H-II
Dwarfing its predecessor, the H-II consists of a 2-stage core vehicle, burning liquid oxygen and liquid hydrogen in both stages, with two large solid-propellant strap-on boosters. Nissan produces the 4-segmented
strap-on boosters which are considerably larger than the main stages of ISAS' M-3 and M-5 series vehicles. The LE-7 first-stage main engine overcame numerous developmental difficulties, while the LE-5A engine used by the second stage merely represents an upgraded version of the proven LE-5 flown on the second stage of the H-I (References 125-133).
H-II (Japan) |
 |
Background Information
- First Launch:
- February 1994
- Flight Rate:
- 1-2 per year
- Launch Site:
- Yoshinobu Launch Complex (Tanegashima, Japan)
- Capability:
- 23,000 lb to 100 NM circular, 30° orbit;14,000 lb to 100 NM circular, 90° orbit; 8,800 lb to GTO; 4,800 lb to GEO
History
- H-II development began in April 1985
- First launch February 1994
- Eight missions scheduled through 1999
Description
- Two-stage vehicle with two strap-on solid boosters
- Stage 1 burns LH2/LO2 in one Mitsubishi LE-7 engine, generating 189,596 lb of thrust at sea level
- Stage 2 burns LH2/LO2 in one Mitsubishi LE-5A engine, generating 27,313 lb of thrust (vacuum)
- Two Nissan solid strap-ons burn HTPB/AP/AI, generating 350,688 lb of thrust each
Profile
- Length:
- 164.1 ft
- Launch Weight:
- 573,040 lb
- Diameter:
- 13.13 ft
- Liftoff Thrust:
- 890,972 lb
- Payload Fairing:
- 39.4 ft x 13.5 ft (16.4 ft diameter fairing available)
|
