H-IIA Launch Vehicle

Here are charts and drawings showing the major characteristics and launch capability of H-IIA Standard Type, and H-IIA Launch Vehicle Family.

Major Characteristics

Major Specifications of the H-IIA launch vehicle

Length (m) 53
Liftoff mass (t) 289 (without payload mass)
Guidance Method Inertial Guidance Method



Item
First StageSRB-ASSBSecond StagePayload
fairing
(4S)
Length (m) 37.2 15.1 14.9 9.2 12
Diameter (m) 4 2.5 1 4 4.07
Mass (t) 114 151 (2 units) 31 (2 units) 20 1.4
Propellant mass 101.1 130 (2 units) 52.4 (4 units) 16.9 -
Thrust (KN) 1,098 5,040 (2 units) 1,490 (2 units) 137 -
Burning time (s) 390 100 60 530 -
Propellant Lox/LH2 Polybutadiene composite solid propellant Polybutadiene composite solid propellant Lox/LH2 -
Propellant Loading Method Turbo pomp - - Turbo pomp -
Specific Impulse (s) 440 283 282 448 -
Attitude control method Gimbal engine system
Auxiliary engine
Gimballed nozzle system Gimballed nozzle system Gimbal engine system
Gas jet system
-
Avionics Control Systems,
Telemetry Transmitter
- - Guidance Navigation,
and Control Systems,
Rader Transponder,
Telemetly Transmitter,
Command Destruct Receiver
-


Launch Capability (H-IIA Standard)

OrbitAltitudePayloads
Geosynchronous Transfer Orbit
(GTO)
about 36,000km about 4t
Low Earth Orbit
(Inclination:30 degrees
about 300km about 10t
Sun Synchronous Orbit
(Summer/Other seasons)
about 800km about 4t /
about 3.8t
Escape from the Earth Gravitation Planetary Mission about 2.5t



H-IIA Lineup

H-IIA Launch Vehicle can be in various configurations by installing solid rocket boosters (SRB-As) additionally. H-IIA can answer various launch needs of payload size and weight by its family members.


- Currently, only H2A202 and H2A204 types are in operation.