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H-IIA Launch Vehicle

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.

H-IIA Launch Vehicle Family

Overall

Type H2A202 H2A204
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
  • (Notes) Geostationary Transfer Orbit (GTO)

Each Stage

  First Stage Solid Rocket
Booster (SRB-A)
(Used for H2A202)
Second Stage
Propellant LH2/LOX HTPB Composite LH2/LOX
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
VHF Telemetry
Electrical Power
- Guidance Control Computer
Inertial Measurement Unit
Flight Termination System
UHF Telemetry
C-Band Tracking
Range Safety Command Receiver
Electrical Power

Payload Fairing/Adapter

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.

Payload Fairing

Fairing for Single Launch

  • Model 4S, Model 5S

Fairing for Dual Launch

  • Model 4/4D-LS, Model 4/4D-LC

Payload Adapter

Payload Adapter for the H-IIA Launch Vehicle

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.

The H-IIA can accept all major satellite buses.

Type PLA (Notes) 937M PLA 1194M PLA 1666MA
PLA 937M PLA 1192M PLA 1666MA
Compatible
Satellite Buses (Example)
Star-2 series LS1300
A2100 Series
Eurostar Series
Spacebus Series
Boeing702B Series
DS2000
DS2000
  • (Notes) PLA: Abbreviation of PayLoad Adaptor.
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