H-IIA

Expendable medium-lift launch vehicle / From Wikipedia, the free encyclopedia

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H-IIA (H-2A) is an active expendable launch system operated by Mitsubishi Heavy Industries (MHI) for the Japan Aerospace Exploration Agency. These liquid fuel rockets have been used to launch satellites into geostationary orbit; lunar orbiting spacecraft; Akatsuki, which studied the planet Venus; and the Emirates Mars Mission, which was launched to Mars in July 2020. Launches occur at the Tanegashima Space Center. The H-IIA first flew in 2001. As of December 2021, H-IIA rockets were launched 45 times, including 39 consecutive missions without a failure, dating back to 29 November 2003.

Quick facts: Function, Manufacturer, Country of origin, Co...
H-IIA
H_IIA_No._F23_with_GPM_on_its_way_to_the_launchpad.jpg
H-IIA No. F23 rolls out to the launch pad in February 2014
FunctionMedium-lift launch vehicle
Manufacturer
Country of originJapan
Cost per launchUS$90 million
Size
Height53 m (174 ft)
Diameter4 m (13 ft)
Mass285,000–445,000 kg (628,000–981,000 lb)
Stages2
Capacity
Payload to LEO
Mass10,000–15,000 kg (22,000–33,000 lb)
Payload to GTO
Mass4,100–6,000 kg (9,000–13,200 lb)
Associated rockets
FamilyH-II
Derivative workH-IIB
Launch history
StatusActive
Launch sitesTanegashima, LA-Y
Total launches
  • 46
    • 202: 31
    • 204: 5
    • 2022: 3
    • 2024: 7
Success(es)
  • 45
    • 202: 31
    • 204: 5
    • 2022: 3
    • 2024: 6
First flight
  • 202: 29 August 2001
  • 204: 18 December 2006
  • 2022: 26 February 2005
  • 2024: 4 February 2002
Last flight
  • 202: 26 January 2023 (active)
  • 204: 22 December 2021
  • 2022: 14 September 2007
  • 2024: 23 February 2008
Type of passengers/cargo
Boosters – SRB-A
No. boosters2–4
Height15.1 m
Diameter2.5 m
Maximum thrust2,260 kN (510,000 lbf)
Total thrust4,520–9,040 kN (1,020,000–2,030,000 lbf)
Specific impulse280 s (2.7 km/s)
Burn time120 seconds
PropellantHTPB
Boosters (2022, 2024) – Castor 4A-XL
No. boosters2–4
Maximum thrust745 kN (167,000 lbf)
Total thrust1,490–2,980 kN (330,000–670,000 lbf)
Specific impulse280 s (2.7 km/s)
Burn time60 seconds
PropellantSolid
First stage
Height37.2 m
Diameter4 m
Powered by1 LE-7A
Maximum thrust1,098 kN (247,000 lbf)
Specific impulse440 s (4.3 km/s)
Burn time390 seconds
PropellantLH2 / LOX
Second stage
Height9.2 m
Diameter4 m
Powered by1 LE-5B
Maximum thrust137 kN (31,000 lbf)
Specific impulse447 s (4.38 km/s)
Burn time534 seconds
PropellantLH2 / LOX
Close
H-IIA_F19_launching_IGS-O4.jpg
The Liftoff of H-IIA Flight 19
H-IIA_Family.png
The H-IIA rocket lineup
H-IIA-Launch-Vehicle.png
The H-IIA

Production and management of the H-IIA shifted from JAXA to MHI on 1 April 2007. Flight 13, which launched the lunar orbiter SELENE, was the first H-IIA launched after this privatization.[1]

The H-IIA is a derivative of the earlier H-II rocket, substantially redesigned to improve reliability and minimize costs. There have been four variants, with two in active service (as of 2020) for various purposes. A derivative design, the H-IIB, was developed in the 2000s and made its maiden flight in 2009.