H-II

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H-II

Fact sheet
Function	Launch vehicle
Manufacturer	Mitsubishi Heavy Industries
Country of origin	Japan
Size
Height	49 m (160 ft)
Diameter	4 m (13.1 ft)
Mass	260,000 kg (570,000 lb)
Stages	2
	Capacity
Payload to LEO	10,060 kg (22,170 lb)
Payload to GTO	3,930 kg (8,660 lb)
Launch History
Status	Retired
Launch Sites	LC-Y, Tanegashima
Total launches	7
Successes	4
Failures	1
Partial Failures	2
Maiden flight	3 February 1994
Last flight	15 November 1999
Boosters (Stage 0)
No boosters	2
Engines	1 Solid
Thrust	1,539.997 kN
Specific Impulse	273 sec
Burn time	94 seconds
Fuel	Solid
First Stage
Engines	1 LE-7
Thrust	1,077.996 kN (242,343 lbf)
Specific Impulse	446 sec
Burn time	346 seconds
Fuel	LOX/LH2
Second Stage
Engines	1 LE-5A
Thrust	121.5 kN (27,313 lbf)
Specific Impulse	452 sec
Burn time	600 seconds
Fuel	LOX/LH2

The H-II was a Japanese satellite launch system, which flew seven times between 1994 and 1999, with five successes. It was superseded by the H-IIA following reliability and cost issues.