The H-IIA Launch Vehicle is a high-performance rocket consisted from a First stage, Second stage, fairing, one or two pairs of Solid Rocket Boosters (SRB-As). The propulsion system runs on liquid hydrogen and liquid oxygen. Two models are produced, the standard type H2A202 with two SRB-A's and the H2A204 type with four SRB-A's attached.
The First stage of the H-IIA Launch Vehicle consists of a high-performance LE-7A engine, an engine section, a propulsion system tank charged with liquid hydrogen and liquid oxygen, a center section connecting the tanks, and an interstage section mating the First and Second stages. A Solid Rocket Booster (SRB-A) has also been newly developed to boost the thrust from the main engine. Two or four SRB-A's installed on the H-IIA Launch Vehicle are attached to the First stage.
The Second stage consists of a highly reliable LE-5B engine, a propulsion system tank charged with liquid hydrogen and liquid oxygen, on-board electronic devices, etc. As a key feature for launch mission support, the LE-5B engine can be ignited up to three times.
|Height||53 meters||53 meters|
|Gross Mass||289 metric tons (excluding satellite mass)||443 metric tons (excluding satellite mass)|
|First Stage||1 (1 LE-7A)||1 (1 LE-7A)|
|Second Stage||1 (1 LE-5B)||1 (1 LE-5B)|
|Solid Rocket Booster||2||4|
|Launch Capacity(Notes)||4.0 metric tons||6.0 metric tons|
|First Stage||Solid Rocket
(Used for H2A202)
|Propellant Mass||100 metric tons||65 metric tons (each)||16.6 metric tons|
|Propulsion System||LE-7A Engine||-||LE-5B Engine|
|Thrust||1,098 kN||2,520 kN (each)||137 kN|
|Burning Time||390 second||100 second||Multiple Re-ignition Capability
Idle Mode Function
|Impulse to weight ratio||440 second||283 second||448 second|
|Avionics System||Guidance Control Computer
Flight Termination System
Rate Gyro Package
Lateral Acceleration Sensor Unit
|-||Guidance Control Computer
Inertial Measurement Unit
Flight Termination System
Range Safety Command Receiver
The payload fairing protects the satellite from harsh environmental conditions as the launch vehicle conveys the customer's satellite securely through the atmosphere into orbit. The PayLoad Adapter (PLA) mates the satellite with the launch vehicle.
The H-IIA can be launched with a versatile range of fairings and payload adapters for compatibility with major satellite models and launch support to meet customer requirements.
Fairing for Single Launch
Fairing for Dual Launch
Here we introduce the typical payload adapters produced domestically in Japan. If the customer requires, we can also provide global standard adapters from overseas manufacturers, for compatibility with any interface.
|Type||PLA (Notes) 937M||PLA 1194M||PLA 1666MA|
Satellite Buses (Example)