H2 (original) (raw)

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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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