Engineering:H-IIB

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H-IIB
H-ⅡBロケット8号機.jpg
H-IIB No. F8 at the launch pad in September 2019
FunctionMedium-lift launch vehicle
ManufacturerMitsubishi Heavy Industries
Country of originJapan
Cost per launchUS$112.5 million[1]
Size
Height56.6 m (186 ft)
Diameter5.2 m (17 ft)
Mass531,000 kg (1,171,000 lb)
Stages2
Capacity
Payload to LEO19,000 kg (42,000 lb)[1]
Payload to ISS (carrying the HTV)16,500 kg (36,400 lb)[2]
Payload to GTO8,000 kg (18,000 lb)[3]
Associated rockets
FamilyH-II
DerivativesH3
Comparable
Launch history
StatusRetired
Launch sitesTanegashima, LC-Y2
Total launches9
Successes9
First flight10 September 2009
Last flight20 May 2020
Notable payloadsH-II Transfer Vehicle
Boosters – SRB-A3
No. boosters4
Length15 m (49 ft)
Diameter2.5 m (8 ft 2 in)
Gross mass76,500 kg (168,700 lb) each
Propellant mass66,000 kg (146,000 lb) each
Thrust2,305 kN (518,000 lbf)
Total thrust9,220 kN (2,070,000 lbf)
Specific impulse283.6 s (2.781 km/s) (Vacuum)
Burn time114 seconds
FuelHTPB
First stage
Length38 m (125 ft)
Diameter5.2 m (17 ft)
Gross mass202,000 kg (445,000 lb)
Propellant mass177,800 kg (392,000 lb)
Engines2 LE-7A
Thrust2,196 kN (494,000 lbf) (vacuum)
Specific impulse440 seconds (4.3 km/s) (vacuum)
Burn time352 seconds
FuelLH2 / LOX
Second stage
Length11 m (36 ft)
Diameter4.0 m (13.1 ft)
Gross mass20,000 kg (44,000 lb)
Propellant mass16,600 kg (36,600 lb)
Engines1 LE-5B
Thrust137 kN (31,000 lbf) (vacuum)
Specific impulse448 s (4.39 km/s) (vacuum)
Burn time499 seconds
FuelLH2 / LOX

H-IIB (H2B) was an 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 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 8,000 kg (18,000 lb) to Geostationary transfer orbit (GTO),[3] compared with the payload of 4000-6000 kg for the H-IIA, a predecessor design. Its performance to low Earth orbit (LEO) was sufficient for the 16,500 kg (36,400 lb) H-II Transfer Vehicle (HTV).[3] The first H-IIB was launched in September 2009 and the last H-IIB was launched in May 2020.[3]

Development

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.[4]

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 UTC on 27 March 2009, however it was cancelled after the launch pad's coolant system failed to activate.[5] This was later discovered to have been due to a manual supply valve not being open.[6] 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.[7] The test was rescheduled for 2 April 2009,[8] when it was successfully conducted at 05:00 UTC.[9] Following this, the second test, which involved a 150-second burn of the first stage, was scheduled for 20 April.[10] This was successfully conducted at 04:00 UTC on 22 April 2009,[11] following a two-day delay due to unfavorable weather conditions.[12] A ground test, using a battleship mockup of the rocket was subsequently conducted on 11 July 2009.[13]

By 2009, the development program of the H-IIB had cost approximately 27 billion yen.[14]

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-A3) powered by polybutadiene. The first stage was powered by two LE-7A 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.[15]

Launch history

Main page: 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 HTV-1, which was on a mission to resupply the International Space Station (ISS).[16]

