MHI Launch Services: Launch Vehicles
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Launch Vehicle Family
Standard type of the H-IIA family
53meters/289metric tons
Heavier version of the H-IIA
53meters/443metric tons
Enhanced version of the H-IIA in launch capability points
56meters/531metric tons
Much more 'Customer-oriented' launch vehicle (Under Development)
approximately 63meters
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 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 Engine | LE-7A×1 | LE-7A×1 |
| Second Stage Engine | LE-5B×1 | LE-5B×1 |
| 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 Configuration
- Payload Fairing
- Satellite (Spacecraft)
- Payload Adapter
- Payload Support Structure
- Cryogenic Helium Gas Bottles
- Second Stage Liquid Hydrogen Tank
- Second Stage Liquid Oxygen Tank
- Avionics Equipment Panel
- RCS (Reaction Control System)
- Ambient Helium Gas Bottles
- Second Stage Engine (LE-5B Engine)
- Interstage Section
- First Stage Liquid Oxygen Tank
- Center Body Section
- First Stage Liquid Hydrogen Tank
- Solid Rocket Boosters (SRB-A)
- First Stage Engine Section
- Auxiliary Engine
- Ambient He bottles
- First Stage Engine (LE-7A Engine)
- SRB-A Movable Nozzle
H2A204 Launch Vehicle Configuration
- Payload Fairing
- Satellite (Spacecraft)
- Payload Adapter
- Payload Support Structure
- Cryogenic Helium Gas Bottles
- Second Stage Liquid Hydrogen Tank
- Second Stage Liquid Oxygen Tank
- Avionics Equipment Panel
- RCS (Reaction Control System)
- Ambient Helium Gas Bottles
- Second Stage Engine (LE-5B Engine)
- Interstage Section
- First Stage Liquid Oxygen Tank
- Center Body Section
- First Stage Liquid Hydrogen Tank
- Solid Launch Vehicle Boosters (SRB-A)
- First Engine Section
- Auxiliary Engine
- Ambient He bottles
- First Stage Engine (LE-7A Engine)
- SRB-A Movable Nozzle
H-IIB Launch Vehicle (Retired)
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).
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 Engine | LE-7A×2 | LE-7A×1 | |
| Second Stage Engine | LE-5B×1 | LE-5B×1 | |
| 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 Configuration
- Payload Fairing
- Satellite (Spacecraft)
- Payload Adapter
- Payload Support Structure
- Cryogenic Helium Gas Bottles
- Second Stage Liquid Hydrogen Tank
- Second Stage Liquid Oxygen Tank
- Avionics Equipment Panel
- RCS (Reaction Control System)
- Ambient Helium Gas Bottles
- Second Stage Engine (LE-5B Engine)
- Interstage Section
- First Stage Liquid Oxygen Tank
- Center Body Section
- First Stage Liquid Hydrogen Tank
- Solid Rocket Boosters (SRB-A)
- First Stage Engine Section
- Auxiliary Engine
- Ambient He bottles
- First Stage Engine (LE-7A Engine)
- 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 Japan’s new flagship rocket.
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 2021 fiscal year.
Overall
| Type | H3 | H2A204 (Ref) | |
|---|---|---|---|
| Height | approximately 63 meters | 53 meters | |
| Gross Mass | T.B.D | 443 metric tons (excluding satellite mass) |
|
| First Stage Engine | LE-9×2 or 3 | LE-7A×1 | |
| Second Stage Engine | LE-5B×1 | LE-5B×1 | |
| SRB-A | Upgrade 0/2/4 | 4 | |
| Launch Capacity | GTO | 6.5 metric tons | 6.0 metric tons |