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H2
Part of H-2
H-2 H-2 - COSPAR 1994-007 |
Heavy lift Japanese indigenous launch vehicle. The original H-2 version was cancelled due to high costs and poor reliability and replaced by the substantially redesigned H-2A.
3 stage vehicle consisted of 2 x H-II SRB + 1 x H-II stage 1 + 1 x H-II stage 2
AKA: H-2. Payload: 10,060 kg (22,170 lb). Thrust: 405,000.00 kN (91,047,000 lbf). Gross mass: 260,000 kg (570,000 lb). Height: 49.00 m (160.00 ft). Diameter: 4.00 m (13.10 ft).
Subtopics
| H-II (2S) Japanese orbital launch vehicle. Three stage version consisting of 2 x H-II SSB boosters + 2 x H-II SRB boosters + core vehicle. |
| H-IIA 212 Japanese orbital launch vehicle. This version uses two core stages side-by-side in an asymmetric configuration, supplemented by two SRB-A solid rocket boosters. |
| H-II HIMES Japanese orbital launch vehicle. Concept of H-2 augmented with Liquid-Air Cycle Engine boosters and advanced HIMES upper stage. |
Country:
Japan.
Spacecraft:
ETS,
Himawari,
FS-1300,
OREX,
VEP,
SFU,
ADEOS,
Fuji,
ETS-7,
ETS-7 Target,
TRMM,
Kakehashi,
LRE,
DASH 2002,
MDS,
DRTS,
USERS,
FedSat,
Mu-Labsat,
WEOS Kanta-Kun,
IGS,
Daichi,
DS2000,
Kaguya,
Kizuna,
Ibuki,
JAXA SDS,
Kagayaki,
KKS,
Kukai,
PRISM,
SOHLA,
SpriteSat.
Launch Vehicles:
H-II,
H-II (2S),
H-IIA 212,
H-IIA,
H-II HIMES,
H-IIA 202,
H-IIA 2024,
H-IIA 2022,
H-IIA 204,
H-IIB.
Launch Sites:
Tanegashima.
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