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Engines H-IIA, H-IIA Heavy & H-IIB
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H-IIA
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Stage |
Engines |
Thrust s.l. |
Isp s.l. |
Thrust vac |
Isp vac |
Propellant |
Burn.time |
Flow rate |
Total Imp |
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- |
- |
kN |
Ns/kg |
kN |
Ns/kg |
t |
s |
t/s |
MN*s |
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Booster |
SSB (Castor IVAXL) | 530.5 | 2342 | 595.1 | 2627 | 13.109 | 57.9 | 0.2265 | 34.4 | |
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Booster |
SRB-A | 1,670.3 (av.) | 2568 | 1,786.0 (av.) | 2746 | 65.04 | 100 | 0.6504 | 178.6 | |
| SRB-A long | 1,670.3 (av.) | 2568 | 1,786.0 (av.) | 2746 | ~74.80 | ~115 | 0.6504 | 205.4 | ||
| Core | LE-7A | short nozzle | 814.9 | 3196 | 1.073.8 | 4211 | 100 | 392.1 | 0.2550 | 421.1 |
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long nozzle* |
840.4 | 3316 | 1.098.3 | 4332 | 394.5 | 0.2535 | 433.3 | |||
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2 |
LE-5B |
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136.5 |
4384 |
16.60 |
534 |
0.0311 |
72.8 |
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* The first launch with a long nozzle engine was used on flight 8 of H-IIA
H-IIA Heavy
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Stage |
Engines |
Thrust s.l. |
Isp s.l. |
Thrust vac |
Isp vac |
Propellant |
Burn.time |
Flow rate |
Total Imp |
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- |
- |
kN |
Ns/kg |
kN |
Ns/kg |
t |
s |
t/s |
MN*s |
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| Booster | SRB-A long | 1,670.3 (av.) | 2568 | 1,786.0 (av.) | 2746 | ~74.80 | ~115 | 0.6504 | 205.4 | |
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LRB |
LE-7A (2) | short nozzle | 1,629.8 | 3196 | 2,147.6 | 4211 | 99.20 | 194.5 | 0.5100 | 417.7 |
| Core | LE-7A |
long nozzle |
840.4 | 3316 | 1,098.3 | 4332 | 100 | 394.5 | 0.2535 | 433.3 |
| 2 | LE-5B | 136.5 | 4384 | 16.60 | 534 | 0.0311 | 72.8 | |||
H-IIB
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Stage |
Engines |
Thrust s.l. |
Isp s.l. |
Thrust vac |
Isp vac |
Propellant |
Burn.time |
Flow rate |
Total Imp |
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- |
- |
kN |
Ns/kg |
kN |
Ns/kg |
t |
s |
t/s |
MN*s |
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| Booster | SRB-A long | 1,670.3 (av.) | 2568 | 1,786.0 (av.) | 2746 | ~74.80 | ~115 | 0.6504 | 205.4 | |
| Wide Core | LE-7A (2) | long nozzle | 1,680.8 | 3316 | 2,196.6 | 4332 | 169.85 | 335 | 0.5070 | 735.9 |
| 2 | LE-5B | 136.5 | 4384 | 16.60 | 534 | 0.0311 | 72.8 | |||
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