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- H-IIB Launch Vehicle
- H-IIA Launch Vehicle
- KOUNOTORI (HTV)
- S-310/S-520/SS-520
- « Development »
- Epsilon Launch Vehicle
- Human Space Activities
- Satellites & Spacecraft
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Here are charts and drawings showing the major characteristics and launch capability of H-IIB.
Major Characteristics (H-IIB Test Flight)
| Length (m) | 56.6 |
|---|---|
| Mass (t) | 531 (without payload mass) |
| Guidance Method | Inertial Guidance Method |
| Item | ||||
|---|---|---|---|---|
| First Stage | Solid Rocket Booster (SRB-A) | Second Stage | Payload Fairing (5S-H) |
|
| Height (m) | 38 | 15 | 11 | 15 |
| Outside diameter (m) | 5.2 | 2.5 | 4.0 | 5.1 |
| Mass (t) | 202 | 306 (for four SRB-As in total) | 20 | 3.2 |
| Propellant mass (t) | 177.8 | 263.8 (for four SRB-As in total) | 16.6 | - |
| Thrust (kN)*1 | 2,196 | 9,220 | 137 | - |
| Combustion time (s) | 352 | 114 | 499 | - |
| Propellant type | Liquid oxygen/hydrogen | Polybutadiene composite solid propellant | Liquid oxygen/hydrogen | - |
| Propellant supply system | Turbo pump | - | Turbo pump | - |
| Impulse to weight ratio (s)*1 | 440 | 283.6 | 448 | - |
| Attitude control method | Gimbal | Movable nozzle | Gimbal gas jet system | - |
| Major onboard avionics | Guidance control equipment Telemetry transmitter |
- | Guidance control equipment Radar transponder Telemetry transmitter Command destruct system |
- |
*1 In vacuum. Solid rocket booster's thrust is set to the maximum value.
H-IIB Launch Vehicle Launch Capacity
| Orbit | Altitude | Payloads |
|---|---|---|
| Geosynchronous Transfer Orbit (GTO) |
36,000km | 8t |
| Orbit for HTV (Inclination:51.6 degrees) |
350km-460km | 16.5t |