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MHI Launch Services:Launch Vehicles [ SPACE ]

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Launch Vehicle Family

H-IIA
H2A202
H2A202
Standard type of the H-IIA family
53meters/289metric tons
H-IIA
H2A204
H2A204
Heavier version of the H-IIA
53meters/443metric tons
H-IIB
H2B
H2B
Enhanced version of the H-IIA in launch capability points
56meters/531metric tons
H3
H3
H3
Much more 'Customer-oriented' launch vehicle (Under Development)
approximately 63meters

H-IIA User's Manual

H-IIA User's Manual

User’s Manual focused on the interface of your satellite and the H-IIA Launch Vehicle

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

H-IIA Launch Vehicle Family

H2A202
H2A204

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
  • 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

Configuration

H2A202 Launch Vehicle

H2A202 Launch Vehicle Configuration

  1. Payload Fairing
  2. Satellite (Spacecraft)
  3. Payload Adapter
  4. Payload Support Structure
  5. Cryogenic Helium Gas Bottles
  6. Second Stage Liquid Hydrogen Tank
  7. Second Stage Liquid Oxygen Tank
  8. Avionics Equipment Panel
  9. RCS (Reaction Control System)
  10. Ambient Helium Gas Bottles
  11. Second Stage Engine (LE-5B Engine)
  12. Interstage Section
  13. First Stage Liquid Oxygen Tank
  14. Center Body Section
  15. First Stage Liquid Hydrogen Tank
  16. Solid Rocket Boosters (SRB-A)
  17. First Stage Engine Section
  18. Auxiliary Engine
  19. Ambient He bottles
  20. First Stage Engine (LE-7A Engine)
  21. SRB-A Movable Nozzle

H2A204 Launch Vehicle

H2A204 Launch Vehicle Configuration

  1. Payload Fairing
  2. Satellite (Spacecraft)
  3. Payload Adapter
  4. Payload Support Structure
  5. Cryogenic Helium Gas Bottles
  6. Second Stage Liquid Hydrogen Tank
  7. Second Stage Liquid Oxygen Tank
  8. Avionics Equipment Panel
  9. RCS (Reaction Control System)
  10. Ambient Helium Gas Bottles
  11. Second Stage Engine (LE-5B Engine)
  12. Interstage Section
  13. First Stage Liquid Oxygen Tank
  14. Center Body Section
  15. First Stage Liquid Hydrogen Tank
  16. Solid Launch Vehicle Boosters (SRB-A)
  17. First Engine Section
  18. Auxiliary Engine
  19. Ambient He bottles
  20. First Stage Engine (LE-7A Engine)
  21. SRB-A Movable Nozzle

H-IIB Launch Vehicle

The H-IIB launch vehicle is a heavier version compared to the H-IIA launch vehicle. Based on the technology of the H-IIA, has achieved vastly increases in its launch capacity through enhanced rocket engine propulsion power and larger satellite fairing.

The H-IIB launch vehicle is a two-stage rocket using liquid oxygen and liquid hydrogen as propellant and has four strap-on solid rocket boosters (SRB-A). First stage of the H-IIB has two liquid rocket engines (LE-7A) and it has four SRB-As attached to the body, while the standard version of the H-IIA has one LE-7A engine and two SRB-As. In addition, the H-IIB's first-stage has expanded to 5.2m in diameter from 4m of the H-IIA's one. The total length of the first stage has also extended by 1m from that of the H-IIA. As the result of such enhancement, the on-board propellant of the H-IIB is 1.7 times more than the H-IIA. The H-IIB has developed based on the technology and the reliability that we have cultivated in development of the H-IIA.

The H-IIB launch vehicle launches the H-II Transfer Vehicle (HTV) as one of transportation to the International Space Station (ISS).

H-IIB Launch Vehicle

Overall

Type H2B H2A204 (Ref)
Height 56 meters 53 meters
Gross Mass 531 metric tons
(excluding satellite mass)
443 metric tons
(excluding satellite mass)
First Stage 2 (2 LE-7As) 1 (1 LE-7A)
Second Stage 1 (1 LE-5B) 1 (1 LE-5B)
SRB-A 4 4
Launch Capacity GTO 8.0 metric tons 6.0 metric tons
Orbit for HTV 16.5 metric tons -

Each Stage

  First Stage Solid Rocket Booster
(SRB-A)
Second Stage
Propellant LH2/LOX HTPB Composite LH2/LOX
Propellant Mass 177.8 metric tons 263.8 metric tons
(for 4 SRB-As in total)
16.6 metric tons
Propulsion System LE-7A Engine - LE-5B Engine
Thrust 2,196 kN 9,220 kN 137 kN
Burning Time 352 minutes 114 minutes 499 minutes
Impulse to weight ratio 440 minutes 283.6 minutes 448 minutes
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 TrackingRange Safety Command Receiver
Electrical Power

Configuration

H2B Launch Vehicle

H2B Launch Vehicle Configuration

  1. Payload Fairing
  2. Satellite (Spacecraft)
  3. Payload Adapter
  4. Payload Support Structure
  5. Cryogenic Helium Gas Bottles
  6. Second Stage Liquid Hydrogen Tank
  7. Second Stage Liquid Oxygen Tank
  8. Avionics Equipment Panel
  9. RCS (Reaction Control System)
  10. Ambient Helium Gas Bottles
  11. Second Stage Engine (LE-5B Engine)
  12. Interstage Section
  13. First Stage Liquid Oxygen Tank
  14. Center Body Section
  15. First Stage Liquid Hydrogen Tank
  16. Solid Rocket Boosters (SRB-A)
  17. First Stage Engine Section
  18. Auxiliary Engine
  19. Ambient He bottles
  20. First Stage Engine (LE-7A Engine)
  21. SRB-A Movable Nozzle

H3 Launch Vehicle

To meet global launch service demands for a wide range of payloads JAXA and MHI has been developing the H3 as a next-generation launch vehicle for Japan.

To offer even better launch services, the H3 will provide more launch opportunities by shortening the lead-time from contract to launch.

Moreover, the H3 will offer enhanced reliability through improved hardware and software. It will also be designed to provide a more relaxing satellite interface environment for customers.

In addition, costs will be drastically reduced by automating assembly and utilizing commercially available components. The maiden flight of H3 is planned in 2020.

H3 Launch Vehicle

Overall

Type H3 H2A204 (Ref)
Height approximately 63 meters 53 meters
Gross Mass T.B.D 443 metric tons
(excluding satellite mass)
First Stage (LE-9) X2 or X3  (LE-7A) X1
Second Stage  (LE-5B-3) X1  (LE-5B) X1
SRB-A Upgrade 0/2/4 4
Launch Capacity GTO 6.5 metric tons 6.0 metric tons

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