H-IIB flights from Tanegashima LC-Y2.
Flight No. Date of Launch (UTC) Result Payload Remarks Remarks
TF1 10 September 2009
17:01:46 		Success Japan HTV-1 First flight of H-IIB
H-IIB TF1 launching HTV Demo (cropped).jpg
F2 22 January 2011
05:37:57 		Success Japan HTV-2
H-IIB F2 launching HTV2.jpg
F3 21 July 2012
02:06:18 		Success Japan HTV-3
Japan Raiko*1
Japan We Wish*1
Japan Niwaka*1
United States TechEdSat*1
Vietnam F-1*1 		*1CubeSats carried aboard HTV, on 4 October 2012 deployed from the ISS
H-IIB F3 launching HTV3.jpg
F4 3 August 2013
19:48:46 		Success Japan HTV-4
Japan Vietnam Pico Dragon*2
United States ArduSat-1*2
United States ArduSat-X*2
United States TechEdSat-3p*2 		*2CubeSats carried aboard HTV for deployment from the ISS
H-IIB F4 launching HTV4.jpg
F5 19 August 2015
11:50:49 		Success Japan HTV-5
Brazil SERPENS*3
Japan S-CUBE*3
United States Flock-2b x 14*3
Denmark GOMX-3*3
Denmark AAUSAT5*3 		*3CubeSats carried aboard HTV for deployment from the ISS
H-2BF5.jpg
F6 9 December 2016
13:26:47 		Success Japan HTV-6
Japan AOBA-Velox III*4
Italy Brazil United States TuPOD*4
Japan EGG*4
Japan ITF-2*4
Japan STARS-C*4
Japan FREEDOM*4
Japan WASEDA-SAT3*4
United States OSNSAT*4
Brazil Tancredo-1*4
United States TechEdSat-5*4
United States 4 × Lemur-2*4 		*4CubeSats carried aboard HTV for deployment from the ISS
H-IIB rocket carrying Kounotori 6 lifts off from the Tanegashima Space Center.jpg
F7 22 September 2018
17:52:27 		Success Japan HTV-7
Japan SPATIUM-I*5
Japan RSP-00*5
Japan STARS-Me*5 		*5 CubeSats carried aboard HTV for deployment from the ISS
F8 24 September 2019
16:05:05 		Success Japan HTV-8
Egypt NARSSCube-1*6
Japan AQT-D*6
Rwanda RWASAT-1*6 		*6 CubeSats carried aboard HTV for deployment from the ISS.
The first launch attempt on 10 September 2019, 21:33 UTC, was postponed due to a fire on the launch pad.
H-ⅡBロケット8号機.jpg
F9 20 May 2020
17:31:00 		Success Japan HTV-9 Kounotori 9 HTV launch to the ISS.
The last launch of both the carrier rocket and vehicle, awaiting new fleet of HTV-X and H3 to launch in January 2024.

See also

References

  1. ↑ SASAKI, Hiroshi; IMADA, Takane; TAKATA, Shinichi (2009). "Development Plan for Future Mission from HTV System". Transactions of the Japan Society for Aeronautical and Space Sciences, Space Technology Japan 7 (ists26): Tk_77–Tk_82. doi:10.2322/tstj.7.Tk_77. ISSN 1347-3840. 
  2. ↑ "About H-IIB Launch Vehicle". JAXA. https://global.jaxa.jp/projects/rockets/h2b/index.html. 
  3. ↑ 3.0 3.1 3.2 3.3 Krebs, Gunter. "H-2B". Gunter's Space Page. http://space.skyrocket.de/doc_lau/h-2b.htm. 
  4. ↑ "A new stage in Japanese space transportation". Tomihisa Nakamura. JAXA. 2007-07-15. http://www.jaxa.jp/article/special/transportation/nakamura01_e.html. 
  5. ↑ "Postponement of the First Captive Firing Test (CFT) of the First Stage Flight Model Tank for the H-IIB Launch Vehicle". JAXA. 2009-03-27. http://www.jaxa.jp/press/2009/03/20090327_cft_e.html. 
  6. ↑ "The First Captive Firing Test for the First Stage Flight Model Tank for the H-IIB Launch Vehicle". JAXA. 2009-03-30. http://www.jaxa.jp/press/2009/03/20090330_cft_e.html. 
  7. ↑ "Suspension of the First Captive Firing Test (CFT) of the First Stage Flight Model Tank for the H-IIB Launch Vehicle". JAXA. 2009-04-01. http://www.jaxa.jp/press/2009/04/20090401_cft_e.html. 
  8. ↑ "The First Captive Firing Test for the First Stage Flight Model Tank for the H-IIB Launch Vehicle". JAXA. 2009-04-01. http://www.jaxa.jp/press/2009/04/20090401_cft2_e.html. 
  9. ↑ "Result of the First Captive Firing Test for the First Stage Flight Model Tank of the H-IIB Launch Vehicle". JAXA. 2009-04-02. http://www.jaxa.jp/press/2009/04/20090402_cft_e.html. 
  10. ↑ "The Second Captive Firing Test for the First Stage Flight Model Tank for the H-IIB Launch Vehicle". JAXA. 2009-04-17. http://www.jaxa.jp/press/2009/04/20090417_cft_e.html. 
  11. ↑ "Result of the Second Captive Firing Test for the First Stage Flight Model Tank of the H-IIB Launch Vehicle". JAXA. 2009-04-22. http://www.jaxa.jp/press/2009/04/20090422_cft_e.html. 
  12. ↑ "Postponement of the Second Captive Firing Test (CFT) of the First Stage Flight Model Tank for the H-IIB Launch Vehicle". JAXA. 2009-04-19. http://www.jaxa.jp/press/2009/04/20090419_cft_e.html. 
  13. ↑ "Results of the H-IIB Launch Vehicle Ground Test Vehicle (GTV) Test". JAXA. 2009-07-11. http://www.jaxa.jp/press/2009/07/20090711_gtv_e.html. 
  14. ↑ 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
  15. ↑ "H-IIB". H-IIB Launch Vehicle. Japanese Aerospace Exploration Agency. 2009-07-15. http://www.jaxa.jp/pr/brochure/pdf/01/rocket05.pdf. 
  16. ↑ "Japan's space freighter in orbit". Jonathan Amos. BBC. 2009-08-10. http://news.bbc.co.uk/2/hi/science/nature/8249357.stm. 

External links



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