Matches in DBpedia 2014 for { <http://dbpedia.org/resource/H-II> ?p ?o. }
- H-II diameter "4.0".
- H-II height "49000.0".
- H-II mass "260000.0".
- H-II lowerEarthOrbitPayload "10060.0".
- H-II mass "260000.0".
- H-II abstract "The H-II (H2) rocket was a Japanese satellite launch system, which flew seven times between 1994 and 1999, with five successes. It was developed by NASDA in order to give Japan a capability to launch larger satellites in the 1990s. It was the first two-stage liquid-fuelled rocket Japan made using only technologies developed domestically. It was superseded by the H-IIA rocket following reliability and cost issues.".
- H-II countryOrigin Japan.
- H-II diameter "4.0".
- H-II failedLaunches "1".
- H-II finalFlight "1999-11-15".
- H-II height "49.0".
- H-II launchSite Tanegashima_Space_Center.
- H-II launchSite Yoshinobu_Launch_Complex.
- H-II lowerEarthOrbitPayload "1.006E7".
- H-II maidenFlight "1994-02-03".
- H-II manufacturer Mitsubishi_Heavy_Industries.
- H-II mass "2.6E8".
- H-II partialFailedLaunches "1".
- H-II rocketFunction Launch_vehicle.
- H-II rocketStages "2".
- H-II status "Retired".
- H-II successfulLaunches "5".
- H-II thumbnail H-ii_adeos.gif?width=300.
- H-II totalLaunches "7".
- H-II wikiPageExternalLink index_e.html.
- H-II wikiPageID "8519352".
- H-II wikiPageRevisionID "580312966".
- H-II altDiameter "13.1".
- H-II altHeight "160.0".
- H-II altLeo "22170.0".
- H-II altMass "570000.0".
- H-II altPayload "8660.0".
- H-II altStage1thrust "242343".
- H-II altStage2thrust "27313".
- H-II boosterengines "1".
- H-II boosterfuel Solid-fuel_rocket.
- H-II boosters "2".
- H-II boostersi "273.0".
- H-II boosterthrust "1,539.997 kN".
- H-II boostertime "94.0".
- H-II caption "The launch of H-II Flight 4, carrying ADEOS I".
- H-II countryOrigin Japan.
- H-II diameter "4 m".
- H-II fail "1".
- H-II first "1994-02-03".
- H-II function Launch_vehicle.
- H-II hasPhotoCollection H-II.
- H-II height "49 m".
- H-II last "1999-11-15".
- H-II launches "7".
- H-II leoPayload "10060.0".
- H-II manufacturer Mitsubishi_Heavy_Industries.
- H-II mass "260000.0".
- H-II name "H-II".
- H-II partial "1".
- H-II payload "3930.0".
- H-II payloadLocation Geostationary_transfer_orbit.
- H-II sites Tanegashima_Space_Center.
- H-II sites Yoshinobu_Launch_Complex.
- H-II stage1engines "1".
- H-II stage1fuel Liquid_hydrogen.
- H-II stage1fuel Liquid_oxygen.
- H-II stage1si "446.0".
- H-II stage1thrust "1,077.996 kN".
- H-II stage1time "346.0".
- H-II stage2engines "1".
- H-II stage2fuel Liquid_hydrogen.
- H-II stage2fuel Liquid_oxygen.
- H-II stage2si "452.0".
- H-II stage2thrust "121.5 kN".
- H-II stage2time "600.0".
- H-II stages "2".
- H-II status "Retired".
- H-II success "5".
- H-II subject Category:Mitsubishi_Heavy_Industries_space_launch_vehicles.
- H-II subject Category:Space_launch_vehicles_of_Japan.
- H-II type Artifact100021939.
- H-II type Conveyance103100490.
- H-II type Instrumentality103575240.
- H-II type MitsubishiHeavyIndustriesLaunchVehicles.
- H-II type Object100002684.
- H-II type PhysicalEntity100001930.
- H-II type Rocket104099429.
- H-II type Vehicle104524313.
- H-II type Whole100003553.
- H-II type MeanOfTransportation.
- H-II type Rocket.
- H-II type RocketEngine.
- H-II type DesignedArtifact.
- H-II comment "The H-II (H2) rocket was a Japanese satellite launch system, which flew seven times between 1994 and 1999, with five successes. It was developed by NASDA in order to give Japan a capability to launch larger satellites in the 1990s. It was the first two-stage liquid-fuelled rocket Japan made using only technologies developed domestically. It was superseded by the H-IIA rocket following reliability and cost issues.".
- H-II label "H-II (foguete)".
- H-II label "H-II".
- H-II label "H-II".
- H-II label "H-II".
- H-II label "H-II".
- H-II label "H-II".
- H-II label "H-IIロケット".
- H-II label "H-II运载火箭".
- H-II sameAs H-II.
- H-II sameAs H-II.