H-II

H-II

H-II rocket at Tsukuba science museum & planetarium
Function	Medium-lift launch vehicle
Manufacturer	Mitsubishi Heavy Industries Nissan Motors (sub) Alliant Techsystems (sub, for the SRBs)
Country of origin	Japan
Size
Height	49 m (161 ft)
Diameter	4 m (13 ft)
Mass	260,000 kg (570,000 lb)
Stages	2
Capacity
Payload to LEO
Mass	10,060 kg (22,180 lb)
Payload to GTO
Mass	3,930 kg (8,660 lb)
Associated rockets
Family	H-II family
Based on	H-I
Derivative work	H-IIA, H-IIB
Comparable	Ariane 4
Launch history
Status	Retired
Launch sites	Tanegashima, LA-Y1
Total launches	7
Success(es)	5
Failure(s)	1
Partial failure(s)	1
First flight	3 February 1994
Last flight	15 November 1999
Boosters
No. boosters	2
Maximum thrust	1,540 kN (350,000 lbf)
Specific impulse	273 s (2.68 km/s)
Burn time	94 seconds
First stage
Powered by	1 × LE-7
Maximum thrust	1,078 kN (242,000 lbf)
Specific impulse	446 s (4.37 km/s)
Burn time	346 seconds
Propellant	LH2 / LOX
Second stage
Powered by	1 × LE-5A
Maximum thrust	121.5 kN (27,300 lbf)
Specific impulse	452 s (4.43 km/s)
Burn time	600 seconds
Propellant	LH2 / LOX

The H-II (H2) rocket was a Japanese satellite launch system, which flew seven times between 1994 and 1999, with five successes. It was developed by NASDA in order to give Japan a capability to launch larger satellites in the 1990s. It was the first two-stage liquid-fuelled rocket Japan made using only technologies developed domestically. It was superseded by the H-IIA rocket following reliability and cost issues.

Background

Prior to H-II, NASDA had to use components licensed by the United States in its rockets. In particular, crucial technologies of H-I and its predecessors were from the Delta rockets (the manufacturer of the Delta rockets, McDonnell Douglas, later Boeing and the United Launch Alliance, would later use the H-IIA's technologies (the rocket itself is the successor to the H-II) to create the Delta III, albeit short lived). Although the H-I did have some domestically produced components, such as LE-5 engine on the second stage and inertial guidance system, the most crucial part, the first stage engine, was a licence-built version of the Thor-ELT of the US. By developing the LE-7 liquid-fuel engine and the solid booster rockets for the first stage, all stages of H-II had become "domestically developed".

The H-II was developed under the following policies, according to a NASDA press release:

1. Develop the launch vehicle with Japanese space technology.
2. Reduce both development period and costs by utilizing developed technologies as much as possible.
3. Develop a vehicle which can be launched from the existing Tanegashima Space Center.
4. Use design criteria which allows sufficient performance for both the main systems and subsystems. Ensure that development will be carried out properly, and safety is taken into account.

The H-II was new, incorporating larger LH₂/LOX tanks, and a new upper stage, consisting of a cylindrical LH₂ tank with a capsule-shaped LOX tank. The LH₂ tank cylinder carried payload launch loads, while the LOX tank and engine were suspended below within the rocket's inter-stage. The second stage was powered by a single LE-5A engine.

History

Development of the LE-7 engine which started in 1984 was not without hardships, and a worker died in an accidental explosion. The first engine was completed in 1994, two years behind the original schedule. The Rocket Systems Corporation (RSC), a consortium of 74 companies including Mitsubishi Heavy Industries, Nissan Motors, and NEC, was established in 1990 to manage launch operations after the rockets' completion. In 1992, it had 33 employees.

In 1994, NASDA succeeded in launching the first H-II rocket, and succeeded in five launches by 1997. However, each launch cost 19 billion yen (US$190 million), too expensive compared to international competitors like Ariane. (This is in part due to the Plaza Accord's changes to the exchange rate, which was 240 yen to a dollar when the project planning started in 1982, but had changed to 100 yen a dollar by 1994.) Development of the next-generation H-IIA rockets started in order to minimize launch costs.

In 1996, RSC signed a contract with the Hughes Space and Communications Group to launch 10 satellites. The successive failure of flight 5 in 1998 and flight 8 in the following year brought an end to the H-II series and the contract with Hughes. To investigate the cause of the failure and to direct resources into the H-IIA, NASDA cancelled flight 7 (which was to be launched after F8 due to changes in schedule), and terminated the H-II series.

Launch history

Main article: List of H-II series and H3 launches

Flight No.	Date / time (UTC)	Rocket, Configuration	Launch site	Payload	Payload mass	Orbit	Customer	Launch outcome
TF1 (Test Flight)	3 February 1994 22:20	H-II	Yoshinobu Launch Complex	OREX (Orbital Re-entry Experiment), VEP (Vehicle Evaluation Payload)		LEO / GTO		Success
	Ryūsei, Myōjō
TF2	28 August 1994 07:50	H-II	Yoshinobu Launch Complex	ETS-VI (Engineering Test Satellite-VI)		GEO		Success
	Kiku 6
TF3	18 March 1995 08:01	H-II	Yoshinobu Launch Complex	GMS-5 (Geostationary Meteorological Satellite-5) / SFU (Space Flyer Unit)		GEO / LEO		Success
	Himawari 5
F4	17 August 1996 01:53	H-II	Yoshinobu Launch Complex	ADEOS I (Advanced Earth Observing Satellite) / Fuji OSCAR 29, JAS-2		LEO		Success
	Midori, Fuji 3
F6	November 27, 1997 21:27	H-II	Yoshinobu Launch Complex	TRMM (Tropical Rainfall Measuring Mission) / ETS-VII (Engineering Test Satellite-VII)		LEO		Success
	Kiku 7 (Orihime & Hikoboshi)
F5	February 21, 1998 07:55	H-II	Yoshinobu Launch Complex	COMETS (Communications and Broadcasting Engineering Test Satellites)		GEO		Partial failure
	Kakehashi, Faulty brazing in second-stage engine cooling system caused engine burn through and cable damage resulting in shutdown midway through the upper stage's second burn, leaving spacecraft in elliptical LEO instead of GTO. Spacecraft thrusters raised orbit enough to complete some communications experiments.
F8	November 15, 1999 07:29	H-II	Yoshinobu Launch Complex	MTSAT (Multi-functional Transport Satellite)		GEO		Failure
	Cavitation in the first stage hydrogen turbopump impeller caused an impeller blade to fracture, resulting in loss of fuel and rapid shutdown of the engine at T+239 s. The vehicle impacted the ocean 380 km NW of Chichijima.

Gallery

• 
  The Ground Test Vehicle of H-II, now installed at Tsukuba Space Center.
• 
  The first and second stages of the canceled Flight 7, at a hangar in Tanegashima Space Center.

See also

• H-II Orbiting Plane (HOPE)
• H-II Transfer Vehicle (HTV)
• H-II (rocket family)
  • H-IIA
  • H-IIB
• Comparison of orbital launchers families
• Comparison of orbital launch systems

External links

• H-II Launch Vehicle Archived 2013-10-30 at the Wayback Machine, JAXA.