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The H-IIA Launch Vehicle is a new rocket developed on
a basis of technical results obtained from the development of the
H-II rocket. The H-IIA Launch Vehicle is designed to meet a diversity
of new needs and demands in modern space transportation, including
for the supplementary transports to the International Space Station
and for the spacecrafts to be launched in the 21st century. This launch
vehicle especially meets the current demands of lower costs while
still maintaining a high degree of reliability achieved hitherto.
The standard type H-IIA (H2A202) is length of 52.5 m, diameter of
4 m, and mass of 285 ton without spacecraft mass. It consists of the
first and second stages, fairing, and Solid Rocket Booster-A (SRB-A),
and is the high-powered large-scale launch vehicle equipped with propellant
systems using liquid hydrogen / oxygen.
The first stage consists of the high performance cryogenic LE-7A engine,
the engine section, LH2 tank, the center body section, LOX tank and
the interstage section. Two or four newly developed Solid Rocket Boosters
(SRB-A) are attached to the first stage in order to augment the LE-7A
engine thrust during an ascent phase. In the H2A202 series, two or
four Solid Strap-on Boosters (SSBs) are strapped on according to customers'
performance requirements.
The second stage consists of highly reliable cryogenic LE-5B engine,
LH2 tank, LOX tank and the avionics systems installed on an equipment
panel. The LE-5B engine has a multi-restart capability to meet various
mission requirements. Attitude control is performed using reliable
electromechanical actuators of the LE-5B engine and a hydrazine gas-jet
reaction control system installed on the equipment panel. |
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First
Stage |
Solid Rocket
Booster (SRB-A) |
Solid Strap-on
Booster (SSB) |
Second
Stage |
Total Vehicle |
Overall Length
(m, with 4S or 5S fairing) |
37.2 |
15.2 |
14.9 |
9.2 |
52.5 |
Diameter
(m) |
4 |
2.5 |
1 |
4 |
-- |
Mass
(metric-ton) |
114 |
150 (2 Units) |
31 (2 Units) |
20 |
Approx. 285*
(H2A202) |
Propellant Mass
(metric-ton) |
100 |
130 (2 Units) |
26 (2 Units) |
16.7 |
-- |
Thrust
(in vacuum, kN) |
1,098 |
4,511
(max, 2 Units) |
1,470
(max, 2 Units) |
137 |
-- |
Burning Time
(sec) |
390 |
100 |
60 |
540 |
-- |
| Propellant |
LH2 / LOX |
Solid Propellant |
Solid Propellant |
LH2 / LOX |
-- |
Specific Impulse
(in vacuum, sec) |
440 |
280 |
282 |
447 |
-- |
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| * not including the payload |
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