View source for H-IIB

{{Short description|Expendable launch system}}
{{Other uses|H2B (disambiguation)}}

{{Use British English|date=May 2020}}
{{Use dmy dates|date=December 2024}}
{{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&nbsp;2019

|function       = [[Medium-lift launch vehicle]]
|manufacturer   = [[Mitsubishi Heavy Industries]]
|country-origin = Japan
|cpl-year       = 
|cpl            = {{US$|112.5 million}}<ref>{{Cite web |date=16 August 2017 |title=Surplus Missile Motors: Sale Price Drives Potential Effects on DOD and Commercial Launch Providers |url=https://www.gao.gov/products/gao-17-609 |access-date=2024-09-08 |website=[[Government Accountability Office]] |language=en}}</ref>
|height         = {{cvt|56.6|m}}
|diameter       = {{cvt|5.2|m}}
|mass           = {{cvt|531000|kg}}

|stages         = 2
|family         = [[H-II (rocket family)|H-II family]] 
|derivatives    = [[H3 (rocket)|H3]]
| comparable    = {{flatlist|
* [[Ariane 5#Variants|Ariane 5 ES]]
* [[Atlas V#Capabilities|Atlas V 541]]
* [[Falcon 9 Full Thrust]]
* [[Proton-M]]
}}
|capacities     = <!--insert one of the following templates for each payload:-->
  {{Infobox rocket/payload
  |location     = [[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     = [[International Space Station|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     = [[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 Space Center|Tanegashima]], [[Yoshinobu Launch Complex|LA-Y2]]
|first          = 10 September 2009
|last           = 20 May 2020
|launches       = 9
|success        = 9
|payloads       = [[H-II Transfer Vehicle]]

|stagedata = {{Infobox rocket/stage
  |type         = booster
  |name         = [[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}}
  |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}}
  |total        = 
  |SI           = {{convert|440|isp}}
  |burntime     = 352 seconds
  |fuel         = [[LH2|LH<sub>2</sub>]] / [[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}}
  |total      = 
  |SI         = {{cvt|448|isp}}
  |burntime   = 499 seconds
  |fuel       = [[LH2|LH<sub>2</sub>]] / [[LOX]]
  }}
|derived_from=[[H-II]], [[H-IIA]]}}

'''H-IIB''' ('''H2B''') was an [[Expendable launch system|expendable space launch system]] jointly developed by the Japanese government's space agency [[JAXA]] and [[Mitsubishi Heavy Industries]]. It was used to launch the [[H-II Transfer Vehicle]] (HTV, or ''Kōnotori'') cargo spacecraft for the [[International Space Station]]. The H-IIB was a liquid-fueled rocket, with solid-fuel [[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 [[Geostationary transfer orbit]] (GTO),<ref name=GSP-H2B/> compared with the payload of 4000–6000&nbsp;kg for the [[H-IIA]], a predecessor design. Its performance to [[low Earth orbit]] (LEO) was sufficient for the {{cvt|16500|kg}} [[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 [[JAXA]] and [[Mitsubishi Heavy Industries]] to launch the [[H-II Transfer Vehicle]]. The system was designed to adopt methods and components that have already been verified by flights on the [[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 [[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|archive-date=15 March 2012|archive-url=https://web.archive.org/web/20120315101157/https://www.jaxa.jp/press/2009/03/20090327_cft_e.html|url-status=dead}}</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|archive-date=15 March 2012|archive-url=https://web.archive.org/web/20120315095438/https://www.jaxa.jp/press/2009/03/20090330_cft_e.html|url-status=dead}}</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|archive-date=15 March 2012|archive-url=https://web.archive.org/web/20120315103215/https://www.jaxa.jp/press/2009/04/20090401_cft_e.html|url-status=dead}}</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|archive-date=15 March 2012|archive-url=https://web.archive.org/web/20120315100342/https://www.jaxa.jp/press/2009/04/20090401_cft2_e.html|url-status=dead}}</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|archive-date=15 March 2012|archive-url=https://web.archive.org/web/20120315094931/https://www.jaxa.jp/press/2009/04/20090417_cft_e.html|url-status=dead}}</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|archive-date=15 March 2012|archive-url=https://web.archive.org/web/20120315095228/https://www.jaxa.jp/press/2009/04/20090419_cft_e.html|url-status=dead}}</ref> A ground test, using a [[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 [[liquid oxygen]] and [[liquid hydrogen]] as propellants and had four strap-on [[solid rocket]] boosters ([[SRB-A|SRB-A3]]) powered by [[polybutadiene]]. The first stage was powered by two [[LE-7]]A engines, instead of one for the [[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|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 [[HTV-1]], which was on a mission to resupply the [[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"
|-
! Flight
! Date of Launch ([[UTC]])
! Payload
! Remarks
! Result
|-
! {{Abbr|TF1|Test Flight 1}}
| 10 September 2009<br />17:01:46
| [[HTV-1]]
| H-IIB flight test<br />HTV demonstration flight
| {{Success}}
|-
! F2
| 22 January 2011<br />05:37:57
| [[Kounotori 2]]
|
| {{Success}}
|-
! F3
| 21 July 2012<br />02:06:18
| [[Kounotori 3]]
|
| {{Success}}
|-
! F4
| 3 August 2013<br />19:48:46
| [[Kounotori 4]]
|
| {{Success}}
|-
! F5
| 19 August 2015<br />11:50:49
| [[Kounotori 5]]
|
| {{Success}}
|-
! F6
| 9 December 2016<br />13:26:47
| [[Kounotori 6]]
|
| {{Success}}
|-
! F7
| 22 September 2018<br />17:52:27
| [[Kounotori 7]]
|
| {{Success}}
|-
! F8
| 24 September 2019<br />16:05:05
| [[Kounotori 8]]
|
| {{Success}}
|-
! F9
| 20 May 2020<br />17:31:00
| [[Kounotori 9]]
| Final flight of H-IIB<br />Final flight of HTV
| {{Success}}
|}

== See also ==
{{Portal|Spaceflight}}
* [[Comparison of orbital launchers families]]
* [[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]

{{Mitsubishi Heavy Industries}}
{{Japanese launch systems}}
{{H-II Transfer Vehicles}}
{{Expendable launch systems}}

[[Category:Mitsubishi Heavy Industries space launch vehicles]]
[[Category:Vehicles introduced in 2009]]
[[Category:Expendable space launch systems]]