H-II

The H- II is a Japanese carrier rocket. Despite the name similarity to HI they presented represents a completely new development

The three to four-digit volume label is derived from the rocket and the coming to the use of boosters. The first digit represents the missile (1 = H II 2 = H IIA, IIB 3 = H ) and the subsequent figures, the number of each LRBS, SRBs and SSBs.

H- II

The development of the H- II rocket began in 1986 to pursue a similar concept as the Ariane 5. During two solid rocket boosters provide the necessary takeoff thrust, a single engine for the main acceleration is responsible. Of H - II, involves the liquid oxygen / hydrogen ( = LOX/LH2 oxygenate liquid / liquid hydrogen), and after the main power process operated LE -7 hydraulically swiveling nozzle. These engines represented a big step for the Japanese space, but brought in their cost-intensive development ( 800 million U.S. dollars of the $ 2.3 billion total cost of the missile ) and some problems. The test of the engine began in 1988 with 1989, two tests failed, which delayed the first flight by two years. Combined with a modified and adopted by the HI second stage with the modern and restartable LE -5A engine with also hydraulically swiveling nozzle that H- II is capable of up to 10 tonnes of payload into low earth orbit (LEO ) to transport. There they were with two different payload fairings with 4.1 m and 5 m in diameter. The latter was once the third launch of the rocket used was where the rocket additionally by two side-mounted Nissan Castor IV AXL Feststoffboster ( licensed production of Thiokol ) with 9.5 m length, each 10 t -off weight and the 600 kN thrust support.

Although the H- II was technically up to date, prevented the high complexity of the rocket and the high start up costs and low reliability associated with commercial success, so that the production set and the H-IIA was developed. Today there is still a copy in front of the visitor center of the start site.

• First flight: February 3, 1994
• Starts: 7, of which one false start and 1 partial success
• Reliability: 71.4 %
• Start-up costs: $ 190 million (1994 )

H-IIA

To make the H II structure also commercially competitive, the start-up costs had to be massively reduced. To achieve this, the concept has been made ​​more flexible. Also, the design of the booster is operated with HTPB have been used (now for shorter composed of one piece instead of segments ), the step transition (now carbon fiber construction) and the tank construction simplified. Thus, it is possible through the use of various solid rocket boosters (SRB or SSB) and originally planned, but later abandoned boosters with liquid fuels ( LRB ) to cover a large payload area and to keep the costs low. Were similar to those planned as the LRB of Delta IV Heavy one or even two first stage. Even with the engines, there were changes, the side-mounted on the H- II turbopump of the LE -7A Erststufentriebwerkes were now mounted above which, causing the engine extended accordingly. The modified second-stage engine LE -5B provides 13% more thrust. Instead of just two five different payload fairings are available with lengths between 12 m and 16 m and diameters between 4.07 m and 5.10 m now. The rocket is available on the commercial market as of Fiscal Year 2007. Largely unknown till now, the military use of the H-IIA. So were four of her starts exposure of reconnaissance satellites to monitor North Korea.

• First flight: 2001
• Starts: 18, of which one false start
• Reliability: 94.4 %
• Start-up costs: 9,3 and 12 billion yen / 85 and 110 million U.S. $ (depending on the booster configuration and time spent on the launch pad ) (prior exchange rates: November 26, 2007)

Possible booster combinations and corresponding carrier designations:

• H-IIA -202 (operating): 2 × SRB -A
• H-IIA -204 (operating): 4 × SRB -A
• H-IIA -2022 (operating): 2 × SRB -A 2 × SSB
• H-IIA -2024 (operating): 2 × SRB -A 4 × SSB

H -IIB

The H -IIB ( formerly called H-IIA -304 ) is a further development of the H-IIA rocket, which is designed for heavier payloads, like the HTV ( 16.5 t). The missile has a first stage with a larger diameter (5.2 m instead of 4 m ) and two LE -7A engines, and four lateral solid-fuel booster (length 56 m, mass 551 t). The GTO payload capacity should be about 8 tons. The development of the missile was started in 2004 with a budget of about 20 billion yen ( equivalent to about 150 million euros ).

On 2 April and 22 April 2009 were test firings take place at the launch site in Tanegashima, both of which were successful.

It was followed on July 11, 2009, an intensive test with subsequent start simulation ( Ground Vehicle test) in the almost complete H -IIB rocket was subjected to a simulated countdown to the launch pad. Only the payload adapter, the payload and the fairing missing in this test.

The first start on 10 September 2009 was known as the TF-1 (TF = Test Flight). Here, the space shuttle H-2 Transfer Vehicle ( HTV ) was successfully launched into space.

Specifications

The boosters are powered by solid fuel. In the first and second stage respectively LOX and LH2 is used as a rocket propellant

1) Boden-/Vakuumschub