H-IIA

H-IIA

H-IIA No. F23 rolls out to the launch pad in February 2014
Function	Launch vehicle
Manufacturer	Mitsubishi Heavy Industries (prime) ATK (sub)
Country of origin	Japan
Size
Height	53 m (173 ft)
Diameter	4 m (13.1 ft)
Mass	285,000 - 445,000 kg (628,317 - 981,057 lb)
Stages	2
Capacity
Payload to LEO	10,000 - 15,000 kg (22,046 - 33,069 lb)
Payload to GTO	4,100 - 6,000 kg (9,038 - 13,227 lb)
Launch history
Status	Active
Launch sites	LA-Y, Tanegashima
Total launches	32 (202: 19, 204: 3, 2022: 3, 2024: 7)
Successes	31 (202: 19, 204: 3, 2022: 3, 2024: 6)
Failures	1 (2024)
First flight	202: 29 August 2001 204: 18 December 2006 2022: 26 February 2005 2024: 4 February 2002
Notable payloads	SELENE Greenhouse Gases Observing Satellite Akatsuki
Boosters (All Variants) - SRB-A, SRB-A3
No. boosters	2 - 4
Engines	1 Solid
Thrust	4,520 - 9,040kN (SRB-A)
Specific impulse	280 seconds (2.7 km/s)
Burn time	120 seconds
Fuel	Solid
Boosters (H-IIA 2022/2024) - Castor 4AXL
No. boosters	2 - 4
Engines	1 Solid
Specific impulse	283 seconds (2.78 km/s)
Burn time	60 seconds
Fuel	Solid
First stage
Engines	1 LE-7A
Thrust	1,098 kN (246,840 lbf)
Specific impulse	440 seconds (4.3 km/s)
Burn time	390 seconds
Fuel	LOX/LH2
Second stage
Engines	1 LE-5B
Thrust	137 kN (30,798 lbf)
Specific impulse	447 seconds (4.38 km/s)
Burn time	534 seconds
Fuel	LOX/LH2

Mitsubishi Heavy Industries (prime)

H-IIA (H2A) is an active expendable launch system operated by Mitsubishi Heavy Industries (MHI) for the Japan Aerospace Exploration Agency. The liquid-fueled H-IIA rockets have been used to launch satellites into geostationary orbit, to launch a lunar orbiting spacecraft, and to launch an interplanetary space probe to Venus. Launches occur at the Tanegashima Space Center. The H-IIA first flew in 2001 and has been launched 30 times by February 2016.

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

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

The launch capability of an H-IIA launch vehicle can be enhanced by adding SRB-A (solid rocket booster or SRB) and Castor 4AXL (solid strap-on booster or SSB) to its basic configuration, creating a "family". The models are indicated by three or four numbers following the prefix "H2A". The first number in the sequence indicates the number of stages; the second number of liquid rocket boosters (LRBs); the third number of SRBs; and, if present, the fourth number shows the number of SSBs. The first two figures are virtually fixed at "20", as H-IIA is always two-staged, and the plans for LRBs were cancelled and superseded by the H-IIB.