])
! Result
! Payload
!Remarks
! Remarks

|-
| TF1
| 10 September 2009<br />17:01:46
| {{Success}}
| {{flagicon|Japan}} [[Engineering:HTV-1|HTV-1]]
|First flight of H-IIB
| [[File:H-IIB_TF1_launching_HTV_Demo_(cropped).jpg|center|frameless|120x120px]]

|-
| F2
| 22 January 2011<br />05:37:57
| {{Success}}
| {{flagicon|Japan}} [[Engineering:Kounotori 2|HTV-2]]
|
|[[File:H-IIB_F2_launching_HTV2.jpg|center|frameless|120x120px]]

|-
| F3
| 21 July 2012<br />02:06:18
| {{Success}}
| {{flagicon|Japan}} [[Engineering:Kounotori 3|HTV-3]]<br />{{flagicon|JPN}} [[Engineering:RAIKO (satellite)|Raiko]]{{smallsup|*1}}<br />{{flagicon|JPN}} [[Engineering:We-Wish|We Wish]]{{smallsup|*1}}<br />{{flagicon|JPN}} [[Engineering:Niwaka|Niwaka]]{{smallsup|*1}}<br />{{nowrap|{{flagicon|USA}} [[Engineering:TechEdSat|TechEdSat]]}}{{smallsup|*1}}<br />{{flagicon|VIE}} [[Engineering:F-1 (satellite)|F-1]]{{smallsup|*1}}
|{{smallsup|*1}}[[Engineering:CubeSat|CubeSat]]s carried aboard HTV, on 4 October 2012 deployed from the ISS
| [[File:H-IIB_F3_launching_HTV3.jpg|center|frameless|120x120px]]

|-
| F4
| 3 August 2013<br />19:48:46
| {{Success}}
| {{flagicon|Japan}} [[Engineering:Kounotori 4|HTV-4]]<br />{{flagicon|JPN}} {{flagicon|VIE}} [[Engineering:PicoDragon|Pico Dragon]]{{smallsup|*2}}<br />{{flagicon|USA}} ArduSat-1{{smallsup|*2}}<br />{{flagicon|USA}} ArduSat-X{{smallsup|*2}}<br />{{nowrap|{{flagicon|USA}} TechEdSat-3p}}{{smallsup|*2}}
|{{smallsup|*2}}[[Engineering:CubeSat|CubeSat]]s carried aboard HTV for deployment from the ISS
| [[File:H-IIB_F4_launching_HTV4.jpg|center|frameless|120x120px]]

|-
| F5
| 19 August 2015<br />11:50:49
| {{Success}}
| {{flagicon|Japan}} [[Engineering:Kounotori 5|HTV-5]]<br>{{flagicon|Brazil}} SERPENS{{smallsup|*3}}<br>{{flagicon|Japan}} S-CUBE{{smallsup|*3}}<br />{{flagicon|USA}} Flock-2b x 14{{smallsup|*3}}<br>{{flagicon|Denmark}} GOMX-3{{smallsup|*3}}<br>{{flagicon|Denmark}} AAUSAT5{{smallsup|*3}}
|{{smallsup|*3}}[[Engineering:CubeSat|CubeSat]]s carried aboard HTV for deployment from the ISS
| [[File:H-2BF5.jpg|center|frameless|213x213px]]

|-
| F6
| 9 December 2016<br />13:26:47
| {{Success}}
| {{flagicon|Japan}} [[Engineering:Kounotori 6|HTV-6]]<br>{{flagicon|Japan}} AOBA-Velox III{{smallsup|*4}}<br>{{flagicon|Italy}} {{flagicon|Brazil}} {{flagicon|USA}} TuPOD{{smallsup|*4}}<br>{{flagicon|Japan}} EGG{{smallsup|*4}}<br>{{flagicon|Japan}} ITF-2{{smallsup|*4}}<br>{{flagicon|Japan}} STARS-C{{smallsup|*4}}<br>{{flagicon|Japan}} FREEDOM{{smallsup|*4}}<br>{{flagicon|Japan}} WASEDA-SAT3{{smallsup|*4}} <br />{{flagicon|USA}} OSNSAT{{smallsup|*4}} <br />{{flagicon|BRA}} [[Engineering:Tancredo-1|Tancredo-1]]{{smallsup|*4}} <br />{{flagicon|USA}} TechEdSat-5{{smallsup|*4}} <br />{{flagicon|USA}} 4 × Lemur-2{{smallsup|*4}}
|{{smallsup|*4}}[[Engineering:CubeSat|CubeSat]]s carried aboard HTV for deployment from the ISS
| [[File:H-IIB_rocket_carrying_Kounotori_6_lifts_off_from_the_Tanegashima_Space_Center.jpg|center|frameless|213x213px]]

|-
| F7
| 22 September 2018<br />17:52:27
| {{Success}}
| {{flagicon|Japan}} [[Engineering:Kounotori 7|HTV-7]]<br />{{flagicon|Japan}} SPATIUM-I{{smallsup|*5}}<br />{{flagicon|Japan}} RSP-00{{smallsup|*5}}<br />{{flagicon|Japan}} STARS-Me{{smallsup|*5}}
|{{smallsup|*5}} [[Engineering:CubeSat|CubeSat]]s carried aboard HTV for deployment from the ISS
|

|-
| F8
| 24 September 2019<br />16:05:05
| {{Success}}
| {{flagicon|Japan}} [[Engineering:Kounotori 8|HTV-8]]<br />{{flagicon|EGY}} NARSSCube-1{{smallsup|*6}}<br />{{flagicon|JPN}} [[Engineering:AQT-D|AQT-D]]{{smallsup|*6}}<br />{{flagicon|RWA}} RWASAT-1{{smallsup|*6}}
|{{smallsup|*6}} [[Engineering:CubeSat|CubeSat]]s carried aboard HTV for deployment from the ISS.<br />The first launch attempt on 10 September 2019, 21:33 UTC, was postponed due to a fire on the launch pad.
| [[File:H-ⅡBロケット8号機.jpg|center|frameless|180x180px]] 

|-
| F9
| 20 May 2020<br />17:31:00
| {{Success}}
| {{flagicon|Japan}} [[Engineering:Kounotori 9|HTV-9]]
|[[Engineering:Kounotori 9|Kounotori 9]] HTV launch to the ISS.<br />The last launch of both the carrier rocket and vehicle, awaiting new fleet of HTV-X and [[Engineering:H3 (rocket)|H3]] to launch in January 2024.
|
|}

== See also ==
* [[Engineering:Comparison of orbital launchers families|Comparison of orbital launchers families]]
* [[Astronomy:Comparison of orbital launch systems|Comparison of orbital launch systems]]

== References ==
{{Reflist}}

== External links ==
* [http://www.jaxa.jp/projects/rockets/h2b/index_e.html JAXA | H-IIB Launch Vehicle] {{Webarchive|url=https://web.archive.org/web/20140326134539/http://www.jaxa.jp/projects/rockets/h2b/index_e.html |date=26 March 2014 }}
* [https://web.archive.org/web/20090916013305/http://www.mhi.co.jp/en/technology/review/abstracte-45-4-16.html "Development Status of the H-IIB Launch Vehicle"]. Mitsubishi Heavy Industries Technical Review Volume 45 Number 4
* [http://www.asahi.com/special/rocket/h2b-3d/ H-2B rocket 3D model]

{{Japanese launch systems}}
{{H-II Transfer Vehicles}}
{{Expendable launch systems}}

[[Category:Expendable space launch systems]]

{{Sourceattribution|H-IIB}}